MISSION EVALUATION PRESIMULATION REPORT … 68-723 MISSION EVALUATION PRESIMULATION REPORT Part 1: CSM 104 (Mission D) Operations Plan August 1968 Contract NAS9-150, SA 300, Exhibit

SOV29 1968

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SD 68-723

MISSION EVALUATION PRESIMULATIONREPORT

Part 1: CSM 104 (Mission D)Operations Plan

August 1968

Contract NAS9-150, SA 300, Exhibit I, Paragraph 5. 1. 1. 2

(NASA-CR-129977) MISSION EVALUATIONPBESIHULATION REPORT. PART 1: CSM(MISSION D) OPEBATIONS PLAN (NorthAmerican Rockwell Corp.) Auq. 1968176 p

N73-,70281

Onclas00/99 37204

SPACE DIVISIONNORTH AMERICAN ROCKWELL CORPORATION

SD 68-723

MISSION EVALUATION PRESIMULATIONREPORT

Part 1: CSM 104 (Mission D)Operations Plan

August 1968

Contract NAS9-150, SA 300, Exhibit I, Paragraph 5. 1. 1.2

SPACE DIVISIONNORTH AMERICAN ROCKWELL CORPORATION

SPACE DIVISION OF NORTH AMERICAN ROCKWELL CORPORATION

CONTENTS

Section Page

1.0 INTRODUCTION 1-11.1 Purpose . . . . . . . . . . 1-11 . 2 Mission D G&C Objectives . . . . . . 1 -11 . 3 Simulation Configuration . . . . . . 1 - 21 . 4 Simulation Schedule . . . . . . . 1 - 3

2.0 MISSION DESCRIPTION . . 2-12. 1 Nominal Mission Phases . . . . . . 2-12. 2 Mission Contingency Phases . . . . . 2-5

3.0 STUDY DEFINITION 3-13. 1 Study Phases . 3-13. 2 SPS AV 3-2

3 . 2 . 1 Study Objectives . . . . . . . - • • • 3 - 23 . 2 . 2 Study Scope . . . . . . . . 3 - 33 . 2 . 3 R u n Description . . . . . . . 3 - 33.2 .4 Run Schedule Synopsis . . . . 3-4

3 . 3 Rendezvous . . . . . . . . . 3-483.3. 1 Study Objectives . . . . . . . 3-483. 3. 2 Study Scope 3-483. 3. 3 Run Description . . . . . . . 3-493.3.4 R u n Schedule Synopsis . . . . . 3-50

3.4 Entry 3-763.4.1 Study Objectives 3-763.4. 2 Study Scope 3-763.4.3 R u n Description . . . . . . . 3-773.4.4 R u n Schedule Synopsis . . . . . ' 3-79

3.5 IMU Alignment 3-843. 5. 1 Study Objectives 3-843. 5. 2 Study Scope 3-843.5.3 R u n Description . . . . . . . 3-873. 5.4 Run Schedule Synopsis 3-87

3. 6 Landmark Tracking 3-973 . 6 . 1 Study Objectives . . . . . . . 3-973 . 6 . 2 Study Scope . . . . . . . . 3-973 . 6 . 3 R u n Description . . . . . . . 3-983.6.4 R u n Schedule Synopsis . . . . . 3-98

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Section

3.7 SM Abort 3-1053.7.1 Study Objectives 3-1053. 7. 2 Study Scope 3-1053. 7. 3 Run Description . . . . . . 3-1063. 7.4 Run Schedule Synopsis . . . . 3-108

3.8 RCS Deorbit . 3-1133. 8. 1 Study Objectives . . . . . . . 3-1133. 8. 2 Study Scope . . . . . . . 3-1143. 8. 3 Run Description . . . . . . 3-1143.8.4 Run Schedule Synopsis . . . . . 3-118

3. 9 MCC/ME 103 Joint Simulation . . . . . 3-1183.10 Final Software Verification Test . . . . 3-121

4.0 DATA OUTPUT REQUIREMENTS . . . . . 4-14.1 Analog 4-14 . 2 Environment . . . . . . . . . 4 - 14 . 3 Downlink . . . . . . . . . 4 - 1

APPENDIXREFERENCES A-l

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ILLUSTRATIONS

Figure Page

1-1 Simulation Configuration Flow Diagram . . . . . 1-51-2 ME 104 Operations Schedule 1-72-1 Relative Motion of CSM in LM Curvilinear System During

LM Active Rendezvous . . . . . . . . 2-63 - 1 Basic Entry Control Modes . . . . . . . . 3-783-2 SM Abort Philosophy 3-107

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TABLES.

Table Page

2-1 Mission D SPS Burn Summary 2-23-1 ME 104 - GNCS SPS Burn' 3-53-2 ME 104 - SCS ATVC Burn 3-193-3 ME 104 Rendezvous SPS CSI/CDH AV Procedures . . . 3-293-4 LM On SPS AV Run Schedule 3-443 - 5 L M O f f S P S A V R u n Schedule . . . . . . . . 3-463 - 6 M E 1 0 4 Post C D H t o Rendezvous Termination . . . . 3-513-7 LM Active Rendezvous Run Schedule . . . . . . 3 - 7 33-8 CSM Active Rendezvous Run Schedule 3-743-9 Display Panel Switch Position Prior to Entry Run . . . 3-80

3-9A ME 104 Automatic GNCS Entry 3-813-10 Entry Run Schedule 3-853-11 P51 IMU Orientation Procedures . 3-883-12 P52 IMU Realignment 3-893-13 P 5 2 Backup I M U Orientation Determination . . . . 3-923-14 P54 Backup IMU Realignment Program 3-933-15 Alignment Run Schedule 3-963-16 P21 Ground Track Determination 3-993-17 P22 Orbital Navigation 3-1003-18 Orbital Navigation Run Schedule 3-1033-19 Mode IV SPS Abort 3-1093-20 SM Abort Run Schedule Synopsis 3-1123-21 Hybrid RCS Deorbit 3-1143-22 RCS Deorbit Conditions and Rationale 3-1183-23 SM RCS Deorbit Run Schedule. . . . . . . . 3-1193-24 Hybrid RCS Deorbit Run Schedule Synopsis . . . .3 -1204-1 Analog Recording Requirements . . . . . . . 4 - 24-2 Environment Recording Requirements . . . . . 4-44-3 Downlink Data Requirements . . . . . . . . 4 - 1 1

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1.0 INTRODUCTION

1. 1 PURPOSE

The purpose of the Mission Evaluation 104 Simulation Study is to verifythat the spacecraft guidance, navigation, and control subsystems are capableof performing the planned mission phases under nominal and certain off-nominal conditions. Crew procedures for selected failure mode conditionswill be verified for Mission D. In addition, spacecraft guidance, navigation,and control subsystems performance characteristics will be evaluated forbackup and failure conditions. As a result, a data base will be generatedfor postflight analysis.

The purpose of this report is to define the studies to be accomplishedduring the ME 104 simulation. The flight phases and test objectives ofMission D are identified with simulation study phases. The objectives ofeach simulation study phase are presented as are the detailed run schedules.The performance results of the ME 101 study, Reference 1, stronglyinfluenced the distribution of emphasis on this study.

1.2 MISSION D G&C OBJECTIVES

The Mission D objectives (Reference 2), which are related to theguidance,navigation, and control functions are listed in succeedingparagraphs:

PI. 23 GSM Autopilot Stability Margin (Cannot be satisfied by ME 104)

a. Validate control system stability during short- and long-duration thrusting.

b. Provide a measure of structural dynamic response to aknown forcing function.

PL 24 CSM IMU Alignment Accuracy

a. Evaluate man-machine interfaces during the alignmentprocess.

b. Establish the uncertainties in the alignment process.

c. Evaluate the overall alignment accuracy in a dockedconfiguration

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PI. 25 IMU Orientation Determination (Cannot be satisfied in ME 104)

a. Determine if stair patterns are visible in daylight.

b. Obtain data for prediction of star visibility in the lunarlanding mission.

c. Determine if LM surface reflections or mass expulsion aredetrimental to the performance of the IMU orientationdetermination function or midcourse navigation sighting.

PI. 28 GNCS Automatic Entry

a. Verify ability of DAP to control an automatic entry and tomaintain attitude and attitude rates within requireddeadbands.

i

b. Evaluate GNCS accuracy in guiding the CM to a desiredtarget point •without exceeding the allowable g loads.

P20, 33 CSM Single Crewman Rendezvous Capability

a. Obtain data on the single crewman accomplishment ofprocedures and on the operational timeline used in pre-paring the CSM for an active rendezvous and update thesimulation if required.

b. Prepare the CSM for a LM rescue while the LM executesthe phases of the LM concentric flight plan (CFP)rendezvous.

SI. 26 Orbital Navigation/Landmark Tracking

a. Establish error uncertainties in the landmark navigationsightings.

b. Evaluate the procedural aspects of landmark tracking ina flight environment using the SCT.

1.3 SIMULATION CONFIGURATION

The simulation configuration consists of the'following six majorareas:

Analog computersPartial SCS hardware

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Partial GNCS hardwareCM evaluatorRTSS/interfaceVisual displays

A total simulation configuration flow diagram is shown in Figure 1-1.A detailed description of each area can be found in Part II of this Pre-simulation Report. This simulation configuration resembles that of ME 101;however, it has the additional capability of providing a visual cue for terminalrendezvous braking employing a LM model.

1. 4 SIMULATION SCHEDULE

The ME 104 simulation will be conducted in seven study phases des-cribed in detail in Section 3. 0. The preliminary schedule for conductingthese study phases is presented in Figure 1-2 and is based on an estimatedstart date of 2 September 1968. The schedule is for planning purposes only.Past experience has shown that a detailed schedule changes frequentlybecause of unpredictable situations and events.

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Page Intentionally Left Blank


SECTION II VEHICLE DYNAMICS ('ANALOG COMPUTATION)SECTION V SIMULATED SCS ELECTRONICS AND SPS GIMBAL DYNAMICS

PANEL SWITCH POSITIONSVARIABLE SCINERTIASSPS GIMBAL POSITION & ACCEL.

SPS THRUST ON SIGNALATVC G1MB.'CMOS ANGULARACCELERATIONSAND RATESMTVC GIMB. CMOS RCS ENGINE COMMANDS BODY RATES TO

GA2TRANSLATION FORCES

BODY BENDING

TAIL WAG DOG

DOG WAG TAIL

BODY ATT ERRORTO GATXg ACCELERATION

TRANSLATION CMOS

SPS THRUST ON-OFF SPS GIMBAL POSITION

RCS PROPELLANTACCOUNTING SPS AND RCS

THRUST SHAPINGORBITAL PITCH RATE

SECTION VI SCSPROTOTYPE HARDWARE

SECTION VIHCM EVALUATOP

SECTION III RTSS ANDASSOCIATED INTERFACEHARDWARE

EVLER ATT ERRORA/D AND

D/A

CONVERSION

(MODIFIEDFRONT END)

FDAI BALL ANGLE ERRORS IDSKY,

&WINDOW

DISPLAY

FDAI BALL ANGLES

OPTICS MODE CONTROL

SECTION VII SNCS PROTO-TYPE HARDWARE AERO FORCES

AND MOMENTSIMU COARSE ALIGN DRIVE

IMU GIMBAL ANGLES GIMBAL ANGLE I/F

IMU TORQUING I/FVISUAL DISPLAYDRIVE EQNS

SXT & SCTGIMBALDRIVESIMULATOR

IMU & OPTICSANGLE COMMANDS UPLINK/DOWNLINK

AND DOWN/LINK CONTROLIMU S OPTICS ANGLES

SIMULATED FIPA OUTPUTS

PROBLEMINITIALIZATION

GPVS DRIVE SIGNALS

SXT (AND SCT SHAFT AND TRUNNION ANGLES

X-Y COORDINATES FOR SXT IMAGE

DRIVE SIGNALS TO DISPLAY MECHANISMS DIGITAL SHAFT ENCODER'RETURNSSECTION IVEXTERNAL VISUALDISPLAY MECHANISMS

PANEL SWITCH POSITIONS

Figure 1-1. Simulation Configuration Flow Diagram

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2. 0 MISSION DESCRIPTION

2. 1 NOMINAL MISSION PHASES

The Apollo Mission D is divided into six major periods of activitieswhich are described in detail in Reference 3. The events in each of thesesix periods that will be simulated are discussed in some detail below. TheSPS burn schedule is summarized in Table 2-1. Contingency phases will bediscussed in the next section.

2. 1. 1 First Period of Activities

Prelaunch and launch phases are not simulated.

2.1.1.1 Earth Parking Orbit

Earth parking orbit includes the CSM transposition, docking, and with-drawal of the LM, which will not be evaluated.

2.1.1.2 First Docked SPS Burn

Upon entering darkness, the CSM IMU is realigned, and preparationis made for the first docked SPS ignition. The 63 fps GNCS controlled,external AV targeted burn raises the apogee to 140 nautical miles to ensurean adequate orbital lifetime. This burn also establishes a safe operatingdistance from the S-IVB. A partial demonstration of the CSM digital auto-matic pilot (DAP) attitude control capability is accomplished with this burn.

2 .1 .2 Second Period of Activities

2 . 1 . 2 . 1 Second Docked SPS Burn

This docked SPS burn is the first of two out-of-plane, long-durationburns. The resultant AV of 1200 fps reduces the orbital inclination androtates the line of nodes to the west. About 20, 600 pounds of propellant areconsumed during the 220 seconds of burn, reducing the CSM mass in order toincrease the effectiveness of the CM RCS to perform LM rescue. This burnalso partially demonstrates the CSM DAP attitude control capability duringthe one-half amplitude stroking test accomplished during the burn.

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2 .1 .2 .2 Third Docked SPS Burn

Approximately one revolution after the second SPS burn, a 1700 fpsGNCS controlled external AV burn is performed to cancel out the trajectoryeffects of tne second burn. About 12, 000 pounds of propellant are con-sumed during the 186 seconds of burn, further enhancing the CSM1 s capabilityfor LM rescue and SM RCS deorbit. A full-amplitude stroking test isaccomplished during this burn.

2 . 1 . 2 . 3 Fourth Docked SPS Burn

The final docked SPS burn circularizes the orbit at 134 nautical miles.This burn is also GNCS-controlled, and external V targeted to burn9 seconds, providing a 100-fps AV. The resultant circular orbit is the baseorbit from which the LM active rendezvous will be initiated in the fifth period.

2 .1 .3 Third Period of Activities

Not simulated.

2. 1. 3. 1 LM Power-Up and Systems Check

The two LM crew members transfer intravehicle to the LM, wherethey proceed to power up the LM and conduct systems check and evaluation.

2 . 1 . 3 . 2 Docked Descent Propulsion System (DPS) Burn

A 283-second DPS burn is accomplished to verify the GNCS DAPcapability to control rates and attitude during a thrusting maneuver in thedocked configuration and to demonstrate manual throttling of the DPS engine.

2.1.4 Fourth Period of Activities

Not simulated.

2. 1.4. 1 EVA

The primary event is the extra-vehicular transfer of a crew memberfrom the LM to the CSM.

2.1 .5 Fifth Period of Activities

Only CSM activities are simulated. The primary activities within thisperiod are the LM-active "double bubble" rendezvous and an unmanned, long-duration ascent propulsion system (APS) burn. The rendezvous profile begins

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with the LM burning radially up into a-small "football" from which the two

co-elliptic sequence initiation/constant delta height (CSI/CDH) sequencesare set up. The first sequence results in a terminal phase initiation (TPI)from above., •which is not performed, and the second results in a TPI frombelow, which is performed.

The CSM may be required to back up the LM on the above CSI/CDHburns and perform a LM rescue. This will be discussed later inSection 2.2.1.

2 .1 ,6 Sixth Period of Activities

In order to reduce the SM RCS propellant required to deorbit the CMinto the nominal recovery area, two orbit-shaping burns are introduced tolower the perigee and raise the apogee.

2. 1.6. 1 Fifth SPS Burn (Apogee Adjust)

The fifth SPS burn is a. posigrade, CSM-only burn.. The 132-fps,6-second, GNCS-controlled burn raises the apogee from 133 nautical milesto 207 nautical miles.

2. 1.6. 2 Sixth SPS Burn (Perigee Adjust)

The 93-fps, retrograde, GNCS-controlled burn lowers the perigee from131 to 95 nautical miles and adjusts the apogee to 210 nautical miles.

2. 1. 6. 3 Predeorbit Activities

The remainder of the sixth period before deorbit is devoted to accom-plishing navigational sighting objectives, gaining new experience with IMUalignments, and conducting experiments. Only a landmark tracking exercisewill be simulated.

2.1.6.4 Seventh SPS Burn (Deorbit)

The deorbit burn is performed over Hawaii with the CSM pitcheddown 47 degrees in a retrograde position. The external AV, GNCS-controlledburn lasts for 12 seconds to provide a 266 fps AV.

2 .1 .6 .5 Entry

During the 15 minutes of free fall between the deorbit burn and the400, 000-feet entry interface, the CM is separated from the SM and is

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maneuvered to the entry attitude. About 11 minutes later, the CM arrives atthe drogue deployment point, where the simulation is terminated. The GNCS-controiled CM will attain a maximum g peak of 3. 3 before achieving therequired target site.

2.2 MISSION CONTINGENCY PHASES

2. 2. 1 LM Rescue

During the fifth period of activities described above, the CSM must beprepared to back up the LM during the CSI/CDH sequences and perform asubsequent rendezvous. The relative motion of the CSM in the LM-centeredlocal vertical system is shown in Figure 2-1.

In backing up the CSI/CDH burns, the CSM will be targeted (externalAV) to burn 1 minute after the scheduled LM burn. The SPS burn will beopposite in direction to LM burn and about equal in magnitude.

The actual LM rescue could be initiated at three different positions inthe trajectory: TPIg, TPIj, or TPI^.. Prior to TPI, SXT marks will be takenof the LM to update the LM state vector in the GNCS. The TPI burns areSM RCS +X translations or SPS burns depending on the required burn duration.Subsequent to TPI, two midcourse burns maybe required, MCC1 and MCC2.Normally the LM will perform the braking maneuvers to conserve SM RCSpropellant. The CSM will perform the docking maneuver.

2. 2. 2 SM Abort

The SM boost abort phase covers the portion of launch from LESjettison to orbit insertion. Present philosophy for SM boost aborts includesthree abort modes. Mode II is in effect from LES jettison to approximately630 seconds GET and results in impact in the continuous recovery area(CRA). The Mode III abort region begins at Mode II termination and ends atinsertion. Depending on abort conditions, impact occurs in the discreterecovery area (DRA) 3350 nautical miles down-range of the pad or in theIndian Ocean recovery area (IORA). Throughout the Mode III region, capa-bility exists for contingency orbit insertion, which is Mode IV. Therefore,Mode III is least likely to be used, because contingency orbit insertion isprimary when possible. It should be noted that the ME 104 mechanizationdoes not include a simulation of the booster flight phase.

2 . 2 . 3 RCS Deorbit

An RCS deorbit capability should be provided from at least one pointin each orbit as a backup in the event of an SPS failure. The RCS deorbit

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maneuver is performed by applying the steady-state thrust generated by theRCS thrusters opposite to the inertial velocity vector, Vp at apogee so as

•to maximize the reduction in perigee altitude per pound of RCS propellantexpended. -

A four-quad SM RCS deorbit is considered to be the nominal backupdeorbit. However, in the event the mission is extended past the SM RCSfour-quad deorbit propellant redline, or a portion of the SM RCS four-quadcapability is lost, a hybrid RCS deorbit using both the SM RCS and CM RCScan be performed. A CM-RCS-only deorbit is not feasible for the "D" mis-sion because the delta V required is not available.

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3.0 STUDY DEFINITION

3. 1 STUDY PHASES

The mission evaluation study will be divided into the following phases:

SPS AVRendezvousEntryIMU/GDC alignmentLandmark trackingSM abortRCS deorbit

In addition, periods of time are allotted for MCC/ME 104 joint simulation andfinal software verification tests (FSVT). The S-IVB/CSM separation and thesubsequent transposition and docking will not be simulated. The study objec-tives and scope and a run schedule synopsis for each study phase are definedin the following paragraphs.

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\ '

3.2 SPS AV

3.2.1 Study Objectives

Study objectives are as follows:

1. Evaluate the A V performance, and dynamic characteristics of theCSM/LM-on for the following TVC modes:

CMCMTVC-acceleration

2. Determine the impact of the stroking test on the AV performance.

3. Verify the related CMC programs (P30, P40).

4. Evaluate the AV performance and dynamic characteristics for theCSM solo in the following TVC modes:

CMCAutomatic SCSMTVC-Rate

5. Evaluate the AV performance for the backup AV's during LMrescue.

6. Evaluate the related G&C procedures under nominal and failuretake-over conditions.

7. Determine the pointing accuracy capability of the previouslymentioned TVC modes with and without system errors.

8. Verify that attitude control is maintained or recovered duringan MTVC failure take-over.

9. Determine if a preventive deorbit potential exists for hard-overfailures.

10. Determine the SM RCS propellant required for orientationmaneuvers, propellant settling maneuvers, and damping the SPSshutdown transient.

11. Provide data base for postflight analysis.

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3.2 .2 Study Scope

The SPS AV study phase will be divided into two subphases: (1) LM-onSPS burns and (2) CSM-only SPS burns.

3 .2 .2 .1 LM-ON SPS Burns

In this subphase, the AV performance and dynamic characteristicswith the LM-on will be evaluated under nominal, system errors, and failuretake-over conditions. Burns 1 through 4 are included in this category. Thestroking test will be accomplished in Burns 2 and 3. All burns will be GNCS-controlled unless a failure is inserted at which time MTVC Accelerationcommand is initiated. The use of SCS automatic TVC does not seemwarranted with the LM-on and will not be studied.

3 . 2 . 2 . 2 CSM-Only SPS Burns

In this subphase, the AV performance and dynamic characteristics willbe evaluated under nominal, system error, and failure takeover conditions.Burns 5 through 7 are included in this category. These burns will be GNCS-controlled unless a failure is inserted, at which time the MTVC rate com-mand is initiated. In addition, the deorbit burn, Burn 7, will be evaluated inthe SCS automatic TVC mode. Of the scheduled SPS burns, the deorbit burnwill receive the most attention.

In addition, potential CSM-only SPS burns exist during the rendezvousphase. SPS burns may be required to back up the LM at CDHi, CSI.j, and/orCDH2 (Figure 2-1). At this time, only GNCS-controlled burns will be eval-uated, including the effects of system error. Furthermore, no backup topartial LM burns will be considered. The resultant rendezvous after CDHjand CDH2 will then be accomplished in real time. A detailed discussion ofrendezvous is covered in section 3. 3.

3 .2 .3 Run Description

Although in the actual mission each SPS burn is preceded by an IMUalignment, during this study phase all runs will be initiated with a prealignedIMU (ideal REFSMMAT). This reduces run duration; moreover, IMU align-ments are covered in another phase. Based on ME 101 experience, thealignments and subsequent SPS burns will be accomplished during MCC/ME 104 joint simulation and Final Software Verification Test (FSVT).

The detailed sequence of events is taken from the SC 103 AOH(Reference 4). The step-by-step test procedures for CMC and SCS ATVC,

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are presented in Tables 3 - l a n d 3-2, respectively. The test procedure forthe backup SPS burns is presented in Table 3-3. It includes both the nonburnoption and required LM update as well as the burn-required option.

3 .2 .4 Run Schedule Synopsis

The run schedule synopsis is divided into the two areas described underScope: LM-on SPS burns (Table 3-4) and CSM-bnly SPS burns (Table 3-5).The proposed runs include the various error sources and/or failures. Theerror sources being considered are thrust misalignment angle (« T)> center-of-gravity uncertainty ( e c. g. , ), and actuator torque load bias (T]_,). Acombined system error (RSS/3(r) value will be obtained using a\^5 <r value fromeach error source. The failure being considered is the SPS gimbal servo-amplifier hard over in either pitch or yaw. The run schedule synopsisincludes the initial conditions, run description, presence of failures, errorsources, and the estimated run lengths.

3-4

SD 68-723


Table 3-1. ME 104 - GNCS SPS Burn

Time Step Procedure

Panel 8

All Circuit Breakers IN

B/D Roll (4) OFF

A/C Roll (4) MNA

Pitch (4) MNAYaw (4) MNA

Panel 7

EDS Pwr ON

TVC Servo Pwr 1 AC1/MNATVC Servo Pwr 2 AC2/MNB

FDAI/GPI Pwr BOTH

LOGIC Pwr 2/3 ON

BMAG Power 1 8* 2 ON

SCS Electronics Pwr GDC/ECA

Panel 1

CMC Att IMU

FDAI Scale 5/1

FDAI Select 1/2

FDAI Source CMC

Att Set GDC

Man Att (3) RATE CMD

Limit Cycle OFF

Att Deadband MAX

Rate LOW

Trans Contr Pwr ON

Rot. Contr Pwr Norm (2) AC/DC

Rot. Contr Pwr Direct (2) OFF

SC Cont CMC

Results

3-5

SD 68-723


Table 3-1. ME 104 - GNCS SPS Burn (Cont)

Time Step ProcedureCMC Mode AUTO

BMAG Mode (3) . RATE 2

SPS Thrust Direct NORMAL!'

AV Thrust A&B OFF

SCS TVC (2) RATE CMD if LM- OFF,. ACCEL GMD if LM-ON

SPS Gmbl Motors (4) OFF

AVCG LM/CSM or CSM

IMU Cage OFF '.

' Entry EMS Roll OFF

*Entry . 05G OFF

LV/SPS Ind tt/Pc - Pc

LV/SPS Ind . SII/SIVB/GPI

TVC Gmbl Drive (2) AUTO

FCSM (2) RESET /OVERRIDE

Panel 2

Up TLM CM ACCEPT

Up TLM IU BLOCK

RCS CMD ON

RCS Trnpr . . gj^

Prim Prplnt (4) GRAY

CM/SM Sep (2) OFF (DN)

RHC (2) ARMED

THC ARMED

EMS Mode STBY

EMS Func AV SET

ORDEAL FDAI Orbit INRTRate/Inrt (2)

Results

3-6SD 68-723



Time Step Procedure Results

CMC-ON (required)ISS-ON, orientation known and alignedSCS-ON (required)Orbit change vehicle preparation (desired)

CMC ATT-IMU.05G SW-OFFTest C/W LampsEMS Mode - STBYEMS Func - AV SETSet AV IND toEMS Func - AV

. _ fps

RCS DAP - LOAD AND ACTIVATE (R03)

Key V48E (load DAP)

FL V04 N46 (DAP config)

Rl

R2 .

V24E, load desired dataPRO

FL V06 N47

CSM WT . Ibs

LM WT . I b s


3-7

SD 68-723




FL V06 N48

PITCH TRIM . deg

YAW TRIM . deg

V24E, load desired dataPRO (exit R03)

Key V46E (activate DAP)

EXT AV PRE-THRUST (P30)

Key V37E 30E

FL V06 N33

GETI, stored 00 . hrs

000 _ _ _ . min

0 _ _.._ _ sec


FL V06 N81 (AV LCL VRT components)

AVX .._ fps

AVY _ _ _ _._ fps

AVZ ._ fps


3-8

SD 68-723




FL V06 N42 (calculated thrust parameters)

HA . nm

HP . _ nm

AV (required) _ . _

PRO

FL V16 N45

Marks (VHF optics) _ _ B _ _

TF GETI (nextburn) B

MGA (next burn)

Set event timer to DSKY value

PRO (exit P30)

FL V37

ESTROKER LOAD (IF REQUIRED)

mm-sec

• deg

Key V06 N02EKey 03012ECheck Rl

Accept, PRO

Reject

Key V21 N01EKey 03012E

Key ££££_

PRO

3-9SD 68-723


Table 3-1. ME 104 - GNCS SPS Burn (Contl


PRESENT ORBITAL PARAMETERS-OPTIONAL

Key V82E (R30)

FL V04 N06

Option Code 0 0 0 0 2

CMC assumed option 0_ 0_ 0_ £ J^(1=CSM, 2=LM)

V22E, load desired data in R2PRO

FL V16 N44

HA

HP

nm

TFF - 1 1 B _5 £ min-sec

PRO (exit R30)

ALIGN GDC TO IMU

Key V16 N20EFL V16 N20 ''

R

P _•_ _ de§

Y . deg

ATT SET tw - Adjust to IMUGimbal angles on DSKY

ATT SET - GDCGDC align pb - Push, Hold

3-10SD 68-723




KEY RELFL V37

G&N THRUSTING (P40)

Key OOEKey V37E 40EKey V06 N81EFL V06 N81

VGX ._ fps

VGY ._ fps

VGZ ._ fps

KEY REL

FL V50 N18 (desired final gimbal angles)

R . deg

P . deg

Y . deg

Call for SM RCS fuel readout

CMC Mode - AutoFDAI/GPI PWR - BothLogic 2/3 PWR - ON (Up)CMC ATT-IMUFDAI SEL - 1/2SCS ELEC PWR - GDC/ECABMAG MODE (3) - Rate 2SC CONT - CMCMAN ATT (3) - Rate CMD

3-11

SD 68-723




AUTOMATIC MANEUVER TO THRUSTINGATTITUDE

PROFL V06 N18 (until'maneuver completed)Go to Step A

MANUAL MANEUVER TO THRUSTINGATTITUDE

Select desired attitude control modeENTRManeuver to thrusting attitude

FL V50 N18 (ATT trim.enable)

Final ATT trim maneuver performedafter gimbal drive and trim check

Call for SM RCS fuel readout

IGNITION PREPARATION

MN BUS TIE (2) - ON (Up)SPS He VLV tb (both) - bpSPS He VLV (both) - AutoRHC PWR Direct (both) - OffSC CONT - CMCCMC Mode-AutoSCS TVC (2) - Rate CMD or Accel CMDLV/SPS IND SII/SIVB - GPITVC GMBL Drive (2) - AutoFCSM SPS A - On (Up)

3-12

SD 68-723


Table 3-1. ME 104 . GNCS SPS Burn (Cont)


05:00 GIMBAL DRIVE AND TRIM CHECK

TVC Servo PWR 1 - AC 1/MNATVC Servo PWR 2 - AC2/MNBTRANS CONTR PWR - ON (Up)RHC PWR NORM 2 - ACRHC 2 - ARMED

IF Rate 1 AV plannedBMAG MODE PITCH - RATE 1BMAG MODE YAW - RATE 1

SPS GMBL MOT PITCH 1 - STARTSPS GMBL MOT YAW 1 - START

AUTO SWITCHOVER CHECK

THC - CWRHC - Verify no MTVC control

SECONDARY TVC CHECK


Confirm and set trim control

SPS GMBL tw (2) - + and -Set to CG trim values

PITCH

YAW

deg

deg

RHC 2 - Verify MTVCTHC - NeutralRHC PWR NORM 2 - AC/DC

3-13

SD 68-723




COMPLETE AUTO ATT TRIM

ACCEPT (maneuver)BMAG Mode (3) - RATE - 2Align SC in Roll (ACCEL CMD)SC Cont - CMCPRO

FL V06 N18 (until maneuvercompletion)

R . deg

P • deg

Y . deg

FL V50 N18

.. deg

.. deg

R

P

Y

REJECT (no maneuver)SC CONT - CMCENTR (exit R60)

RHC PWR Direct (both) - MNA/MNBMAN ATT (3) - RATE CMDRATE - HIGHBMAG MODE (3) - ATT 1 RATE 2Call for SM RCS fuel readout

3-14

SD 68-723




02:00

00:35

00:30

00:15

00:05

CMC GMBL DRIVE TEST

FL V50 N25Rl 00204

ACCEPT - PRO (trim at 16 sec)

REJECT - ENTR (trim at 4 sec)

V06 N40

TF GETI

VG

AV (ACCUM)

2 MIN COUNTDOWN,

mm-sec

_ fps

fps

Report TTI = 2 minFDAI SCALE - 5/5AV THRUST A - NORMALTHC - ARMEDRHC (both) - ARMED

DSKY clears

V06 N40(Avg G On)EMS MODE - AUTO

Perform ullage (if required)

FL V99 N40 (engine enable)

3-15

SD 68-723


Table 3-1. ME 104 - GNCS SPS Burn.(Cont)

Time

00:00

IGN+ 1SEC

Step Procedure

TF GETI _ _ B _ _ min-sec

VG B _'._ fps

AV (ACCUM) ._ fps

PRO (ENTR inhibits ENG IGN)

IGNITION

SPS THRUST It - ONV06 N40

TFC B min-— — ~~ ~ sec

VG (DECK)' • _ fps

AV ACCUM (INCR) . _ fps

AV IND - DECREASING

Monitor FDAI AND GPI

Discontinue ullage

INITIATE STROKER TEST (IF REQUIRED)

AT TFC = MIN SECKey V68E (initiates stroker test)

Auto termination of stroker test

ENGINE OFF AND SHUTDOWN

SPS THRUST It - Off

Results

3-16

SD 68-723




FL V16 N40 (Engine Cutoff)

TFC B mm- sec

VG _._ fps

AV (ACCUM) _._ fps

AV THRUST A - OFF

Report engine OFF

SPS ENG INJ VLV A IND (2) - CLOSE

SPS He VLV tb (both) - bp

SPS GMBL MOT PITCH 2 - OFFSPS GMBL MOT YAW 2 - OFFSPS GMBL MOT PITCH 1 - OFFSPS GMBL MOT YAW 1 - OFF

SCS TVC SERVO PWR 2 - OFFSCS TVC SERVO PWR 1 - OFFEMS MODE - STBY

Record AV IND __ _ __ _ ._ fps

PRO

FL V16 N85 (VG.vector components)

. VGX ._ fps

VGY ._ fps

VGZ ._ fps

Key V82E

3-17

SD 68-723




FL VI6 N44 (orbital parameters)

HA nm

HP nm

TFF B min-sec

PRO

FL V16 N85

VGX, Y, Z . fps

PROFL V37Key OOE

MN BUS TIE (2) - OFFEMS FUNG - OFFTRANS CONTR PWR - OFFFCSM SPS A - RESET/OVERRIDE

3-18SD 68-723


Table 3-2. ME 104 - SCS ATVC BURN

TIME STEP PROCEDURE RESULTS

CMC-ON (Req'd)ISS-ON, Orientation Known & Aligned

SCS-ON (Req'd)Orbit Change Vehicle Preparation (Desired)

CMC ATT-IMU. 05G SW-OFFTest C/W LampsEMS Mode - STBYEMS Func - AV SETSet AV IND to _.. _EMS Func - AVBMAG Mode (3) - ATT 1 RATE 2SC CONT-SCS, SCS TVC (2) - AUTOATT DB - MAX., LIMIT CYCLE - ON

EXT AV PRE-THRUST (P30)

MIN__SECFR INIT TOIGN

MIN SECBURN DUR.

Key V37E 30E

FL V06 N33

GETI, Stored + 00 . HRS

+ °°° __• MIN

+ 0 _ _ . _ _ SEC

V25E, Load Desired DataPRO

FL V06 N81 (AV LCL VRT Components)

AVX . FPS

AVY

AVZ

FPS

FPS

3-19SD 68-723


Table 3-2. ME 104 - SCS ATVC BURN (Cont)


V25E, Load Desired DataPRO

FL V06 N42 (Calc'd Thrust Parameters)

HA . _ N M

HP . _ N M

AV (Req'd) ._FPS

PRO

FL V16 N45

Marks (VHF Optics) B

TF GETI (Next Burn) B MIN-SEC

MGA (Next Burn) . DEC

Set Event Timer to DSKY Value

PRO (Exit P30)

FL V37

PRESENT ORBITALPARAMETERS-OPTIONAL

Key V82E (R30)

FL V04 N06

Option Code 0 0 0 0 2

3-20

SD 68-723




CMC As sumed Option 0^ £ 0 0 l_(1=CSM, 2 = LM)

V22E, Load Desired Data in R2PRO

FL VI6 N44

HA

HP

TFF

AT INIT

B MIN-SEC

PRO (Exit R30)

ALIGN GDC TO IMU

Key V16 N20EFL V16 N20

R .

P

DEG

DEG

DEG

ATT SET tw - Adjust to IMUGimbal Angles on DSKY

ATT SET - GDCGDC Align pb - Push, Hold

KEY RELFL V37

3-21SD 68-723




GfcN THRUSTING (P40)

Key OOEKey V37E 40EKey V06 N81EFL V06 N81

VGX _.

VGY .

VGZ .

KEY REL

FPS

FPS

FPS

FL V50 N18 (Desired Final Gimbal Angles)

R . DEG

P . DEG

Y . DEG

Call for SM RCS Fuel Readout

CMC Mode - AUTOFDAI/GPI PWR - BOTHLogic 2/3 PWR - ON (Up)CMC ATT-IMUFDAI SEL - 1/2SCS ELEC PWR - GDC/ECASC CONT - SCS

MANUAL MANEUVER TO THRUSTINGATTITUDE

BMAG Mode (3) - RATE 2, MAN ATT(3)ACCEL CMD, LIMIT CYCLE-OFFPROManeuver to Thrusting Attitude

FL V50 N18 (ATT Trim Enable)

3-22SD 68-723



TIME

05:00

STEP PROCEDURE

Final ATT Trim Maneuver PerformedAfter Gimbal Drive & Trim Check

Call for SM RCS Fuel ReadoutBMAG Mode (3) - ATT 1, RATE 2MAN ATT (3) - RATE CMD, LIMIT

CYCLE-ON

IGNITION PREPARATION

MN BUS TIE (2) - ON (Up)SPS He VLV tb (Both) - bpSPS He VLV (Both) - AUTORHC PWR Direct (Both) - CHSC CONT - SCSCMC Mode- AUTOSCS TVC (2) - AUTOLV/SPS IND SII/SIVB - GPITVC GMBL Drive (2) - AUTOFCSM SPS (2) - ON (UP)

GIMBAL DRIVE AND TRIM CHECK

TVC Servo PWR 1 - ACI/MNATVC Servo PWR 2 - AC2/MNBTRANS CONTR PWR - ON (Up)RHC PWR NORM 2 - ACRHC 2 - ARMED

IF Rate 1 AV PlannedBMAG MODE PITCH - RATE 1BMAG MODE YAW - RATE 1


AUTO SWITCHOVER CHECK

THC - CWRHC - Verify no MTVC Control

RESULTS

3-23

SD 68-723



TIME STEP PROCEDURE

SECONDARY TVC CHECK


Confirm & Set Trim Control

SPS GMBL tw (2) - + and -Set to CG Trim Values

PITCH - _. DEC

YAW - _ - _ _ D E G

RHC 2 - Verify MTVCTHC - NeutralRHC PWR NORM 2 - AC /DC

COMPLETE ATT TRIM

LIMIT CYCLE-OFFB.MAG Mode "(3) - RATE 2, MAN ATT (3) -

MIN IMPRHC 2 — NULL ATT ERRORSATT DB-MINENTR i

RHC PWR Direct (Both) - MNA/MNBMAN ATT (3) - RATE CMD, LIMIT

CYCLE-ONRATE - LOBMAG MODE (3) - ATT 1 RATE 2Call for SM RCS Fuel Readout

CMC GMBL DRIVE TEST

FL V50 N25Rl 00204

ACCEPT - PRO (Trim at 16 SEC)

RESULTS

3-24SD 68-723




02:00

00:35

00:30

00:05

00:00

REJECT - ENTR (Trim at 4 SEC)

V06 N40

TF GETI

VG

MIN-SEC

+ ._ FPS

AV (ACCUM) + 0^ 0_ 0^ 0. 0_ FPS

2 MIN COUNTDOWN

Report TTI = 2 MinFDAI SCALE - 5/5AV THRUST (2) - NORMALTHC - ARMEDRHC (Both) - ARMEDLIMIT CYCLE - OFF

DSKY Clears

V06 N40(Avg. G On)EMS MODE - AUTO

Perform Ullage

FL V99 N40 (Engine Enable)

TF GETI B MIN-SEC

VG FPS

AV (ACCUM) . _ FPS

PRO (ENTR Inhibits ENG IGN)

IGNITION

THRUST ON pb PUSHSPS THRUST It - ON

3-25SD 68-723



TIME

IGN+1SEC

STEP PROCEDURE

V06 N40RATE - HIGH

TFC _ _ B MIN-SEG

VG (DECR) -_FPS

AV ACCUM (INCR) . _ FPS

AV IND - DECREASINGMonitor FDAI & GPI

Discontinue Ullage

ENGINE OFF & SHUTDOWN

SPS THRUST It - Off

FL VI 6 N40 (Engine Cutoff)

TFC B MIN-SEC

VG + Q O Q Q . Q F P S

AV (ACCUM) j ._FPS

AV THRUST (2) - OFF

Report Engine OFF

SPS ENG INJ VLV A IND (2) - CLOSE

SPS He VLV tb (Both) - bp

SPS GMBL MOT PITCH 2 - OFFSPS GMBL MOT YAW 2 - OFFSPS GMBL MOT PITCH 1 - OFFSPS GMBL MOT YAW 1 - OFF

RESULTS

3-26SD 68-723


TABLE 3-2. ME 104 - SCS ATVC BURN (Cont)

TIME STEP PROCEDURE

SCS TVC SERVO PWR 2 - OFFSCS TVC SERVO PWR 1 - OFFEMS MODE - STBY

Record AV IND . _ FPS

PRO

FL V16 N85 (VG Vector Components)

VGX . _ FPS

VGY ._ FPS

VGZ ._FPS

Key V82E

FL V16 N44 (Orbital Parameters)

HA ._._ NM

HP -. _ NM

TFF B MIN-SEC

PRO

FL V16 N85VGX, Y, Z . _ FPS

PROFL V37

FCSM SPS (2) - RESET /OVERRIDE

KEY 61E

GO TO G&N CM/SM SEPARATION

RESULTS

3-27SD 68-723




ENTRY PARAMETERS (IF RUN ENDS AT ,CM/SM SEPARATION)

FL V06 N6l

IMPACT LAT (+NORTH)IMPACT LONG (+EAST)HDS UP/DN (+UP)

V25E, LOAD DESIRED DATAPRO

DECDEC

FL V06 N60 (ENTRY DATA)

GMAX _ _ _.

V PRED _ _ _ ' _GAMMA El .

PRO

FL V06N63

RTOGO (. 05G TOSPLASH)

VIO (AT . 05G)TFE (TIME FROM

ENTRY)

G. FPS

DEC

B

NM' FPS

MIN-SEC

PRO (EXIT P61)

TERMINATE RUN

3-28

SD 68-723


Table 3-3. ME 104 Rendezvous SPS CSI/CDH AV Proceduresa. CSM Backup AV with LM Ignition and Burn

b. CSM Backup AV with No LM Lignition - CSM Performs SPS AV

GETTF

TIG PROCEDURE

Initial Switch Positions

Panel 8All Circuit BreakersB/D Roll Jets (4)A/C Roll Jets (4)Pitch Jets (4)Yaw Jets (4)

Panel 7EDS PwrTVC Servo Pwr 1TVC Servo Pwr 2FDAI/GPI PwrLogic Pwr 2/3BMAG Pwr (both)SCS Elec Pwr

Panel 2UPTLM CMUPTLM IURCS CMDRCS TransferPRIM PRPLNT (4)

Panel 1CMC AttFDAI ScaleFDAI SelectFDAI SourceAtt SetMan Att (3)Limit CycleAtt DBRate

INOFFMNAMNAMNA

ONAC I/MNAAC2/MNBBothON (up)ONGDC/ECA

AcceptBlockONSMGray

IMU5/11/2CMCGDCRate CMDOFFMaxLow

3-29

SD 68-723


Table 3-3. ME 104 Rendezvous SPS CSI/CDH AV Procedures (Cont)

GETTFTIG PROCEDURE

Panel 1Trans Contr PwrRHC Pwr - Norm (2)RHC Pwr - Direct (2)SC ControlCMC ModeBMAG Mode (3)SPS Thrust DirectAV Thrust A & BSCS TVC (2)SPS Gimbal Motrs (4)AV CGIMU CageEntry EMS RollEntry . 05GLV/SPS IND - cc/PcLV/SPS IN DSB/SIVB/GPITVC GMBL Drive (2)FCSM (2)CM/SM Sep (2)

Preliminary EMS SetEMS ModeEMS FuncSet AV Ind toEMS Func

Set ET to

Initial Attitude of CSM

Heads UP/DOWNNose (DOWN/UP) Range

Key V37E OOE

*Key V48EF V04 N46

Key V24E to Load

ONAC/DCOFFCMCAutoRate 2NormalOFFRate CMDOFFCSMOFFOFF :OFFPCGPIAutoRe set/Over rideOFF

STBYAV Set

• _ fpsAV

POO

(Load DAP)1110311111

3-30

SD 68-723



GETTFTIG PROCEDURE

PROF V06 N47

Key V24E to Load

PROF V06 N48

Key V24E to LoadPRO

Key V46E

Key V37E 30E

F V06 N33 (CSM TIG)Key V25E

Load

PROF V06 N81 (AVLV)

Key V25ELoad

PROF V06 N42 (HA, HP, AVCDH)

DSKY

Copy Values

PROF VI6 N45 (N, TFI, MGA)

Set ET to R2

+ '_ Ibs+ 0 0 0 0 0 I b s

degdeg

(activate DAP)

P30

+ 0 0 0+ 0 0 0 "+0

fpsfpsfps

n. min, mifps

(count down)

3-31SD 68-723



GETTFTIG PROCEDURE

PROF V37

Key OOE

CB EMS (2)EMS ModeEMS Func.EMS ModeLoad AVEMS Func

Monitor SPS It.Monitor AVMonitor SPS It.

Confirm AVEMS ModeEMS FuncLoad AVEMS Func '

Key V82EF V04 N06 (code, option)

00002OOOOx

(1 = CSM, 2 = LM)Accept or Load

PROF V16 N44 (HA, HP, TFF)

POO

- Closed- STBY- AV Set- Auto= 1586.8 fps- AV Test- ONCountdown- OFF= -20 .8 ± 20 .7- STBY- AV Set

- AV

(ORB. PARAM. )

00001

DSKYn. min. mim/s

PRO

Align GDC to IMUKey V16 N20 E

F V16 N20 (R, P, Y)

3-32SD 68-723


table 3-3. ME 104 Rendezvous SPS CSI/CDH AV Procedures (Cont)

GETTFTIG PROCEDURE

Att. Set TWAtt. SetGDC Align PB

Key RLSE

Key V37E 40E

F V50 N18 (R, P, Y)

Key V06 N81EF V06 N81 (AVLV at TIG)

Copy Values

Key RLSEF V50 N18 (R, P, Y)

Call for RCS Fuel Printout I

CMC ModeSC ControlCMC AttBMAG Mode (3)Man Att. (3)FDAI SelectFDAI/GPI PwrLogic 2/3 PwrSCS Elec Pwr

a. Automatic Maneuver

F V50 N18 (R, P, Y)

PROF V06 N18 (R, P, Y)F V50 N18 (R, P, Y)

- Rl, R2, R3- GDC- Press/Hold

P40

DSKY._ fps. __ fps._ fps

- Auto- CMC- IMU- Rate 2- Rate CMD- 1/2- Both- ON (up)- GDC/EGA

3-33SD 68-723



GETTFTIG PROCEDURE

PROF V06 N18F V50 N18

b. Manual Maneuver

F V50 N18 (R, P, Y)

SC ControlMan. Att.PRORHCMan Att.

c. Trim Maneuver

F V50 N18 (R, P, Y)

SC ControlCMC ModePRO

F V06 N18F V50 N18

Final Trim After Tests

Call for Fuel Printout^

Ignition Preparation

MN Bus Tie (2)SPS He VLV tb (Both)SPS He VLV (Both)RHC Pwr Direct (Both)SC ControlCMC ModeSCS TVC (2)LV/SPS IND SII/SIVB

(to trim)

SCSAccel. CMD

maneuver to Att.Rate CMD

CMCAuto

- ON (up)- Bp- Auto- OFF- CMC- Auto- Rate CMD- GP1

3-34

SD 68-723



GETTFTIG PROCEDURE

04:00

TVC GMBL Drive (2)FCSM SPS A

Gimbal Drive and Trim Check

TVC Servo P'wr 1TVC Servo Pwr 2Trans. Contr. PwrRHC Pwr Normal (2)RHC (2)

If Rate 1 AV PlannedBMAG Mode (P, Y)

SPS GMBL Motr ( P I )SPS GMBL Motr ( Y l )

Auto Switchover Check

THCRHC

Monitor SPS GMBL, Display

F V50 N18 (R, P, Y)

Secondary TVC Check

SPS GMBL Motr (P2)SPS GMBL Motr (Y2)

Confirm and Set Trim ControlSPS GMBL TW (2) (+ and -)

PitchYaw

RHC (2)THCRHC Pwr. Normal (2)

AutoON (up)

AC1/MNAAC2/MNBON (up)ACArmed

- Rate 1

- Start- Start

- CW- Verify No MTVC CONTR

StartStart

. deg

. degVerify MTVCNeutralAC/DC

3-35SD 68-723



GETTFTIG PROCEDURE

Final Maneuver TrimBMAG Mode (3)Align SC in Roll

SC ControlMan. Att. (R)

RHCMan. Att. (3)SC ControlCMC Mode

PROF V06 N18F V50 N18

Key ENTR

RHC Pwr Direct (Both)Man. Att. (3)RateBMAG Mode (3)Attitude DBEnable B/D Roll Jets

F V50 N25Rl 00204

Call for Fuel Printout^

Realign GDC to IMU

Key V16 N20EF V16 N20

Att. Set TWAtt. SetGDC Align PB

Key RLSE

F V50 N25

- Rate 2(0 or 180)- SCS- Accel CMD- maneuver- Rate CMD- CMC- Auto

(accept)

- MNA/MNB- Rate CMD- High- Att. I/Rate 2- Min- MNA

(Ignore)

(R,P,Y)

- Rl, R2, R3- GDC- Press/Hold

(00204)

3-36SD 68-723



TFGET TIG

01:00

00:00

00:05

00:10

00:15

00:20

PROCEDURE

Gimbal Drive Test (CMC)

To Monitor DriveKey PRO

GMBL's trim in 16 sec

To Bypass Test SequenceKey ENTR, thenPRO

GMBL's trim in 4 sec

F V06 N40 (TFI, VG, AVacc)

DSKY

Report: 1 min to LM IGN.

FDAI ScaleVerify SPS Thrust ItAV Thrust A

LM IgnitionSet ET Counting UP

LM Ignition Confirmed

If NO LM IGNITIONGO TO PAGE

LM Thrusting ConfirmedMonitor LM Burn

Key V34E

F V37

Key OOE

B m/sfpsfps

- 5/5- OFF- Normal

(Exit P40)

POO

3-37SD 68-723



GETTFTIG

00:40

PROCEDURE

AV Thrust A - OFFSPS GMBL Motr P, Y2 - OFFSPS GMBL Motr P, Yl - OFFSPS Eng. Inj VLV A Ind - CloseSPS He VLV tb (Both) - BpSPS TVC Servo Pwr 2 - OFFSPS TVC Servo Pwr 1 - OFFRHC Pwr Direct (Both) - OFFFCSM SPSA (Both) - Reset/OVRD

LM Burn Completed

EMS Func - OFFEMS Mode - STBYMN Bus Tie (Both) - OFFTHC Pwr - OFF

Key V82ELoad LM CodePRO

F V06 N44 (Hp, Ha, TFF)PRO

Receive LM AV's and TIG

Key V37E 76E P76

F V06 N84 (LM AVX y z )Key V25E - • 1 f V

Load - . fpsfps

PROF V06 N33 (LM TIG)

Key V25E +0 0 __ hrLoad + 0 0 0 min

+0 . sec

3-38

SD 68-723



TFGET TIG

Step A

PROCEDURE

PROF V37

Key OOEKey V82E

Load LM code

PROF V06 N44 (Hp, Ha, TFF)

PRO

a. If TPI to be completed

Key V37E 20E

Continue: Use RendezvousProcedures

b. If TPI Computations Only

Key V37E 34E

F V06 N37 (TIG TPI)Key V25E

Load

PROF V06 N55

Key V22ELoad E

Key V23 ELoad <r

PROF VI 6 N45 (N, TFI, MGA)

POO

P20

P34

+ 0 0 hr+ 000 min+0 . sec

( - , E , <r )

- . deg

= . deg

3-39SD 68-723



GETTFTIG PROCEDURE

DO NOT PROCEED

Key V32E (Recycle)

F V06 N37 (TIG/TPI)+ 00 hr

(DSKY) + 0 0 0 _ _ m i n+0 . sec

Copy Values

PROF V06 N58 (Hp, AVTpI, AVTpF)

._ n. miDSKY - _ f p s

- _ f p s

Copy Values

PROF V06 N59 (AV^QS comp. )

fpsDSKY ._ fps

._ fps

Copy Values

PROF V 1 6 N 4 5 (N, TFI, MGA);

Key V34E (terminate prog. )

F V37

Key OOE PQO

TERMINATE RUN

3-40SD 68-723



GETTFTIG

0020

00:25

00:30

00:35

00:45

00:55

01:00

PROCEDURE

GSM Performs SPS AV

F V06 N40 (TFI, VQ, AVacc)

B m/sDSKY ._ fps

. _ f p s

If PROG Alarm TIG slippedDSKY Returns atnew TIG - 35 sec

DSKY Blanks

THC - ArmedRHC - Armed

V06 N40 (Ave G ON)

EMS Mode - AutoCheck AVacc for PIPA Bias

R3 < 001. 0 fps

Perform Ullage+X Translation - THC

F V99 N40 (Engin enable)B m/s

DSKY ir__~_7 fPs

_._ fps

PRO (to request ignition)(ENTR to inhibit)GSM IgnitionSPS Thrust It. - ON

V06 N40 (TFC, VG, AVacc)TFC (Time from C/O - )

3-41SD 68-723



GETTFTIG

01:01

C/0 +00:01

PROCEDURE

Discontinue Ullage

Monitor BurnEMS AV Ind. - decreaseN40: VG and TFCSPS PC Ind.

SPS Engine CutoffSPS Thrust It. - OFF

F V 1 6 N 4 0 (Eng C/O)TFC (time from C/O + )

AV Thrust A - OFF

Report: Engine Off

SPS ENG. INJ. VLV A IND (2) - CloseSPS He VLV tb (Both) - Bp

SPS GMBL MOTR P, Y-2 - OFFSPS GMBL MOTR P, Y-l - OFF

SCS TVC SERVO Pwr 2 - OFFSCS TVC SERVO Pwr 1 - OFF

EMS Mode - STBYRecord AV Ind.

PROF V16 N85 (VG Body)

Null VQ (x, y, z) if necessary

THC _ Locked

Key V82E (ORB Param. )F V16 N44 (HA, Hp, TFF)

3-42SD 68-723



GETTFTIG PROCEDURE

PROF VI6 N85 (VG-Body)

PRO

F V37

MN Bus Tie (2)EMS Func.Trans Contr. PwrFCSM SPS A

Return to Step A

(exit P40)

- OFF- OFF- OFF- RESET/OVRD

3-43SD 68-723

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3-47

SD 68-723


3. 3 RENDEZVOUS .

3.3.1 Study Objectives •

Although the SC 104 mission plan does not include an actual inflightconfirmation of CSM-active rendezvous capability by a single crew member,in the event LM-active rendezvous is not completed, the capability for aCSM rescue of the LM is mandatory. This capability, then, must be demon-strated through simulation. The objectives for this simulation study are:

1. Verify the software (COLOSSUS) rendezvous programs: POO,P17, P20, P34, P35, P40, P41, P47, and P76.

2. Verify the adequacy of G&C procedures for both passive andactive rendezvous.

3. Develop alternate procedures as required.

4. Evaluate the effects of trajectory deviations.

5. Evaluate the effect of navigation on MSFN errors.

6. Evaluate the effects of system error sources.

7. Determine the effect of a GNCS failure on the capability tocomplete a rendezvous.

8. Determine the effect of RCS jet or quad failure on the capabilityto complete a rendezvous. , :; '

9. Establish SM RCS propellant values for both active and passiverendezvous.

10. Provide a data base for postflight analysis.

3. 3. 2 Study Scope

The rendezvous study phase will be divided into three areas of investi-gation: CSM-passive rendezvous performance, CSM-active rendezvousperformance, and failure effects on rendezvous success and performance.

3-48

SD 68-723


3.3.2.1 CSM-Passive Rendezvous

The CSM-passive rendezvous study will evaluate the nominal opera-tions and procedures onboard the CSM while the LM-active rendezvous, is inprogress. Nominal operation will include:

1. Acquiring the necessary observation data

2. Accepting and incorporating uplinked and voice-linked data

3. Monitoring LM actions and status both visually and in the CSMcomputer

4. Performing backup computations

5. Performing the required procedures for A V preparations andcount downs.

In addition, backup charts for L/M-active operations will be utilized, ifavailable, where CSM activities must respond to voice-link from the LM.

3.3.2.2 CSM-Active Rendezvous

The CSM-active rendezvous study will evaluate the rendezvous per-formance under both nominal and off-nominal conditions for each of the sevenevent times (except CSIi, which is nominally zero) at which CSM-activerendezvous may be initiated. This will include external AV activities andon-board computed A V operations, both with and without error sources.

3 .3 .2 .3 Failure Effects on Rendezvous Success and Performance

This portion of the study will evaluate both the dynamics and operationaleffects resulting from various failures during the CSM-active rendezvous.The ability of a single crew member to detect a failure and make a successfulrendezvous will be evaluated. Failure conditions may include CMC, IMU,or optics failure and RCS jet or quad failure. Suggestions for modificationsto the procedures will be made and/or evaluated.

3. 3. 3 Run Description

The majority of the runs will begin immediately following the scheduledLM burn. Normally the CMC will be initiated with a different state vectorthan is the RTSS in order to simulate MSFN errors. Each run requires theuse of the external visual displays, normally the SXT and always the dockingwindow. During prebraking, the docking window scene will just contain amoving, blinking light representative of the LM beacon. At braking distances,

3-49SD 68-723


the scene will change to a view of an LM model using the GPVS. The testprocedures were derived from the Mission D Rendezvous proceduresDocument (Reference 5 ) and the CSM 103 AOH, but they include certainsimulation-determined and data requirement procedure's. The detailed testprocedures are listed in Table 3-6. i

3.3.4 Run Schedule Synopsis

The rendezvous study includes both LM-active and CSM-active rendez-vous. Run schedule synopses for both are presented in Tables 3-7 and 3-8.

3-50SD 68-723


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3-52SD 68-723


Table 3-6. ME 104 Post CDH to Rendezvous Termination (Cont)

GETTFTPI Procedure

CDH Burn Completed

Switch Settings

FDAI/GPI Pwr . - BothSCS Elec Pwr . GDC/ECATrans Cont Pwr - ONRot Cont Pwr Direct (Both) - OFFAuto RCS Sel (B /D Roll-4) - OFF

FDAI ScaleRateAtt DB

- 5/1- Low- Max

FDAI SelectCMC AttEMS ModeEMS FuncBMAG Mode (3)Man Att (3)Optics ModeOptics ZeroOptics Drive

BothIMUSTBYOFFRate 2Rate CMDManZeroRSLV

Optics in Telescope Mode(Blinking Target)

*Zero in the SXT - adjustRemove Zero in SXTOptics Zero - OFF

SC Control - CMCCMC Mode - Free

Countdown to Operate

Operate (- ) ET

3-53SD 68-723


Table 3-6.. ME 104 Post CDH to Rendezvous Termination (Cont)

GETTFTPI Procedure

Key V37E OOE

Key V48E (Load DAP)F V04 N46 (11102) .

(11111)

PROF V06 N47 (+ )

( + 0 0 0 0 0 )

PROF.V06 N48 ( + 0 0 _ . _ )

( + 0 0 '._)

PRO

Key V46E (Activate DAP)

Mnvr to Zero R, Y on FDAI 1

GDC Align

Key V06 N20 ESet Att Set TW (O, P, O)

GDC Align PB - Press

ORDEAL Set

Key V82 EF V06 N44 (Hp, Ha, TFF)

Ave Rl & R2Set Alt on Dial

PROKey V83E

F V16 N54 (R, R, 6 )Slew FDAI to 9

PRO

POO

3-54

SD 68-723


Table 3-6. ME104 Post CDH to Rendezvous Termination (Cont)

GETTFTPI Procedure

Call for Fuel Printout Q)

Key V37 E 20E

F V50 N18 (please mnvr)(R, P, Y)

a. Auto ManeuverSC Control - CMCCMC Mode - Auto

PROV06 N18 (R, P, Y)

Monitor on FDAIF V50 N18

b. Manual ManeuverSC Control - SCSCMC Mode - AutoMan Att - Accel CMD

PRORHC maneuver

F V50 N18Man Att - Rate CMD

c. Trim ManeuverF V50 N18

SC Control - CMCCMC Mode - Auto

PROV06N18

Monitor on FDAIFV50 N18

Key ENTR (when satisfied)RHC - LockedCall for Fuel Printout ©Enable Roll Jets B/DMove to LEB

Optics Zero - OFFOptics Zero - Zero (15 sec)

POO

P20

3-55SD 68-723



GETTFTPI Procedure

Key V37E 34E

F V50 N18

Key ENTR

F V06 N37 (TIG/TPI)

Key V25E

Load

PRO

+00 _+000"+0

Optics Zero - OFF

Optics Mode - CMC

F V06 N55 (-, E, cr )

To Compute EKey V22E

LLoad (+OOOOOE)J

To Load EKeyV22ELoad (+207. 45E)

To Load <rKey V23ELoad (+XXX. XXE)

PRO

F V16 N45 (N, TFI, MGA

DO NOT PROCEED

Key V32E (Recycle)

F V06 N55 (-, E, <r )or

F V06 N37 (TIG/TPI).

Copy E or TIG

P34

3-56SD 68-723



GETTFTPI Procedure

PRO

F V06 N58 (H

Copy AV's

*EMS Func -AV SetSet AV Indicator to R2EMS Func -AV

PRO

F V06 N59 (AV

Copy Data

comp)

PRO

F V16 N45 (N, TFI, MGA)

Set ET - countdown

Compare Solutions

*Key V06 N52E

F V06 N52 ( tr CSM)

Key RLSE


KeyV57E

F V51 (please mark)

Optics Mode - Man

Make Marks (one/min)

F V06 N49 (AR, AV, +1)

Accept : PROReject : Key V32E

P34

3-57

SD 68-723



GETTFTPI Procedure

Optics Mode - CMC

PRO (process last mark)

F V16 N45 (N, TFI, -1)

Key V93E (reinitialize)

*Key V85E (if time)

F V06 N53 (R, R, 4> )Copy (R, $ )

PRO

Key V57E

F V51 please mark

Make marks (one/min)

. F V06'N49 (AR, AV, +1)


["Alternate W/V85E if time]L Record Data - PRO J


F V16 N45 (N, TEI, MGA)

Optics Mode - ManOptics Zero - Zero

Move to Couch

Receive TIG from LM


P34

3-58SD 68-723



GET.TFTPI Procedure

PRO (final recycle)

F V06 N55 (-, E, <r )or

F V06 N37 (TIG/TPI)

Record E or TIG

PRO

F V06 N58 (Hp,

Record AV's

*EMS Func - AV SetSet AV Indicator to R2EMS Func - AV

PRO

F V06 N81 (V LV)CJT

Copy AV components

PRO

F V06 N59 (V LOS)

Copy VGLOS

PRO


Reset ET

Call for Fuel Printout ®

Key V77E (+X axis track)

P34

3-59SD 68-723



GETTFTPI Procedure

09:00

08:30

Optics in Window Mode(blinking Tgt)Docking Position

F V50 N18 (please mnvr)

PRO (accept mnvr)

V06 N18

Monitor Mnvr. to COAS Track

F V50 N18 (please trim)

Key ENTR (accept trim)


PRO (exit P34)

F V37

Key 41E


Backup Data Procedure

Att DB - MinRate - LowSC Control - SCSBMAG Mode (3) - Att I/Rate 2Man Att (F, Y) - Min ImpRHC - ArmedDisable Roll Jets B/D

Bo re sight on LM (COAS)

Key V83E

F V06 N54 (R. R. 6 )

Maintain Boresight (COAS)

P34

P41

3-60SD 68-723



GETTFTPI Procedure

08:00

06:00

05:00

Key NOUN (freeze display)

Copy R, R, 6

Key 20E

F V06 N20 (R, P, Y)Att Set tw-Rl, R2, R3Align GDC to IMU

GDC Align PB - PressKey RLSE

F V06 N54 (R, R, 6 )

Boresight on LM (COAS)

Verify ORDEAL, (6)

Maintain Boresight (COAS)


Copy R, R, 6

Key RLSE

PRO


Call for Fuel Printout (3)

Auto ManeuverBMAG Mode (3) - Rate 2Man.Att(P.Y) - Rate CMDEnable Roll Jets - B/D (4)SC Control - CMCCMC Mode - Auto

P41

3-61SD 68-723



GETTFTPI Procedure

04:00

01:20

01:00

00:40

00:35

00:30

PRO

V06 N18

Monitor Mnvr to TPI Thrust Att

F V50 N18

PRO (last trim)

V06 N18F V50 N18

Key ENTR (accept trim)

F V06 N85 (V Body)Cj

Calculate BackupsCompare Solutions

EMS ModeEMS FuncLoad AV TPIEMS FuncEMS ModeLim Cycle

- STBY- AV Set

- AV- Auto.- OFF

BMAG Mode (3) - Att I/Rate 2

If PROG Alarm

TIG slippedDSKY clears atnew TIG - 35 secCOMP ACTY lightoff (exit R41)

DSKY Blanks

THC - ArmedRHC - Armed

V16 N85 (V_ Body)Lr

P41

3-62SD 68-723



GETTFTPI Procedure

00:15

00:00

01:00

Call for Fuel Printout

F V16 N85 (VG Body)Null VQ'S w/THCStart ET countup

¥„ Zero

PRO (exit P41)

THGAtt DBEMS Mode,EMS Func

- Locked- Max- STBY- OFF

BMAG Mode (3) - Rate 2

Call for Fuel Printout ©

F V37

Key 35E

F V50 N18 (auto mnvr)

PRO

V06 N18 (mnvr)

Monitor mnvr to COAS

F V50 N18 (please trim)

PRO (for trim)

Key ENTR (to accept)

Call for Fuel-Printout @


P41

P35

3-63

SD 68-723



GETTFTPI Procedure

03:00

06:30

07:00

Key V54E

F V06 N94 (S, T, -)

P35

Key V24ELoad + E

E

PRO

F V53 (please mark)

Att DB - minSC Control - SCSBMAG Mode (3) - Att 1/Rate 2Man Att (P, Y) - Min ImpBoresight on LM (COAS)

Make Marks (one/min) by keying ENTRReject with V86E

F V06 N49 (AR, AV, +1)




Key V83E

F V06 N54 (R, R, 6 )



Copy e

Key RLSE

PRO


3-64

SD 68-723

SPACE DIVISION.OF NORTH AMERICAN ROCKWELL CORPORATION


GET

Exactly

TFTPI

08:00

09:30

10:00

Procedure

Key V54E P35

F V06 N94 (S, T, -)

PRO

F V53 (please mark)

Bore sight on LM (COAS)

Make marks (one/min) by keying ENTRReject with V86E

F V06 N49 (AR, AV, +1)

(Remove V50 N18 with ENTR)

Accept: PROReject: Key V32E


F V16 N45 (N, TFI, -1)

PRO (final Cycle)

F V06 N81 (V LV)

CopyVG ' s

Key V83E

F V06 N54 (R, R, 6 )



Copy R, R, 6

Key RLSE

PRO

3-65SD 68-723



GETTFTPI Procedure

11:00

11:20

11:25

11:30

11:45

Calculate Backups P35'

F V06 N81 (Vq LV)

Key V22ELoad (+00000) in R2

PRO

F V06 N59 (VG LOS)

Copy data/Compare Solns

PRO

F VI6 N45 (N, TFI, MGA)

PRO

F V37

Key 41E P41

F V50 N18

Key ENTR (Bypass mnvr)

F V06 N85 (Vq Body)

Man Att (3) - Rate CMD

If PROG Alarm, TIG SlippedDSKY Returns atnew TIG - 35 sec

DSKY Blanks

V16 N85 (VG Body)

THC - Armed

Call for Fuel Printout (§)

3-66SD 68-723



GETTFTPI Procedure

12:00

14:00

F V16 N85 (VG Body)

Null VQ'S with THC

PRO (exit P41)

Call for Fuel Printout (9)

THC - Locked

F V37

Key 35E

F V50 N18 (auto mnvr)

Key ENTR (bypass mnvr)

F V16 N45 (N, TFI, -1)

Key V54E

F V06 N94 (S, T, -1)

Key V24ELoad + E

E

P41

P35

PRO

F V53 please mark

Man Att (P, Y) - Min Imp


Make LM Marks (one/min) by keying ENTRReject with V86E

F V06 N49 (AR, AV, +1)


3-67

SD 68-723


Table 3-6. ME 104 Post CDH to Rendezvous Termination .. (Cont)

GETTFTPI Procedure

16:30

17:00

18:00

PRO (process last mark) P35


Key V83E

F V06 N54 (R, R, 6 )


Key NOUN

Copy 6

Key RLSE

PRO


Key V54E

F V06 N94 (S, T, -)

PRO

F V53 (please mark)


Make LM Marks (one/min) by keying ENTRReject with V86E

F V06 N49 (AR, AV, +1)




3-68

SD 68-723



GETTFTPI Procedure

Exactly 19:30

20:00

21:00

PRO (final cycle)

F V06 N81 (VG LV)

Copy VQ

Key V83E

F V06 N54 (R, R, 6 )



Copy R, R,6

Key RLSE

F V06 N54 (R, R, 6 )

PRO

Calculate Backups

F V06 N81 (VG LV)

PRO

F V06 N59 (VG LOS)

Copy/Compare Solns

PRO

F VI6 N45 (N, TFI, MGA)

PRO (Exit P35)

F V37

Key 41E

F V50 N18 (R, P, Y)

P35

P41

3-69

SD 68-723



GETTFTPI Procedure

21:20

21:25

21:30

21:45

22:00

Key ENTR (bypass mnvr)

V06 N85 (VG Body)


P41

If PROG Alarm, TIG slippedDSKY Returns atnew TIG - 35 sec

DSKY Blanks

V06 N85 (VQ Body)

THC -. Armed

Call for Fuel Printout (To)

F V 1 6 N 8 5 (VG Body)Null VG' s with THC

PRO (Exit P41) .

Call for Fuel Printout

THC - Locked

*Call for R, R data (RTSS)

F V37

Key OOE

SC Control - SCS

Key V83E

F V06 N54 (R, R, 6 )

POO

3-70SD 68-723



GETTFTPI Procedure

SC Control - SCS POOAtt DB - MinBMAG Mode (3) - Att I/Rate 2Check LOS Rates

*Call for R R dataCompare R, R, LOS Rate

with LM Radar Data

Man Att (P, Y) - Min ImpBo re sight on LM - COAS


Key V83 if LM not burned

F V16 N54 (R, R, 6 )*Call for R, R data

F V16 N54 (R, R, 6 )

Compare R & R w/RRdata

PRO

Check LOS Rate/Compare w/RR data*Call for R, R data

LOS Control & Braking

Auto RCS Sel B/D Roll - MNAEMS Func - AVEMS Mode - Auto

Key V37E 47E P47

F V16 N83 (AV Body)

THC - Armed

Key V83E if LM not burned

F V16 N54 (R, R, 6 )

3-71SD 68-723



GETTFTPI Procedure

Perform Braking

Perform LOS Control(Key V60 as Required)

Call for Fuel Printout for BrakingBefore and After

Call for frequent R, R data

Braking Gates

P47

R

1. 0 nmi

0. 5

0. 25

1000 ft

R

25 fps

15

10

5 fps

3-72

SD 68-723


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3-73

SD 68-723


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3-74

SD 68-723


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3-75SD 68-723


3.4 ENTRY



1. Substantiate the capability of the integrated subsystem to performan automatically steered trajectory under nominal and off-nominalentry state vector, spacecraft, and landing site conditions.

2. Substantiate the capability to perform a manually steered GNCSentry for nominal and off-nominal landing site conditions.

3. Demonstrate capability to perform an entry with the GNCSinoperative.

4. Substantiate EMS as a backup display and verify adequacy of thescroll pattern.

5. Establish propellant budgets for entry.

6. Establish contingency procedures dictated by new panelconfiguration*

7. Verify nominal and backup G&C procedures.

8. Substantiate EMS, constant bank, and rolling entries.


10. Verify the related COLOSSUS programs. (P61, P62, P63,P64, P67)

3. 4. 2 Study Scope

During the entry study phase, the G&C events that occur between theend of the deorbit burn and jettison of the apex cover prior to drogue chutedeployment will be evaluated. For particular cases, SPS deorbit and RCSdeorbit phases will be included to provide continuity. The three basic entrymodes will be substantiated for ME .104, the major portion of the evaluationhaving been accomplished during ME 101. Particular emphasis will be givento the verification of the COLOSSUS entry programs. The three entry modes

3-76

SD 68-723


are the automatic GNCS, the manual GNCS, and the .SCS. The modes aredescribed below, and a simplified block diagram of each is shown inFigure 3-1.

1. Automatic GNCS Entry. In this entry mode, the crew primarilymonitors trajectory parameters and vehicular dynamics,

2. Manual GNCS Entry. In this entry mode, the crewman willsatisfy CMC steering commands displayed on the FDAI withrotation control inputs into the SCS for roll attitude control.

3. SCS Entry. In this entry mode, the crewman manually controlsthe CM attitude by monitoring the FDAI and utilizing the rotationcontrol. The crewmen must control the lift vector such that noviolations of tangency rays on the EMS scroll occur. For somecases, transition to an SCS entry from a GNCS entry, simulatinga CMC malfunction, will be accomplished.

3.4.3 Run Description

The entry study phase will cover the G&C events from CM/SM separa-tion to drogue chute deployment. This includes the preentry phase prior to0. 05 g and the atmospheric entry phase after 0. 05 g. During the preentryphase, the CM is oriented to the inertial attitude required for a heat shield-forward aerodynamic trim condition at 0. 05 g and maintains this inertialattitude until 0. 05 g. During the atmospheric entry phase, the CM is"steered" to a preselected target by rotating the CM about the wind axis(roll) with rate damping in the pitch and yaw axes. The CMC and crewfunctions after CM/SM separation are described below for each of the threebasic entry modes.

1. Automatic GNCS Entry. The detailed test procedures and theinitial switch positions for the display panels are presented inTable 3-9.

2. Manual GNCS Entry. The only difference between a. manual GNCSentry and an automatic GNCS entry is that the CM attitude iscontrolled by the astronaut using the rotation control rather thanthe entry DAP. The astronaut uses the CMC steering commandsthat appear on the FDAI attitude error needles for attitude con-trol information. Manual maneuver control is selected by aclockwise rotation of the translation control.

3. SCS Entry. When in the SCS entry mode, the astronaut manuallycontrols the vehicle attitude using the rotation control and

3-77SD 68-723


AUTOMATIC GNCS MODE

GNCS CM RCS

FDA IMONITOR

PILOTMONITOR

EMS

SCS

MANUAL GNCS MODE

GNCS

FDA I

SCS MODE

FDA I

ATTITUDECOMMANDS

PILOT

oc.o

RATE CMD

SCS

ACCEL CMD

EMS

RCS

* /(P COS«+ R SIN«)dt

ANGULAR RATES

ATTITUDEATT ERRRATE PILOT

CD CO

_ RATE CMD1

EMS

SCS

ACCEL CMD

I.05 G

RCS

Figure 3-1. Basic Entry Control Modes

3-78SD 68-723


monitoring the FDAI ball and EMS displays. Several controltechniques can be used, including a rolling entry and constant-bank profiles.


The run schedule synopsis is presented in Table 3-10. Included inthe schedule is the flight mode utilized, the type of initial condition statevector, the target, CM L/D, control mode, estimated time per run, and acomment as to objective.

3-79SD 68-723


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3-80

SD 68-723


Table 3-9A. ME 104 Automatic GNCS Entry

Step Procedure Expected

REQUIRED

CMC - ONISS - ON . • •SCS - ON

Set display panel switcherSet event timer

Count up event timer at start of program

K e y V S Y E O O EAlign FDAI 2ManAtt — Accel CMDManeuver to separation attitude

Roll = 1 8 0 . 0 DECPitch = 1 8 0 . 0 DECY a w = 4 5 . 0 D E C

CM/SM sep (both) —on (up)RCS TRNFR —CMRCS CMD — ON

Maneuver to entry attitude

RollPitchYaw

0.0 DEC55.0 DEC

0. 0 DEC

Auto RCS SEL A/C ROLL(4) —OFFAuto RCS SEL CM2(6) — OFF

(Dl, D2, A3, C4, D3, B4)

K e y V 3 7 E 6 l EFL V06 N61

Impact lat . ; DEG•Impact long . DEGHds up/dn

IF reject V25E load dataAccept PRO

FL V06 N60 (Entry Data)G max . GV pred . FPSGamma El . DEG

RecordPRO

3-81SD 68-723


Table 3-9A. ME 104 Automatic GNCS Entry (Cont)


10

11

12

FL V06 N63RTOGO (0. 05g to spl) ____ .VIO (at 0. 05g) _____ .TFE __ B __

EMS mode — STBYEMS func —Test 5

Set scroll patt. to 37KEMS func — RNG set

Set RNG ind for RTOGOEMS func — Vo set

Align scroll to display indEMS func — EntryPRO

P62 (auto select by P6l)IF FL V37

Key 62E

FL V51 N2522211 (Request CM/SM sep)

PRO

FL V06 N61Impact lat ___ . __

NMFPSMINSEC

DECDECImpact long ___ . __

Hds up/dn ___ . __PRO (If rej V25E load new data)

DSKY P63EMS mode Auto

Align FDAI 2BMAG MODE (3) — rate 2

V06 N64 (monitor)G . __ _ GVI . FPSRTOGO ,~_ NM

Check RTOGO agrees with EMSMAN ATT(3) — Rate CMDSC CONT — CMC

3-82

SD 68-723


Table 3-9A. ME 104 Automatic GNCS Entry (Cont)


13

14

15

16

DSKY — P64 (0. 5g)

0. 05g sw —On (up)EMS roll —On (up)

V06 N68 (MONITOR)BETAVIH DOT

DSKY — P67 (0. 2g)

V06 N66 (MONITOR)BETACRSRNG ERRDWNRNG ERR

VI 6 N67 (MONITOR)RTOGOLATLONG

MONITOR ALTIMETER

DEGFPSFPS

DEGNMNM

NMDEGDEG

3-83

SD 68-723


3.5 IMU ALIGNMENT



1. Determine the accuracy of the IMU orientation as performed by thecrew using the sextant (SXT) for both the CSM and LM/CSMconfigurations.

2. Determine the accuracy of the IMU orientation as performed by thecrew using the crewman's optical alignment sight (COAS) for theLM-off configuration.

3. Determine the accuracy of alignment of the IMU using the SXTfor both LM-on and LM-off configurations.

4. Determine the accuracy of alignment.of the IMU using the COASfor the LM-off configuration.

5. Verify the operational integrity of the IMU orientation program(P51) and IMU realignment program (P52).

6. Verify the operational integrity of the backup IMU orientationprogram (P53) and backup IMU realignment program (P54).

7. Determine the time and RCS propellant required to perform eachIMU alignment and realignment.

8. Evaluate the related GfcC procedures.

9. Provide a data base for postflight analysis. .

3. 5. 2 Study Scope

This portion of the study will evaluate the capability to perform the IMUorientation, the accuracy of the determination, and the RCS propellant requiredfor the alignment tasks. The IMU alignment that occurs before each of theseven SPS burns, except Burn 6, will be simulated. IMU orientation deter-mination will be simulated, in addition to alignment, for SPS Burns 1, 2,and 5. IMU alignment prior to the rendezvous operations, prephasing and

3-84SD 68-723


Table 3-10. Entry Run Schedule

DeorbitFlight •Mod,-

GS,N/extiV

G«.N/3»extiV

GS.N/MTVC

GfcN (over burn)

GJ.N (under burn)

SCS auto TVC

3 a SCS autoTVC

SCS auto TVC/MTVC

GfcN/ext iV

Reent r ies only

NA

Ent ryrlichtMode

GC.N auto

\rSCS-EMS

\ iGS.-N manual

G&N auto

1 rGfcrN manual

1fSCS-EMS

1tConstant bank

CNCS man/SCS

1Rolling

Hun

Prior todt-nr

1

>U bu rn

f

End ofdeorbi t burn

1 t

400 k

Ênd ofdeorbit burn

1400 k

E n t r yState

Vector

Nominal

1Over burn

Under burn

Nominal

1 t

Nominal

1 >

TaI. at

rent/Long

Nominal

J[80 center

30 center

Nominal

1 p

Nom nalJV

Nominal

30 off center

60 off center

80 center

80 center

30 off center

60 off center

60 off center

Non-

30 0

nal

ff center

60 off center

Nom nal

Nom inal

30 off center

60 off center

Nominal1

1y

30 off center

60 off center

TBD fromrun

L/D

Nominal

i p

High

Low

Nominal

î

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Nominal

j

Nominal

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AllControl

DAP

,,

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Rate CMD

ACCEL CMD

ACCEL CMD

Rate CMD

ACCEL CMD

Rate CMD

ÂCCEL CMD

iRate CMD

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f loninteni *

Monitor CMC, and(CMS. V e r i f y DAP

V e r i f y backup

Pilot flies CMCatt i tude e r ror nee'lles;~Time for above

23 schedule r u n s arelisted in SP.S AV

Moni to r CMC andobserve CMC t rendsfor d i f f e r e n t tareet ,locations

Evaluate crew

CMC commands for

locations

Evaluate the backupent rv technioue

: C M C fa i l s d u r i n creen t ry and EMS

3-85

SD 68-723


Table 3-10. Entry Run Schedule (Cont)

FailureMode

Roll jet drvrhrd over

Pitch jpt drvrhrd over

Yaw jet drvrhrd over

Roll direct collhot short

Pitch direct coilhot short

Yaw direct coilhot short

Yaw BMAG Zop^n

Roll a\v amphrd over withno opp jet

EntryFlightMode

O&N auto/man

1

G&N

i

GfcN man

RunInitiation

End ofdeor

1

l)it burn

r

EntryState

Vector

Nominal

4

TargetLat/Long

Nominal

if

L/D

Nominal

<J

AltControl

Rate CMD

1r

Total estimated time includea only run time anduplinking time

EatNo. of

Runa

1

1

1

1

1

1

1

1

CatTimeperR u n

(min)

15

35

35

'35

35

35

35

35

'

TotalEat

Time(min)

35

35

35

35

35

35

35

35

1065

Comrrmnt H

Failure at « < 0. 05

Failure at g ^ 0. 05

Failure at g «• 0. 05

Failure at « > 0. 05

Failure at q ^0. 05

Failure at 2 < 0. 0!

Failure at 2 ' 0. Or

Failure at s > 0. Or

3-86

SD 68-723


post-TPIj, will be simulated. The alignment of the IMU to one of threeorientations will be investigated: the "preferred" orientation, which is theoptimum platform alignment for a specific burn; the "nominal" orientation,which is the local geocentric orientation; and the "REFSMMAT" orientation.The "landing site" orientation will not be investigated. For those SPS burnsor rendezvous operations performed in the LM-off configuration, the IMUorientation and alignment using the crewman's optical alignment sight (COAS)will be simulated.


Prior to each of the seven SPS burns (except Burn 6) and the rendez-vous operations, post-TPIj, and prephasing, the IMU is fine-aligned to oneof the three orientations. If the IMU has been turned off or has been allowedto drift for. an extended period of time, the existing alignment must first bedetermined. The IMU orientation determination is accomplished using pro-gram P51. The IMU alignment is then performed using program P52 and,time permitting, occurs on the succeeding nightside portion of the orbit. Inthe contingency of an optics failure, the IMU orientation determination andalignment may be performed using the COAS. COAS utilization requires amodified program procedure; the IMU orientation is accomplished using thebackup IMU orientation program (P53), and the alignment is performed usingthe backup IMU realignment program (P54). The detailed procedures foreach of these programs are presented in Tables 3-11, 3-12, 3-13, and 3-14,respectively.

3. 5.4 Run Schedule Synopsis

Table 3-15 presents the schedule of runs that will be used to verify theIMU and backup IMU orientation determination and alignment programs.The runs are categorized as to SPS or rendezvous burn, number and type ofrun, IMU orientation utilized, vehicle configuration, programs verified,error sources, control modes, and simulator run times. The total numberof runs scheduled is 31, of which 17 use the sextant and programs (P51 andP52), 9 are scheduled for backup alignments employing COAS and programsP53 and P54, and the remaining 5 are for backup IMU-GDC alignments.SPS burns 1 through 5 will be preferred orientation alignments. REFSMMATalignments will be used for both rendezvous operations. The nominal align-ment option of P52 is scheduled for verification on the post-TPI^ rendezvousoperation. The deorbit burn will be aligned to a simulated ground uplinkorientation. All runs except a duplication of Burn 4 will be made •with IMUerror coefficients. The duplicated SPS Burn 4 run .will be initiated withdata simulating the effects of long-term gyro drift.

3-87SD 68-723


Table 3-11. P51 IMU Orientation Procedures

Step Crew Operation Step Crew Operation

2

3

CMC - onISS - onSCS - on

CMC ATT-IMUlogic 2/3 power-on

Optics power - upG/N opt pwr - onG/N pwr - AC1 or AC2Opt mode - manualOpt zero - zero 15 sec

Select total attitude display

Key 37E 51E

5

6

FL V50 N2500015 (acquire target)

a. Select desiredattitude control modeand maneuver

May key VI6 N20 tomonitor for impendinggimbal lock)

PRO

or 10

To coarse align IMUto SC axis ENTR(when attitude isacceptable)

V42 N22 (coarse align)R . P . Y 000.00 deg

No attitude light on -then off and recycleto Step 4

FL V51 (please mark)

FL V50 N2500016 (terminate marks)

ACCEPT - PROREJECT - mark reject

button

FL V01 N71OOOXX (target code)

ACCEPT - PROREJECT - V21E - load

data, recycle to Step 5for Target 2

Planet onlyFL V06 N88

FL V06 N05XXX. XX DEG(star angle difference)

ACCEPT - PROREJECT - V32E return to

Step 4

FL V37 KEY XXE

3-88

SD 68-723


Table 3-12. P52 IMU Realignment

Step

1

2

3

4

Crew Operation

CMC - onIMU - powered - up and

alignedSCS - powered - upG/N pwr optics - onBMAG mode (3 ea) -

Rate 2SCS channels (4 ea) - onSC cont - CMCOptics - man, opt zero -

15 sec

KEY V37E 52E

Perform. IMU statuscheck routine (R02)

FL -V04 N06Option code ID 00001Option OOOOXBlank

Rl - option code

R2 - option assumed byCMC

00001 preferred00002 nominal00003 REFSMMAT00004 landing site

Step

5

Crew Operation

ACCEPT - PRO(REFS - Step 9)(pref - Step 7)

Reject - KEY V22E andload option

Possible FL V05 N0900215 - orientation not

specified KEY V32Eand go to Step 4

PROG and PGNS It - on

a. nominal or REFSMATacceptable. (V32E)repeat selection

RSET

b. Preferred desired -select new program todefine orientationV37E E

RSET

FL V06 N34GET (ALIGN)

XXXXX. hrsOOOXX. minOXX.XX sec

ACCEPT - PRO(If nominal go to Step 7)

REJECT - Load GET (KEYV25E) (ALIGN)

3-89SD 68-723


Table 3-12. P52 IMU Realignment (Cont)


FL V06 N89XX. XXX deg latXX. XXX deg long/2XXX. XX nm alt

* stored landing sitecoordinates

*alt should be zero

ACCEPT - PROREJECT - Load data V25E

FL V06.N22 .XXX. XX deg OG rollXXX. XX deg IG pitchXXX. XX deg MG yaw

a. If MGA is acceptable,select mode to ensureCSM stability

PRO

b. If MGA not acceptable ,either(1) Maneuver vehicle to

obtain acceptableMGA, KEY V32E or

(2) Select new programV37E E

Perform coarse alignmentroutine (R50)

NO ATT light onFDAI ball follows IMUgimbal movement--NO ATT light off

*If all angular changes areless than 5 deg, coarsealign will not beperformed.

10

FL V50 N25

00015BlankBlank

please acquirecelestialbody

a. Maneuver to acquiresuitable body - PROor

b. Bypass star selectionroutine ENTER - go toStep 10

. Possible FL V05. N0900405 - 2 stars not inFOV

PROG It - onPGNS It - on

a. Maneuver to acquiresuitable star

PRORSET or

b. KEY V32ERepeat Step 9

RSET

FL V01 N70OOOXX celest body codeBlankBlank

0001-45

464750

PlanetStarSunEarthMoon

ACCEPT - optics - CMCPRO (if planet go to 12)

REJECT - load data V21E

3-90

SD 68-723


Table 3-12. P52 IMU Realignment (Cont)


11 FL V06 N88For planet load only

ACCEPT - PRO, REJECTKEY V25E and load

12 Perform auto opticspositioning (R52)*If OCDU angles not dis-played - VI6 N92E

*Possible FL V05 N09404 ~ TA > 90 deg

a. Select control mode andmaneuver to reduce TA

b. or key V34E

*Possible FL V05 N09407 ~ TA> 50 deg

KEY RELEASE andmaneuver to reduce TA

*When marks are desired,optic mode - manual

13 FL V51 (please mark)Mark (on target)

14 FL V50 N2500016 (term, marks)

ACCEPT - PROREJECT - mark reject

15 FL V01 N71OOOXX target code

ACCEPT - PROREJECT - V21E and load

desired code

Repeat steps 10 through 15for Target 2

16

17

18

19

20

21

Planet onlyFL V06 N88

ACCEPT - PRO

FL V06 N05

XXX. XX degsightingangledifference

ACCEPT - PROREJECT - V32E (go to

Step 19)

FL V06 N93 (Agyro angles)X, Y, Z, XX. XXX deg

ACCEPT - PROREJECT - V32E

FL V50 N25

00014 fine align check

ACCEPT - PRO returnto Step 9

REJECT - ENTR

FL V37

OOE

Optics Zero - Zero

3-91SD 68-723


Table 3-13. P53 Backup IMU Orientation Determination


.1

2

CMC - onISS - onSCS - on

CMC ATT - IMUCOAS - calibrated


KEY V37E 53E

FL V50 N2500015 (acquire target)

V16N20 in LEB to monitorfor impending gimbal lock

*to avoid impending gimballock key ENTER and go to"b" below

a. Select desired attitudecontrol mode, maneuverto acquire target ifnecessary

PRO

b. To coarse align IMU toSC axis ENTR (whenattitude acceptable)

V41 N22 (coarse align)R ,P ,Y - 000.00 degNO ATT light - on, then

offReturn to Step 3

10

FL V06 N92.

SA XXX. XX degTA XX. XXX deg

ACCEPT - PROREJECT - V24E load

desired SA and TA(nominal SA = 000 .00 ,TA = 57.470)

FL V53 (please.mark)

RHC - center target inCOAS reticle (MIN IMPrecommended)

ENTR

FL V50 N2500016 (terminate marks)

ACCEPT - PROREJECT - ENTR and .

return to 5

FL V01 N71OOOXX (target code)

ACCEPT - PROREJECT - V21E and load,

return to Step 4 fortarget 2

FL V06 N88 (planet only)

x .y .z PL .XXXXXACCEPT - PRO

.REJECT - V25E and load

FL V06 N05XXX. XX deg star angledifference

ACCEPT - PROREJECT - V32E and

return to Step 3

FL V37 KEY XXE

3-92SD 68-723


Table 3-14. P54 Backup IMU Realignment Program


2

3

SetupCMC - onIMU - power up and alignedSCS - power upSC cont. - SCSMan att (3 ea) - minimum

impul s eSCS channels (4 ea) - on

Key V37E 54E

Perform IMU status checkroutine fR02)

FL V04 N06

00001 option code IDOOOOX optionBlank

Rl - option code ID for IMUorientation selection

R2 - option assumed by CMC

00001 preferred00002 nominal00003 REFSMMAT00004 landing site

ACCEPT - PROIf REFS selected go to 9If pref selected go to 7

REJECT - load option(KEY V22E)

*FL V05 N09

00215PROG It - onPGNS It - on

preferredselectedbut notdefined

a. If nominal or REFSMMATacceptable

V32E and reselectRSET

b. If preferred desired -select new program todefine orientation

V37 ERSET

FL V06 N34

OOXXX.oooxx.oxx.xx

hrs GET (align)minsec

GET (align) - time at whichR and V are defined fornominal or landing site

* Initial display is '0 ' . Ifaccepted, GET (align) ispresent time.

ACCEPT - PROIf nominal accepted: .go to 7

REJECT - load GET (align)

FL V06 N89 (landing site)

XX. XXX lat (deg)XX. XXX long/2 (deg)XXX. XX alt (nm)

ACCEPT - PROREJECT - load correct

data (KEY V25E)

3-93

SD 68-723


Table 3-14. P54 Backup IMU Realignment Program (Cont)


FL V06 N22 (gimbal angles)

XXX. XX roll (deg)XXX. XX pitch (deg)XXX. XX yaw (deg)

a. If MGA is acceptable -select mode to ensurestability

PRO

b. If MGA not acceptableeither . . ,

(1) Maneuver to accept-able MGA, V32E or

(2) Select new program .V37E E

Perform coarse alignmentroutine (R50)

NO ATT light - onFDAI ball follows IMU

gimbal movementNO ATT light - off

*If angular changes are<5 deg coarse align will

not be performed.

FL V50 N25

00015BlankBlank

acquirecelestialbody

a. Maneuver to acquirebody

PRO

b. Bypass star routineENTR

10

11

12

13

*FL V05 N09

00405Prog light -

onPGNS light

on

two starsnot avail-able infield ofview

a. Maneuver to acquirePRO - then'RSET

b. V32E - repeat Step 9RSET

FL V01 N70

OOOXXBlankBlank

celestialbodycode

00 - Planet01-45 - Star

46 - Sun47 - Earth50 - Moon

ACCEPT - PROIf target not a planet, goto 12

REJECT - load desiredcode

If planet selected

FL V06 N88X, Y, Z PL .XXXXX

ACCEPT - PROREJECT - load data

(KEY V25E)

Perform alternate LOSmark routine (R56)

Repeat Steps 10 through12 for second body

3-94

SD 68-723


Table 3-14. P54 Backup IMU Realignment Program (Cont)

Step

14

15

Crew Operation

Perform sighting displayroutine (R54)

*If sighting results wererejected (V32E) - go toStep 16

Perform gyro torquingroutine (R55)

Step

16

17

Crew Operation

FL V50 N25

00014 PleaseBlank performBlank ) fine align

ACCEPT - PROreturn to Step 9

REJECT - ENTR

Perform programtermination routine (ROO)

FL V37KEY XXE

3-95SD 68-723


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3-96

SD 68-723


3. 6 LANDMARK TRACKING

3. 6. 1 Study Objectives


1. Verify the operational integrity of the orbital navigation program(P22).

2. Verify the operational integrity of the ground track determinationprogram (P21).

3. Determine ease in locating and identifying landmarks.

4. Determine the time and RCS propellant required to perform thenavigation function.

5. Evaluate landmark tracking in the LM-on configuration.

6. Evaluate the orbit determination capability of the orbital naviga-tion program (P22) for the tracking of known and unknownlandmarks.


3. 6. 2 Study Scope

This portion of the study will evaluate the automatic and manual track-ing capability for known landmarks and the manual tracking capability forunknown landmarks. The tracking of landmarks with the CSM configurationwill be performed in the "nominal" sighting a titude. LM-on landmarktracking will be performed using the broadside attitude with respect to theorbital ground track. Other sighting attitudes will be investigated to obtaina comparison with respect to ease of tracking and RCS propellant consump-tion. Tracking of a single landmark and sequential tracking of three ormore landmarks will be simulated. The state vector updates resulting fromprocessing tracking data will be used to evaluate the orbital determinationcapability of the tracking modes. The ground track determination programwill be used during simulation runs to facilitate selection of landmarks.

3-97SD 68-723



Orbital navigation is accomplished by scanning telescope tracking of aknown landmark or by .sextant tracking of an unknown landmark. The naviga-tional measurements are used by the CMC to obtain an estimate of thevehicle's position and velocity. A known landmark is a landmark for whichthe longitude, latitude, and altitude are defined and may be stored in theCMC or entered by -way of the DSKY by the astronaut. An unknown landmarkis a landmark selected by the astronaut because of a recognizable terrainfeature and ease of tracking, but whose coordinates are not defined. Thetracking of a known landmark is further facilitated by the use of the automaticoptics positioning routine, while unknown landmarks must be trackedmanually. Prior to the tracking sequence, the orbital ground track programmay be used to facilitate the selection of known landmarks by computing thelongitude and latitude of the vehicle at selected times during the comingtracking sequence. The detailed procedures for the ground track deter-mination program (P21) and the orbital navigation program (P22) are pre-sented in Tables 3-16 and 3-17, respectively.

3. 6. 4 Run Schedule Synopsis

Table 3-19 presents the schedule of runs that will be used to verifythe orbital navigation program (P22) and the ground track determinationprogram (P21). The runs are classified as to landmark number, trackingoption, control mode, error sources, error values, and simulator runningtime. The landmark numbers presented are symbolic in that two basictracking sequences will be investigated. The landmark F type of sequencewill occur near the highest latitude of the ground track, and the T-typelandmark will be near-equatorial. Tracking -will be performed on both asingle landmark and a sequence of three or more landmarks for F and T types.Landmarks will be designated as known, unknown, or a combination of thetwo for sequential tracking. Runs 1 and 2 will be initiated as circular orbits,and state vector errors of various magnitude will be used to establish a database and a region of convergence so as to evaluate the orbital determinationcapability of P22. The nominal, broadside and selected tracking attitudeswill be employed for these runs. Runs 3 and 4 are designed for the samepurpose as Runs 1 and 2 except that Type T landmarks will be employed.Runs 5 and 6 are scheduled to track, in sequence, three or more landmarksthat are combinations of known and unknown. Run 7 is scheduled to showthe effects of a drifting IMU on the orbit determination process. Pro-gram P21 may be utilized in any of the runs but will be scheduled for use inRuns 5 and 6.

3-98

SD 68-723


Table 3-16. P21 Ground Track Determination


1

2

CMC - on

Key V37E 21E

FL V04 N06

00002 option codeOOOOX CMC assumed

option

(00001) = CSM(00002) = LM

ACCEPT - PROREJECT - V22E load option

FL V06 N34 (GET lat-long. )

OOXXXOOOXXOXX.XX

hrminsec

ACCEPT - PROREJECT - V25E load time of

lat-long

FL V06 N43

Lat (+N) XXX. XX degLong. (+E) XXX.XX degAlt XXXX. X nm

(alt above launch padradius)

*To increment time-lat-long. by 10 min keyV32E and return toStep 3

PRO (terminates P21)

FL V37 XXE

3-99SD 68-723


Table 3-17. P22 Orbital Navigation


1

2

Required

CMC - onISS - on and orientation

knownOptics power - upOptics mode - CMCCMC Att - IMU0. 05 G switch - offSCS - on


Select attitude control modedesired

Key V37E 22E

^'Possible PROG alarmKey V05 N09E00210 (ISS not on)

or

00220 (IMU orientationnot known)

FL V37 KEY XXE

FL-V06 N45

R3 XXX. XX deg

max MGAif x-axisin orbitplane

a. If IMU alignment satis-factory, performORDEAL initialization

b. Maneuver to sightingattitude and establishorbit rate

RHC - position Xsc axis^20 deg below localhorizontal, SEF heads up(COAS LOS on horizon oruse ORDEAL FDAI)

RHC or ATT IMP - pitchto offset orbital rate,roll to avoid shaft axis= 10 deg of landmark

PRO

FL V07 N70 (lunar orbitonly)

R2 - LMK code ABCDE

A 1 (known LMK) g2(unknown LMK)

B Index of offsetdesignator

C Not usedDE LMK ID

ACCEPT - If A=2, OPTMODE-Manual PRO (Goto step 8)

or

If A=l & DE = 00 PRO (Goto step 7)

or

3-100

SD 68-723


Table 3-17. F22 Orbital Navigation (Cont)

Step

5(cont)

r.

Crew Operation

If A=l and DE=00 PRO

-"Possible PROG alarm(00404 and 00407)

REJECT - Key V22E andload desired data

FL V06 N89 (landmarkdata)

Lat (+N)Long. /2 (+E)Alt

XX. XXX degXX. XXX degXXX. XX nm

ACCEPT - PROREJECT - V25E load data

^Possible FL V05 N09000404 (TA > 90 deg)maneuver until opticscan acquire landmark

or V34E (terminatesprogram)(FL V37 XXE)

-"Possible PROG alarm(TA >50 deg)Key V05 N09E

00407Maneuver to reducedesired trunnion angle

V06 N92 (new OCDU angles

SA XXX. XX degTA XX. XXX deg

If not displayed - V16 N92Eto mark optics - MAN

Step Crew Operation

FL V51 (please mark)

ACCEPT - repeat markprocedure or PRO

REJECT - push mark rejectand repeat mark procedure

If 5 marks madeFL V50 N2500016 (terminate marks)ACCEPT - PROREJECT - mark reject

Optics zero (15 sec)Optics mode - CMC

FL V05 N71 (landmarkdata)

R2 - ABCDE

A =1 (known), 2 (unknown)B = offset indicatorC =unusedDE = landmark ID

ACCEPT - PRO, if A = 2(or A = 1 and DE£0) go

to Step 11

REJECT - V22E load data

3-101 SD 68-723


Table 3-17. P22 Orbital Navigation (Cont)


10

11

12

FL V06 N89 (landmarkcoordinates

Lat XX. XXX degLong. /2 XX. XXX degAlt XXX. XX nm

ACCEPT - PROREJECT - V25E load data

FL V06 N49

AR XXXX. X nmAV XXXX. X fps

ACCEPT - PROREJECT - V32E and in

EO -return to Step 6 or LO -return to Step 5

FL V06 N89

Lat XX. XXX degLong. /2 XX. XXX degAlt XXX. XX nm

ACCEPT - PRO, EO -return to Step 6, LO -Step 5

REJECT - V32E, EO -return to Step 6,LO - Step 5

13 Key V34E (to terminate P22)

FL V37 key XXE

3-102 .SD 68-723


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3.7 SM ABORT



1. Verify efficient and satisfactory crew operational proceduresfor each SM abort mode.

2. Evaluate the system rate damping capability for tumbling aborts.

3. Evaluate the adequacy of the time of free fall (tff) and maximumg (Gxnax) limit lines for Mode II aborts.

4. Evaluate the adequacy of the specified prethrust coast time forMode III and IV aborts.

5. Determine SPS AV maneuver execution errors for tumbling aborts(Modes III and IV).

6. Evaluate abort criteria and mode selection logic.

7. Determine RCS and SPS propellant requirements for tumblingaborts.

8. Evaluate the effectiveness of the land avoidance criteria forMode III aborts.

9. Evaluate the effectiveness of Mode III and IV AV maneuvers toachieve the desired terminal conditions.

10. Verify satisfactory operation of related CMC programs.

3.7.2 Study Scope

The SM abort study will evaluate the three abort modes (II, III and IV)that cover the phases of the launch from LES jettison to orbit insertion. TheMode II and III aborts for which orbit insertion is not achieved will beevaluated through the entry phase. This will be the first mission evaluation

3-105SD 68-723


of SM aborts off the Saturn V launch vehicle and with a fully loaded CSM.The basic SM abort philosophy is presented in the flow diagram in

Figure 3-2.


The major events of the three abort modes are described below.

3.7. 3. 1 Mode II

This mode results in a free fall into the continuous recovery area(Pad + 60 nm to 3350 nm downrange) with a maximum load factor duringentry of 16 g and a minimum of 100 seconds' f ree fall to 300, 000 feet. Thenominal range of time from liftoff for this mode is approximately 185 to630 seconds. The sequence of G&C events is as follows:

1. RCS +X translation and/or SPS rate damping burn

2. Maneuver to CM/SM separation attitude and separate

3. Maneuver to entry attitude

4. Full lifting entry

3. 7. 3. 2 Mode III

This is the least probable abort mode and will be used only ifimmediate return of the spacecraft becomes necessary. This mode is usedfrom approximately 630 seconds after liftoff to orbit insertion. It providessplashdown in the discrete recovery area 3350 nm downrange of the padwith the following sequence of events:

1. RCS +X translation and possibly an SPS rate damping burn

2. Maneuver to the retrograde thrusting attitude and performance ofrequired AV

3. Maneuver to CM/SM separation attitude and separation

4. Maneuver to entry attitude

5. Entry into discrete landing area

3-106

SD 68-723


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3-107SD 68-723


3. 7. 3. 3 Mode IV

From GET of 600 seconds to orbit insertion, the capability existsfor contingency orbit insertion. The following sequence of events isplanned.

1. RCS +X TRANSLATION and possibly an SPS rate damping burn

2. Maneuver to the posigrade thrusting attitude and performance ofrequired AV to achieve an initial orbit with a minimum perigeealtitude of 75 nm.

3. A burn at apogee to obtain the desired orbit

An example of a Mode IV abort is given in Table 3-19.


The SM abort study phase will evaluate the abort capability fromvarious points throughout the launch phase from LES jettison to orbitinsertion. Various failure conditions during the abort will be investigated;failures •will include loss of internal attitude reference, loss of voicecommunications, and CMC failure. The run schedule synopsis is presentedin Table 3-20.

3-108SD 68-723


Table 3-19. Mode IV SPS Abort

Event TimeStep (sec) Crew Procedure

CMC - on (required)ISS - on (required)SCS - on (required)CMC ATT - IMULOGIC BUS 3 - on (up).05 g - OFFBMAG MODE - RATE 1FDAI SCALE - 50/15FDAI SEL - 1/2RATE - HIGHATT DBD - MAXLIMIT CYCLE - OFFDIRECT RCS - on (up)RCS CHANNELS (4) - ASC CONT - SCSAV THRUST - OFFSPS THRUST - NORMALLV/SPS IND - SII/SIVBRCS CMD - OFFSCS TVC - AUTOTVC GMBL DR - AUTOSPS GMBL MOT (4) - onEMS AV IND - 3000. 0 fpsGDC aligned to IMUMAN ATT - RATE CMD/RSI align to 0 deg

EMS FUNC - AVEMS MODE - STDBYRCS TRNFR - SMEvent timer - 00:03SPS GMBL ind settings

6 et =.

6 t =.

.deg.

-deg.

00:03 Computer run initiated following booster separation.

3-109SD 68-723

SPACE DIVISION,OF NORTH AMERICAN ROCKWELL CORPORATION

Table 3-19. Mode IV SPS Abort (Cont)

Step

1

2

3

4

5

6

7

8

Event Time(sec)

00:03. 8

00:04

00:24

Crew Procedure

Event time reset and counting up

EVNT TMR RSET - RESETEVNT TMR STRT - START

DIRECT ULLAGE - push

RCS CMD - on

LV/SPS IND SII/SIVB - GPI

THC - center and +X translationDIRECT ULL rel

Monitor spacecraft rates

Key V37EKey 47 ENTR(30 sec for display to appear)

Terminate +X translation

Key V16 N50 E

SPLASH ERROR . _ n. mi.

HP ._n.mi .

TFF B min - sec

Maneuver to insertion attitude

R 180 degP 350 degY 0 deg

Obtain insertion update

3-110SD 68-723


Table 3-19. Mode IV SPS Abort (Cont)

Step

9

10

11

12

13

14

15

16

17

18

Event Time(sec)

120

135

173

Crew Procedure

BMAG MODE (3) - ATT 1 RATE 2

Verify SPS GMBL ind (2) = SPS GMBL tw (2)settings

6 i | i f = deg

EMS MODE - AUTO

Start Ullage

AV THRUST (2) - NORMAL

SPS THRUST - DIRECT ON

Terminate ullage - IGN +1 sec

AV ind = 1950 fps (HP ^75 nm)

AV THRUST (2) - OFF

EMS MODE - STBYEMS AV ind 1884 fps

SECO +40 secStatus from ground

3-111SD 68-723


Table 3-20. SM Abort Run Schedule Synopsis

RunNo.

1

2

3

4

5

6

7

8

9

10

11

12

Mode

II

II

II

III

III

III

III

IV

IV

IV

IV

IV

Description of Run

Min. tff HighLV/CSM Rates

Max. G, HighLV/CSM Rates

End of Mode IIHigh LV/CSM Rates

Early Mode IIINominal LV/CSM Rates

Early Mode IIINominal LV/CSM Rates

Late Mode IIINominal LV/CSM Rates

Late Mode IIINominal LV/CSM Rates

Mode II/IV CrossoverNominal L/V CSM Rates

Mode II/IV CrossoverNominal LV/CSM Rates

Mode II/IV CrossoverHigh LV/CSM Rates

Mode II/IV CrossoverHigh LV/CSM Rates

Mid Mode IVNominal LV/CSM Rates

Delta-VReqm't(FPS)

0

0

0

- 400

~ 400

-1500

-1500

-2000

-2000

-200.0

~ 2000

~ 1000

Source ofCrew Information

Ground

Ground

Ground

Ground

CMC

Ground

CMC

Ground

CMC

Ground

CMC

Ground

Numberof Runs

1

1

1

1

1

1

1

1

1

1

1

1

3-112SD 68-723


Table 3-20. SM Abort Run Schedule Synopsis (Cont)

RunNo.

13

14

15

16

17

Mode

IV

IV

IV

IV

IV

Description of Run

Mid Mode IVNominal LV/CSM Rates

Late Mode IVNominal LV/CSM Rates

Late Mode IVNominal LV/CSM Rates

Late Mode IVHigh LV/CSM Rates

Late Mode IVHigh LV/CSM Rates

Delta-VReqm't(FPS)

~1000

-100

-100

^100

-100

Source ofCrew Information

CMC

Ground

CMC

Ground

CMC

Numberof Runs

.1

1

1

1

1

17 RunsTotal

3.8 RCS DEORBIT



1. To establish a data base for mission planning and postflightanalysis

2. To verify RCS deorbit procedure compatibility with the COLOSSUSprogram and the SC 103 Main Control & Display Panel configuration

3. To verify RCS propellant requirements and maneuver efficienciesassociated with various procedures and failure modes and to obtaindata to define the RCS propellant/mission redlines beyond whichsuccessful RCS deorbits cannot be achieved.

3-113

SD 68-723


4. To evaluate the CMC program used during RCS deorbit

5. To verify guidance and control capability of performing an RCSdeorbit by achieving a specified entry state vector

3.8.2 Study Scope

The RCS deorbit study phase will evaluate RCS deorbit capability forthree spacecraft loadings with orbit conditions corresponding to the following:

1. Insertion orbit

2. Rendezvous orbit

3. Final orbit (following failure of SPS deorbit)

Service module RCS deorbit will be evaluated at these orbit conditionsin both the CMC and SCS modes with four-quad and two-quad configurations.Three-quad, spin-stabilized retro will be. studied from the rendezvous orbit,during which the AV requirement (170 fps) will probably make two quadoperation impractical.

Hybrid RCS deorbits that combine four-quad tx translation with single-and dual-system CM RCS AV will be evaluated from the rendezvous, and finalorbits. • >.,

3.8.3 Run Description

Simulation runs will start approximately 15 minutes prior to apogee,with the IMU prealigned and the CMC in the external AV program (P30).The G&C system will be properly configured for either the nominal or failureruns. An RCS deorbit simulation run is summarized in Table 3-21. Ahybrid deorbit is given which utilizes both SM and CM RCS thrusting.

Table 3-21. Hybrid RCS Deorbit

Step Crew Procedure

Configure MDPKey —Key ReleaseInitialized in P30V06 N33

. hr

. minsec

3-114SD 68-723


Table 3-21. Hybrid RCS Deorbit (Cont)

Step Crew Procedure

Key V48E (load DAP)FL V04 N 46E

III212IIIIACCEPT-PROREJECT V24E - Load Desired Data

FL V06 N 47E

+ 22222 CSM Weight+ 22222 LM Weight

FL V06 N 48E+ Gimbal Trim Pitch+ Gimbal Trim Yaw

FL V06 N 33 (GETI)

+ 22112- hr

+ 22211- min

+ 212-22 sec

FL V06 N 81 (Delta V Components)

- 2222-1 fPs along x

+ 0 0 0 0 0 fps along Y

- 2211-^. fPs alon§ z

FL V16 N 45Marks

+ 2TB~12 (SET THE DET)Middle Gimbal Angle

FL V37Key 41E (Initiate P41)

FL V50 N 18 (Preferred Attitude)+ ill-11 Ro11

+ lli-Il Pitch+ 222-11 Yaw

Perform Manual Attitude ManeuverTo Roll = 0, Pitch = 228, Yaw = 0

3-115SD 68-723



Step Crew Procedure

10

11

12

13

14

15

16

17

18

19

20

Key V16 N81E (Delta V Components]

-.P. 2 1 0. • 1+ _ O Q _ 0 , O Q _

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21111

FL V06 N47+2_1 II 2. CM Weight

0_ £ 0_ 0 0 LM Weight

FL V06 N47

P trimY trim

Key V46E (activate DAP)

S/C Control to CMCCMC AUTOBMAGS ATT 1 Rate 2

Key Proceed (Auto attitude trim)

EMS Function - V set: set V 41. 0 fpsEMS Function V: ATT D. B. min: Rate-Low:RHC, THC armed: LIM cycle off:EMS Mode - AUTO

FL V50 N18 (preferred attitude)

+2 9. 2 £ 2 R

+fL i 8^. 11 P

+°_ 2.2 2 £ Y

GETI minus 35 sec DSKY blanks

3-116SD 68-723



Step Crew Procedure

21

22

23

24

25

26

27

28

29

GETI minus 30 sec

FL V06 N85

+22112 VGX

+22222 VGY

+ 0 0 0 0 0 V G Z

When DET 00 BOO startSM RCS AV - Monitor EMS AV

V82 E

FL VI6 N44

+ Apogee+ Perigee+ TFF ' ' '

Burn complete; EMS AV = 0HP =

SC control - SCS; CM/SM Sep;RCS transfer - CM; Rate high

Manual maneuver to CM retro

Desired ballR + 2 2 2 - 2 2 DEGP +! 1.5. J) .0 DEC

Y + 2 2 2 - 2 2 DEC

One minute after completion ofSM AV, begin CM AV

MAN ATT PITCH, ACCEL CMD

Begin CM AVRHC 1 - Initialize continuous neg pitchRHC 2 - Pulse plus pitch to maintain

attitude in pitch axisMonitor Hp on DSKY

Discontinue CM AV when Hp = 37. 0 N. M

End of run

3-117SD 68-723


3. 8. 4 Run Schedule Synopsis

The RCS deorbit study, consisting of nominal and failure modes ofSM RCS deorbit and hybrid deorbit, will be conducted at three points of theplanned mission. The selection of initial conditions, grouping of runs, andrelated rationale are summarized in Table 3-22.

Table 3-22. RCS Deorbit Conditions and Rationale

Orbit Type of Run Rationale

Insertion

Rendezvous

Final

SM RCS deorbit,nominal and failure modes

SM RCS, hybridnominal modes

SM RCS, hybridnominal and failure modes

Duty cycles for maximum SCloading

Maximum retro velocity required,intermediate SC loading

Duty cycles for minimum SCloading; minimum retro velocityrequired

The run schedule synopsis for SM RCS deorbit and hybrid deorbitare presented in Tables 3-23 and 3-24.

3.9 MCC/ME 103 JOINT SIMULATION

The study objectives, scope, run definition, and run schedule aredetermined by the Flight Control Division of MSC. It is NR's understandingthat the following maneuvers will be accomplished during the MCC/ME 103joint simulation:

1. SPS Burn 1

2. SPS Burn's 1 and 2

3. SPS Burn 4

4. L/M Rescue - CSM Active Rendezvous .

5. SPS Burns 5 and 6

6. G&N SPS Deorbit

3-118

SD 68-723


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3-119

SD 68-723


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3-120

SD 68-723


7. SCS SPS Deorbit

8. G&N SM RCS Deorbit

9. SCS SM RCS Deorbit

10. G&N Hybrid Deorbit

The initial conditions required and a daily run schedule covering athree day period will be provided by MSC at a later date.

The resultant data will be analyzed by NR personnel and reported onalong with the results of the other study phases.

3. 10 FINAL SOFTWARE VERIFICATION TESTS (FSVT)

The final software verification tests objective is to verify as many ofthe CMC software programs for flight as is practical. To achieve this end,the most recent trajectory data, usually the Operational Trajectory, AOHprocedures, CMC Colossus Tape Revision, and flight plan information willbe utilized in these tests. The exact procedures, and detailed runs schedulewill be mutually determined by NR and MSC at a later date.

3-121SD 68-723


4. 0 DATA OUTPUT REQUIREMENTS

The data output requirements for this simulation are divided into threecategories: analog, environment, and downlink.

4. 1 ANALOG

The analog data requirements consist of parameters that require con-tinuous recording for transient response analysis as well as real-timemonitoring. This list is composed of parameters computed on the analogcomputers and a few select parameters that are computed on the RTSS andD/A-converted. These analog requirements are defined in Table 4-1.

4. 2 ENVIRONMENT

The environment data requirements consist primarily of trajectory-type parameters that are computed on the RTSS and discretes that representthe configuration of the CM panel switches. The environment recordingrequirements are defined in Table 4-2.

4. 3 DOWNLINK

The downlink data consist of CMC stored information. Five downlinkdata lists exist: (1) powered, (2) coast and align, (3) rendezvous and pre-thrust, (4) entry and update, and (5) program 22 (landmark tracking). Eachlist has a 100-word capability. The downlink requirements for this studyare defined in Table 4-3 for each of the five lists.

4-1

SD 68-723


Table 4-1. Analog Recording Requirements

Channel Term

RECORDER 1

12345678

SPS pitch gimbal commandSPS pitch gimbal angle pickoffSPS pitch gimbal rateSPS yaw gimbal commandSPS yaw gimbal angle pickoffSPS yaw gimbal rateSPS thrustLM on - LM off

RECORDER 2

1234

.5.678

Roll rotational stick commandRoll RCS moment, SM/CMRoll body accelerationRoll body rateRoll BMAGIMU outer gimbal angle (roll)AltitudeDynamic pressure

RECORDER 3

1234567

Pitch rotational stick commandPitch RCS moment, SM/CMPitch body accelerationPitch body rate .Pitch BMAG.IMU inner gimbal angle (pitch)

RECORDER 4

12345

Yaw rotational stick commandYaw RCS moment, SM/CMYaw body accelerationYaw .body rateYaw BMAG

4-2

SD 68-723


Table 4-1. Analog Recording Requirements (Cont)

Channel Term

RECORDER 4 (Cont)

678

IMU middle gimbal angle (yaw)

PGA

RECORDER 5

12345678

Displayed roll rateDisplayed roll attitude errorDisplayed pitch rateDisplayed pitch attitude errorDisplayed yaw rateDisplayed yaw attitude errorScale rate discrete, 50/10Scale rate discrete, 5

RECORDER 8

12345678

Quad A/-rollQuad B/+rollQuad C/pitchQuad D/yaw

/system A/system B

SM total/CM total

SM/CM RCS propellant

RECORDER 9

12345678

A4C4B4D4C3AlBlD3

- A2/- C2/- B2/F9 -- D2/F11- A3/F1 -- C1/F3 -- D1/F5 -- B3/F7 -

SM/CM RCS engines

F12- F10F2F4F8F6

4-3

SD 68-723


Table 4-2. Environment Recording Requirements

Symbol Definition Units

ALTITUDE GREATER THAN 400, 000 FEET

THTHTLPSILXYZXDIYDIZDIVITHTIPSIHRGPHITHTPSIHDVGGMA

°"EFAlphaBetaGACCLMASS

VCxVCyVCz

^manFX

FYFZRADAIGAMGAOGAPX

Time from launchGeocentric altitudeGeocentric latitudeGeocentric longitudeSpacecraft position along X inertial axisSpacecraft position along Y inertial axisSpacecraft position along Z inertial axisSpacecraft velocity along X inertial axisSpacecraft velocity along Y inertial axisSpacecraft velocity along Z inertial axisVelocity relative to inertial axisInertial flight path angleInertial heading angleRange measured from pad/targetLocal geocentric Euler angle ,Local geocentric Euler angleLocal geocentric Euler angleTime rate of change of HLocal geocentric velocityLocal geocentric flight path angleLocal geocentric heading angleAngle of attackSide slip angleG's sensed along X bodyTotal massCharacteristic velocity X reference axisCharacteristic velocity Y reference axisCharacteristic velocity Z reference axisManeuver efficiencyForce sensed along X body axisForce sensed along Y body axisForce sensed along Z body axisPosition along XQ axis from earth centerIMU inner gimbal angleIMU middle gimbal angleIMU outer gimbal angleAcceleration along X SM

secftdegdegftftftf t / s e cf t / secf t /secf t / secdegdegnmdegdegdegf t / secf t / s e cdegdegdegdegg'sslugsft/ secf t / secf t / secNDIbIbIbftdegdegdegf t /sec 2

4-4

SD 68-723

SPACE DIVISION of NORTH AMERICAN ROCKWELL CORPORATION

Table 4-2. Environment Recording Requirements (Cont)

Symbol Definition Units

ALTITUDE GREATER THAN 400, 000 FEET (Cont)

APYAPZTHLGD

« eTorbie1XPASYPASZPASXDPSYD PSZDPSXCE

YCE

ZCE

XCDE

YCDE

ZCDE

XLE

YLE

ZLE

XLDE

YLDE

ZLDE

Acceleration along Y SMAcceleration along Z SMGeodetic latitudePitch axis pointing errorsYaw axis pointing errorsOrbital periodOrbital inclination angleOrbital eccentricityAngular momentumLM inertial X position relative to CSMLM inertial Y position relative to CSMLM inertial Z position relative to CSMLM inertial X velocity relative to CSMLM inertial Y velocity relative to CSMLM inertial Z velocity relative to CSMDifference between CMC and environment

CSM inertial X positionDifference between CMC and environment

CSM inertial Y positionDifference between CMC and environment

CSM inertial Z positionDifference between CMC and environment

CSM inertial X velocityDifference between CMC and environment

CSM inertial Y velocityDifference between CMC and environment

CSM inertial Z velocityDifference between CMC and environment

LM inertial X positionDifference between CMC and environment

LM inertial Y positionDifference between CMC and environment

LM inertial Z positionDifference between CMC and environment

LM inertial X velocityDifference between CMC and environment

LM inertial Y velocityDifference between CMC and environment

LM inertial Z velocity

f t /sec 2

f t /sec2

degdegdegmindegNDf t 2 / secftft

ftf t /secf t / secft /sec

ft

ft

ft

f t /sec

f t / sec

f t /sec

ft

ft

ft

f t / sec

f t / sec

f t /sec

4-5

SD 68-723


Table 4-2. Environmental Recording Requirements (Cont)

Symbol Definition : Units

ALTITUDE GREATER THAN 400, 000 FEET (Cont)

a

PebRARPHAHp

. fE

. . ^C

CO

AXI

AYIAZIRLOSVLOSXPLV

YPLV. ' s ,

.ZPLV

QBARMNALPHATPHIAL/D

VAUivlWjG

Semi-major axisSemi-latus rectumTotal energySemi-minor axisApogee distancePerigee distanceApogee distance above earth surfacePerigee distance above earth surfaceTrue anomalyEccentric anomalyLongitude of ascending nodeArgument of latitudeArgument of perigee

*REFSMMAT (RTSS)Sensed acceleration along inertial XSensed acceleration along inertial YSensed acceleration along inertial ZRange along the CSM to LM line-of-sightVelocity along the CSM to LM line-of-sightCSM position in X of LM centered local

vertical coordinate systemCSM position in Y of LM centered local

vertical coordinate systemCSM position in Z of LM centered local

vertical coordinate system

ÂLTITUDE LESS THAN 400, 000 FEET

Dynamic pressureMach numberTotal angle of attackAerodynamic roll angleAerodynamic lift-to-drag ratioAirspeedAirspeed along SC X axisAirspeed along SC Y axisAirspeed along SC Z axisTotal g's

ftftft-lbftftftnmnmdegdegdegdegdeg

ft /sec2

f t /sec2

f t /sec2

•ftf t / sec

ft

ft

ft

lb/ft2

NDdegdegNDf t /secf t / secft /secf t / secg's

*These, parameters are recorded in addition to those listed underALTITUDE GREATER THAN 400, 000 FEET.

4-6

SD 68-7Z3



Switch NameSwitch Open(False or 0)

Switch Closed(True or 1)

DISCRETES

FDAI SCALE

FDAI SELECT

FDAI SOURCE

MAN ATT ROLL

MAN ATT PITCH

MAN ATT YAW

ROTATION CONT POWER-NORMAL 1ROTATION CONT POWER-NORMAL 2ROT CONTROL POWER-DIRECT 1ROT CONT POWER-DIRECT 2BMAG MODE-ROLL

BMAG MODE - PITCH

BMAG MODE - YAW

CMC MODE

SCS TVC PITCH

SCS TVC YAW

TVC GIMBAL DRIVE - PITCH

TVC GIMBAL DRIVE - YAW

SCS ELEC POWER

1

1/2

ATT SET

ACCEL COMD

ACCEL COMD

ACCEL COMD

OFF

OFF

OFF

OFF

ATT I /RATE 2

ATT I /RATE 2

ATT I /RATE 2

HOLD

RATE COMD

RATE COMD

AUTO

AUTO

OFF

50/10512

GDCCMCMIN IMPRATEMIN IMPRATEMIN IMPRATEACAC /DCACAC /DCMNAMNA/MNB .MNBMNA/MNBRATE 2RATE 1RATE 2RATE 1RATE 2RATE 1AUTOFREEAUTOACCEL COMDAUTOACCEL COMD1212GDC /EC AEGA

4-7

SD 68-723


Table 4-2. Environmental Recording Requirements (Gont)



DISCRETES

SCS TVC SERVO PWR. 1

SCS TVC SERVO PWR 2

TELESCOPE TRUNNION

SPEED

AUTO RCS SELECT AI

C1

A2

c2

Bl

Dl

B2,

D2

A3

C3

A4

C4

B3

D3

B4

OFF

OFF

0°

MED

OFF

OFF

OFF

OFF

OFF

OFF

OFF

OFF

OFF

OFF

OFF

OFF

OFF

OFF

OFF

AC 1 /MNAAC 2 /MNAAC 1 /MNAAC2/MNBSLAVE TO SXT25°HILOMNAMNBMNAMNBMNAMNBMNAMNBMNAMNBMNAMNBMNAMNBMNAMNBMNAMNBMNAMNBMNAMNBMNAMNBMNAMNB-MNAMNBMNAMNB

4-8

SD 68-723





DISCRETES

AUTO RCS SELECT D4

LIMIT CYCLEATTITUDE DEADBANDRATETRANS CONT POWERS/C CONTROLSPS THRUST DIRECTDIRECT ULLAGETHRUST ONAV THRUST AAV THRUST BGDC ALIGNSPS GIMBAL MOTORS -

PITCH 1SPS GIMBAL MOTORS -

PITCH 2SPS GIMBAL MOTORS -

YAW 1SPS GIMBAL MOTORS -

YAW 2AV CGIMU CAGEENTRY EMS ROLLENTRY 0. 05GLV/SPS INDLV/SPS INDBMAG POWER 1BMAG POWER 2ATT SETFDAI POWER

OPTICS ZEROOPTICS COUPLINGOPTICS MODEUP TELEMETRY - MDCUP TELEMETRY - LEB

OFFOFFONMINLOWOFFSCSNORMALOFFOFFOFFOFFOFFOFF

OFF

OFF

OFF

LM/CSMOFFOFFONaGPIOFFOFFIMUOFF2

OFFDIRECTCMCBLOCKBLOCK

MNAMNBOFFMAXHIGHONCMCONONONNORMALNORMALONON

ON

ON

ON

CSMONONOFFPCS II/SIVBONONGDC12BOTHZERORESOLVEMAN.ACCEPTACCEPT

4-9

SD 68-723





DISCRETES

SM RCS PRI PROP

SM RCS SEC PROP

SM RCS H E 1

SM RCS HE 2

CM RCS PROP 1CM RCS PROP 2CM SM SEPRCS COMDRCS TRANSFER

ABCDABCDABCDABCD

OFFOFFOFFOFFOFFOFFOFFOFFOFFOFFOFFOFFOFFOFFOFFOFFOFFOFFOFFOFFSM

ONONONONONONONONONONONONONONONONONONONONCM

4-10

SD 68-723


Table 4-3. Downlink Data Requirements

WordNumber First Register Second Register

POWERED LIST

1

2

3

4

5

6

7

8

9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

I.D. (77774g)

CSM state vector (R )./s*

CSM state vector (R )

CSM state vector (R )f t

CSM state vector (V )


CSM state vector (V z)

CSM state vector time

Actual X CDU angle

Actual Z CDU angle

ADOTS roll orOGARATE

ADOTS pitch orOMEGA B pitch

ADOTS yaw orOMEGA B yaw

X attitude error

Z attitude error

THETADX

THETADZ

TIG

T.., Lambertr

RTARGX

RTARGY

RTARGZ

TGO

Synch bits (77340 )8



CSM state vector (R )L-t

CSM state vector (V ).X.




Actual Y CDU angle

ADOTS roll or OGARATE

ADOTS pitch or OMEGA B pitch

ADOTS yaw or OMEGA B

Y attitude error

RCS flags

THETADY

TIG

T LambertF

RTARGX

RTARGY

RTARGZ

TGO

yaw

4-11

SD 68-723


Table 4-3. Downlink Data Requirements (Cont)


POWERED LIST

24

25

26

27

28

29

30

31

32

33

34

35

36

37

38

39

40

41

42

43

44

45

46

47

48

PIPTIME1

DELVX

DELVY

DELVZ

PACTOFF

PCMD

CSTEER

REFSMMAT (RjC )

REFSMMAT (R C )1 ^

REFSMMAT (RjC^

REFSMMAT (R C )

REFSMMAT (R C )Lt C*

REFSMMAT (R C )£ J

Flagword 0

Flagword 2

Flagword 4

Flagword 6

Flagword 8

DSPTAB+0

DSPTAB+2

DSPTAB+4

DSPTAB+6

PIPTIME1

DELVX

DELVY

DELVZ

YACTOFF

YCMD

REFSMMAT (R^)

REFSMMAT (R C )1 Lt

REFSMMAT (R C )

REFSMMAT (R C )C* J.

REFSMMAT (R C )C* L*

REFSMMAT (R C )

Flagword 1

Flagword 3

Flagword 5

Flagword 7

Flagword 9

DSPTAB+1

DSPTAB+3

DSPTAB+5

DSPTAB+7

4-12

SD 68-723




POWERED LIST

49

50

51

52

53

54

55

56

57

58

59

60

61

62

63

64

65

66

67

68

69

70

71

DSPTAB+8D

DSPTAB+10D

TIME 2

LM state vector (R )-A.

LM state vector (Ry)

LM state vector (R7)£-t

LM state vector (V ).X,

LM state vector (V )

LM state vector (V )Z_i

LM state vector time

Actual X CDU angle

Actual Z CDU angle




X attitude error

Z attitude error

THETADX

THETADZ

DSPTAB+9D

DSPTAB+11D

TIME 1

LM state vector (R )

LM state vector (Rv)

LM state vector (R y)





Actual Y CDU angle

Optics CDU trunnion angle



ADOTS yaw or OMEGA B yaw

Y attitude error

RCS flags

THETADY

4-13

SD 68-723




POWERED LIST

72

73

74

75

76

77

78

79

80

81

82

83

84

85

86

87

88

89

90

91

92

93

94

PIP AY

Elevation angle

Central angle

Offset point

Flag word 10

TEVENT

PCMD

LM MASS

DAPDATR1

ERROR X

ERROR Z

WBODY (roll) orOMEGA C (roll)

WBODY (pitch) orOMEGA C (pitch)

WBODY (yaw) orOMEGA C (yaw)

Desired FINAL CDUY

Channel 1 1

Channel 13

Channel 30

Channel 32

PIP AX

PIPAZ

Elevation angle

Central angle

Offset point

Flagword 11

TEVENT

YCMD

CM MASS

DAPDATR2

ERROR Y

WBODY (roll) or OMEGA C (roll)

WBODY (pitch) or OMEGA C (pitch)

WBODY (yaw) or OMEGA C

Desired FINAL CDUX

Desired FINAL CDUZ

Channel 12

Channel 14

Channel 31

Channel 33

(yaw)

4-14

SD 68-723




POWERED LIST

95

96

97

98

99

100

VGTIGX

VGTIGY

VGTIGZ

VGTIGX

VGTIGY

VGTIGZ'

COAST AND ALIGN LIST

1

2

3

4

5

6

7

8

9

10

11

12

13

14

15

16

17

I. D. (77777 _)o


CSM state vector (Ry)

CSM state vector (RZ)

CSM state vector (Vx)


CSM state vector ( V _ )


Actual X CDU angle

Actual Z CDU angle

THETADX

THETADZ

Synch bits (77340Jo




CSM state vector (V ).X.


CSM state vector (V )L-t


Actual Y CDU angle


THETADY

4-15

SD 68-723





18

19

20

21

22

23

24

25

26

27

28

29

30

31

32

33

34

35

36

37

38

39

40

41

42

STARID1

MARKTIMEl

Y CDU angle

Z CDU angle

X CDU angle

MARKTIME2

Y CDU angle

Z CDU angle

X CDU angle

REFSMMAT (R C )

REFSMMAT (R C )1 Lt

REFSMMAT (R C )

REFSMMAT (R 2C i )

REFSMMAT (R C )Ct £*

REFSMMAT (R C )w «J

Flagword 0

Flagword 2

Flag word 4

STARID2

MARKTIME 1

Optics shaft angle for last

Optics trunnion angle MARKTIMEl

MARKTIME 2

Optics shaft angle for last

Optics trunnion angle MARKTIME2

REFSMMAT (R C )

REFSMMAT (R C )J. Lt

REFSMMAT (R C )

REFSMMAT (R C )

REFSMMAT (R C )Lt C*

REFSMMAT (R C )^ 3

Flagword 1

Flagword 3

Flagword 5

4-16

SD 68-723





43

44

45

46

47

48

49

50

51

52

53

54

55

56

57

58

59

60

61

62

63

64

65

66

67

Flag word 6

Flagword 8

DSPTAB+0

DSPTAB+2

DSPTAB+4

DSPTAB+6

DSPTAB+8D

DSPTAB+10D

Actual X CDU angle

Actual Z CDU angle

THETADX

THETADZ

Flagword 7

Flagword 9

DSPTAB+1

DSPTAB+3

DSPTAB+5

DSPTAB+7

DSPTAB+9D

DSPTAB+1 ID

Actual Y CDU angle


RCS flags

THETADY

4-17

SD 68-723



WordNumber

68

69

70

71

72

73

74

75

77

78

79

80

81

82

83

84 -

85

86

87

88

89

90

91

. 92

First Register Second Register


Optics shaft

•- •

IMODES 30

Channel 11

Channel 13

•_

IMODES 33

Channel 12

Channel 14

4-18SD 68-723


t Table 4-3. Downlink Data Requirements (Cont)



93

94

95

96

97

98

99

100

Channel 30

Channel 32

DSPTAB+0

DSPTAB+2

DSPTAB+4

DSPTAB+6

DSPTAB+8D

DSPTAB+10D

Channel 31

Channel 33

DSPTAB+1

DSPTAB+3

DSPTAB+5

DSPTAB+7

DSPTAB+9D

DSPTAB+1 ID

RENDEZVOUS AND PRETHRUST LIST

1

2

3

4

5

6

7

8

9

10

11

12

13

I.D. (77775g)

CSM state vector (R )A


CSM state vector (R )£-»

CSM state vector (Vx)




Actual X CDU angle

Actual Z CDU angle

ADOTS roll orQGARATE



Synch bits (77340 )o




CSM state vector (V )X



CSM state vector, time

Actual Y CDU angle





4-19SD 68-723





14

15

16

17

18

19

20

21

22

23

24

25

26

27

28

29

30

31

32

33

34

35

36

37

38

X attitude error

Z attitude error

THETADX

THETADZ

TIG

T LambertF

RTARGX

RTARGY

RTARGZ

MARK TIME

Y CDU angle

Z CDU angle

X CDU angle

TPI TIME

ECSTEER

DELVTPF (magnitude)

TPF time

DELVSLV X

DELVSLV Y

DELVSLV Z

Range

Y attitude error

RCS flags

THETADY

TIG

T LambertF

RTARGX •'

RTARGY

RTARGZ

MARK TIME

Optics shaft angle

Optics trunnion angle

OPTIC MARKS

TPI TIME .

DELVTPF (magnitude)

TPF time .

DELVSLV X

DELVSLV Y

DELVSLV Z

Range

4-20

SD 68-723





39

40

41

42

43

44

45

46

47

48

49

50

51

52

53

54

55

56

57

58

59

60

62

Range rate

Flagword 0

Flagword 2

Flagword 4

Flagword 6

Flagword 8

DSPTAB+0

DSPTAB+2

DSPTAB+4

DSPTAB+6

DSPTAB+8D

DSPTAB+10D

TIME 2

LM state vector (R,,)

LM state vector (Rv)






Actual X CDU angle

Actual Z CDU angle



Range rate

Flagword 1

Flagword 3

Flagword 5

Flagword 7

Flagword 9

DSPTAB+1

DSPTAB+3

DSPTAB+5

DSPTAB+7

DSPTAB+9D •:• y

DSPTAB+1 ID

TIME 1

LM state vector (Rv)2\.

LM state vector (RY)


LM state vector (V )A


LM state vector (V )£~*


Actual Y CDU angle




4-21

SD 68-723


Table 4-3. Downlink Data Requirements (Corit)


RENDEZVOUS AND PRETHRUST LIST .

63

64

65

66

67

68

69

70

71

72

73

74

75

76

77

78

79

80

81

82

83

84

85


X attitude error

Z attitude error

THETADX

THETADZ

Optics shaft

Elevation angle

Central angle

Offset point

DELVEET3 X

DELVEET3 Y

DELVEET3 Z

LM MASS

DAPDATR1

ERROR X

ERROR Z


ADOTS yaw or OMEGA B

Y attitude error

RCS flags r

THETADY

Elevation angle

Central angle

Offset point

DELVEET3 X

DEL.VEET3 Y

DELVEET3 Z

CM MASS

DAPDATR2

ERROR Y

WBODY (roll) or OMEGA

yaw

C (roll)

4-22

SD 68-723





86

87

88

89

90

91

92

93

94

95

96

97

98

99

100



Desired FINALCDU Y

Channel 11

Channel 13

Channel 30

Channel 32

RTHETA

GEODETIC LAT

LONG

V PRED

GAMMA(EI)


WBODY (yaw) or OMEGA C (yaw)

Desired FINAL CDU X

Desired FINAL CDU Z

Channel 12

Channel 14

Channel 31

Channel 33

RTHETA

GEODETIC LAT

LONG

V PRED

GAMMA(EI)

ENTRY AND UPDATE LIST

1

2

3

4

5

6

I.D. (77776Jo




CSM state vector (Vv).A.


Synch bits (77340Jo

CSM state vector (R „)XX





4-23

SD 68-723





7

8

9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

26

27

28

29

30

CSM state vector (V )^j


Actual X CDU angle

Actual Z CDU angle




X attitude error

Z attitude error

THETADX

THETADZ

ENTRY DAP MODE

QREL (pitch rate)

L/D1

CSM state vector (V„)£-t


Actual Y CDU angle





Y attitude error

RCS flags

THETADY

PREL (roll rate)

RREL (yaw rate)

L/D1

4-24SD 68-723





31

32

33

34

35

36

37

38

39

40

41

42

43

44

45

46

47

48

49

50

51

52

53

54

Roll error

LATANG

ROOT

THETAH

GEODETIC LAT(SPLSH)

LONG (SPLSH)

ALPHA

Flagword 0

Flagword 2

Flagword 4

Flagword 6

Flagword 8

DSPTAB+0

DSPTAB+2

DSPTAB+4

DSPTAB+6

DSPTAB+8D

DSPTAB+10D

TIME 2

PIPTIME1

DELVX

DELVY

Roll angle

LATANG

ROOT

THETAH

GEODETIC LAT (SPLSH)

LONG (SPLSH)

BETA

Flagword 1

Flagword 3

Flagword 5

Flagword 7

Flagword 9

DSPTAB+1

DSPTAB+3

DSPTAB+5

DSPTAB+7

DSPTAB+9D

DSPTAB+1 ID

TIME 1

PIPTIME1

DELVX

DELVY

4-25

SD 68-723





55

56

57

58

59

60

61

62

63

64

65

66

67

68

69

70

71

72

73

74

75

76

77

DELVZ

TTE (EMS)

VIO

VPRED (El)

Actual X CDU angle

Actual Z CDU angle




X attitude error

Z attitude error

ERROR X

ERROR Z

THETADY

ENTRY DAP MODE

OREL (pitch rate)

DELVZ

TTE (EMS)

VIO

VPRED (El)

Actual Y CDU angle

Optics GDU trunnion angle




Y attitude error

RCS flags

ERROR Y

THETADX

THETADZ

PREL (roll rate)

RREL (yaw rate)

4-26

SD 68-723





78

79

80

81

82

83

84

85

86

87

88

89

90

91

92

93

94

95

96

97

98

99

100

LM MASS

DAPDATR1

Roll angle




Desired FINALCDU Y

Channel 11

Channel 13

Channel 30

Channel 32

GAMMA (El)

CM MASS

DAPDATR2

Roll command

WBODY (roll) or OMEGA C (roll)


WBODY (yaw) or OMEGA C

Desired FINAL CDU X

Desired FINAL CDU Z

Channel 12

Channel 14

Channel 3 1

Channel 33

Range for initialization

(yaw)

4-27

SD 68-723




PROGRAM 22 LIST

1

2

3

4

5

6

7

8

9

10

11

12

13

14

15

16

17

18

19

20

21

I.D. (77773g)

CSM state vector (R )-X.


CSM state vector (R)• £-1

CSM state vector (V ).A.


CSM state vector (V )Zj


Actual X CDU angle

Actual Z CDU angle

X attitude error

Z attitude error

MARKTIME for firstmark

INNER GIMBALANGLE

MIDDLE GIMBALANGLE

OUTER GIMBALANGLE

Synch bits (77340 )o

CSM state vector (R )Jv


CSM state vector (R )i

CSM state vector (V ).X,


CSM state vector (V )£-i


Actual Y CDU angle


Y attitude error

MARKTIME for first mark

SHAFT ANGLE

TRUNNION ANGLE

Most significant part of MARKTIME forsecond mark

4-28

SD 68-723




PROGRAM 22 LIST

22

23

24

25

26

27

28

29

30

31

32

33

34

35

36

37

38

Least significant partof MARKTIME forsecond mark

SHAFT ANGLE

TRUNNION ANGLE

MARKTIME for thirdmark

INNER GIMBALANGLE

MIDDLE GIMBALANGLE

OUTER GIMBALANGLE

Least significant partof MARKTIME forfourth mark

SHAFT ANGLE

TRUNNION ANGLE

MARKTIME for fifthmark

INNER GIMBALANGLE

MIDDLE GIMBALANGLE

OUTER GIMBALANGLE

LANDMARK

INNER GIMBAL ANGLE

MIDDLE GIMBAL ANGLE

OUTER GIMBAL ANGLE

MARKTIME for third mark

SHAFT ANGLE

TRUNNION ANGLE

Most significant part of MARKTIME forfourth mark

INNER GIMBAL ANGLE

MIDDLE GIMBAL ANGLE

OUTER GIMBAL ANGLE

MARKTIME for fifth mark

SHAFT ANGLE

TRUNNION ANGLE

4-29

SD 68-723




PROGRAM 22 LIST

39

40

41

42

43

44

45

46

47

48

49

50

51

52

53

54

55

56

57

58

59

60

61

Flag word 0

Flagword 2

Flag word 4

Flagword 6

Flagword 8

DSPTAB+0

DSPTAB+2

DSPTAB+4

DSPTAB+6

DSPTAB+8D

DSPTAB+10D

TIME 2

LANDMARKLATITUDE

LANDMARKLONGITUDE

LANDMARKALTITUDE

Actual X CDU angle

Actual Z CDU angle

-

Flagword 1

Flagword 3

Flagword 5

Flagword 7

Flagword 9

DSPTAB+1

DSPTAB+3

DSPTAB+5

DSPTAB+7

DSPTAB+9D

DSPTAB+1 ID

TIME 1

LANDMARK LATITUDE

LANDMARK LONGITUDE

LANDMARK ALTITUDE

Actual Y CDU angle


4-30

SD 68-723




PROGRAM 22 LIST

62

63

64

65

66

67

68

69

70

71

72

73

74

75

76

77

78

79

80

81

82

83

84

Optics shaft

No. of marks

Landing site vectorX comp.

Landing site vectorY comp.

Landing site vectorZ comp.

Landing site vector X comp.

Landing site vector Y comp.

Landing site vector Z comp.

4-31SD 68-723




PROGRAM 22 LIST

85

86

87

88

89

90

91

92

93

94

95

96

97

98

99

100

Channel 11

Channel 12

ChannelSO

Channel 32

Channel 12

Channel 14

Channel 31

Channel 33

4-32

SD 68-723


APPENDIX

REFERENCES

1. Mission Evaluation 101 - Study Analysis Report. SD 68-452(24 September 1968)

2. Mission Requirement - 'D' Type Mission - LM Evaluation and CombinedOperations. NASA MSC SPD 8-R-005 (8 April 1968, revised 1 July 1968)

3. Apollo Mission D (AS-503/CSM-103/LM-3) - Spacecraft Reference Tra-jectory Volume 1 - Nominal Trajectory. MSC Internal Note No. 68-FM-93(30 April 1968)

4. Apollo Operations Handbook - Command and Service Modules -Volume 2 - Operational Procedure^!SD 67-778, SM2A-03-SC103-(2)(1 August 1968)

5. CSM Rendezvous Procedures - D Mission Preliminary Copy. NASAMSC, (19 July 1968).

A-l

SD 68-723

Documents

MISSION EVALUATION PRESIMULATION REPORT … 68-723 MISSION EVALUATION PRESIMULATION REPORT Part 1: CSM 104 (Mission D) Operations Plan August 1968 Contract NAS9-150, SA 300, Exhibit