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Approved for public release; distribution isunlimited.
Distribution authorized to U.S. Gov't. agenciesonly; Test and Evaluation; JUN 1977. Otherrequests shall be referred to Air ForceArmament Lab., Eglin AFB, FL.
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•} MMp?gwy»w^!WP4WW«W'^
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.ii^.i'^-/" ' ■"■ ■■
i
AFATUTR-77-85 /
AN AERIAL GUNNERY AERODYNAMIC LEAD PURSUIT MODEL
THE DIVISION OF ENGINEERING RESEARCH LOUISIANA STATE UNIVERSITY • BATOK ROUGE , LOUISIANA 70803
JUNE 1977
FINAL REPORT FOR PERIOD JUNE 1976-JUNE 1977
Distribution limited to U. S. Government agencies only; this report documents test and evaluation; distribution limitation applied June 1977. Other requests for this document must be referred to the Air Force Armament Laboratory (DLYD), Eglin Air Force Base, Florida 32542.
AIR FORCE ARMAMENT LABORATORY AIR FOICI SYSTIMS COMMAND • UNIT» STATIS AIR PORCI
?.il-K;E^>i ■ / r. '.Mi, iitaUinUJi-.i
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2. GOVT ACCESSION NO.
'AN AERIAL GUNNERY AERODYNAMIC LEAD PURSUIT MODEL,
7. AUTMORf»)
£3: 9. PERFORMING ORGANIZATION NAME AND ADDRESS
The pivlrtwt of Engineering Research ^ ^Louisiana State Univoaity ^aton Rouge, Louisiana 70803
p" ft I. CONTROLLING OFFICE NAME AND ADDRESS
Air Force Armament Laboratory Armament Development and Test Center Eglin Air Force Base. Florida 32542
14. MONITORING AGENCY NAME i ADDRESSft/d/f/ersnt from Con(re/f/ru| Ofllee)
READ INSTRUCTIONS BEFORE COMPLETING FORM
3 PECIPIENT'S CATALOG NUMBER
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PERFORMING OR« REPORT NUMBER
CONTRACT OR GRANT NUMBERf«; / F|8635-76K >25-76-C^f273j
10. PROGRAM ELEMENT, PROJECT, TASK A"\ir If^TKuW'r NUMBERS JON: I 9134|07/-O3 ProgramTl^^nt 62602F
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16. DISTRIBUTION STATEMENT fof thi» Report;
Distribution limited to U. S. Government agencies only; this report documents test and evaluation; distribution limitation applied June 1977. Other requests for this document must be referred to the Air Force Armament Laboratory (DLYD), Eglin Air Force Base. Florida 325A2.
J '7. DISTRIBUTION STATEMENT (.at (he abstract entered tn Block 30, It different from Report;
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18. SUPPLEMENTARY NOTES
Available in DDC
19. KEY WORDS fContinue on reverse side if necessary and identify by block number)
Aerial Gunnery Aerodynamic Lead Pursuit Model
Uj JAN 3 19T8
JlissEircns E
20. ABSTRACT ^Continue on reverse side If necessary and Identify by block number; 7 A digital simulation of aerial gunnery was developed. A six-degree-of-freedom
attacking aircraft controlled by control surface deflections was implemented to perform aerodynamic lead pursuit of an evading target. The attacker is capable of flying within the bounds of its performance envelope. The target is a coordinated flight and aerodynamically constrained model capable of some evasive logic. Three sight systems have been Implemented into the simulation. The program was written in FORTRAN IV and has been checked out on the XDS Sigma 5, the IBM 360/65, and the CDC 6600 computers.
DD FORM 1 JAN 71 1473 EOITION OF I NOV 65 IS OBSOLETE SSIF
IFIOA'
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UNCLASSIFIED SeCUWITY CLASSIFICATION OF THIS PAOEfWiwi D»f Bnltnd)
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PREFACE
This report was prepared by the Division of Engineering Research, Louisiana State University, Baton Rouge, Louisiana 70803 under Contract F08635-76-C-0273, with the Air Force Armament Laboratory, Armament Development and Test Center, Eglin Air Force Base, Florida 325A2. This effort began in June 1976 and was completed in June 1977. Mr. Gerald Solomon (DLYD) monitored the program for the Armament Laboratory.
This technical report has been reviewed and is approved for publication.
FOR THE COMMANDER:
jj R. MURRAY // diief, Analysis Division
(The reverse of this page is blank.)
■
u1"111 ' i "l ^W^»P"
TABLE OF CONTENTS
Section
I
II
III.
Title Page
INTRODUCTION 1
Objectives 1
Literature Survey 1
Overview 1
ATTACKER SIMULATION 3
Purpose 3
Subprogram PILOT 3
Error Computation 3
Single Channel Controller 3
L*OD trO-L-L 61 IjOf^lC ••••••••••••••■••••••■■•••••••••••3
Total Controller 6
Aerodynamic Simulation 8
Data for the Attacker 10
TARGET EVASIVE MANEUVERS 17
Introduction 17
Target Maneuvers 17
Equation of Motion 18
Integration of Equations of Motion 19
Input Data to Define Maneuver Program 25
State Vector Indices 27
111
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„. .^T^^,,,,,,^^,^,^^,,,^
TABLE OF CONTENTS (CONCLUDED)
Section Title Page
IV SIGHT SYSTEM 31
Sight Modes 31
Sight Algorithm 1 31
Sight Algorithm 2 31
Sight Algorithm 3 32
Data Requirements 32
Data for the Sight Programs 32
V IMPLEMENTATION INTO GAMES 34
Games 34
Structure of GAMES 34
Pilot 34
CDC 6600 Runs 35
VI OVERVIEW OF INPUT FILE STRUCTURE 36
Initial Call to Pilot 36
Subsequent Re-runs 37
References 38
Appendix A - Program Listings and Sample Run 39
IV
-M..—***»*,*^*^.*,- iiiiimiiiniiinii mi, i
■-■■■■ " ■ ■ ■' ■-.■■ -. ■"■,: ■ ■ :■ : ■■
■MM
Figure
1
2
3
4
LIST OF FIGURES
Title Page
View Through Heads Up Display 4
Flow Chart of Controller Logic 7
Alrframe Simulation 14
Flow Diagram of ESCAPE 20
i
■
(The reverse of this page is blank)
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-
SECTION I
INTRODUCTION
OBJECTIVES
The design intent of the effort described by this report was the construction of a digital software simulation of an attacker-target encounter in aerial gunnery combat. The simulation was restricted in scope to the target tracking phase of the encounter with no particular attention being focused on tactical aspects. The primary effort was expended in obtaining an optimally controlled attacking aircraft capable of flying within the boundaries of its performance envelope, the emphasis being placed upon obtaining realistic aerodynamic lead pursuit in the tracking phase of the encounter. Complimentary to this effort were the simulation of the target and the sight systems and the overall problem of fitting the simulation into GAMES (Reference 1).
LITERATURE SURVEY
Consistent with the proposed work outline, a literature able simulations was made to determine the basic capabilities simulations (References 2 and 3). Based upon the requirement attacker be able to fly realistic uncoordinated flight in the the IMAGE simulation was the only viable candidate for the at simulation. The development of a totally new simulation was was deemed infeaslble within the time constraints allowed for Thus, the decision to extract from the IMAGE simulation the a and aerodynamics was made and Implemented.
survey of avall- of those that the tracking phase, tacker airframe considered but the project,
irframe dynamics
OVERVIEW
The overall effort was divided into four basic tasks: (1) Attacker airframe and pilot, (2) target simulation, (3) sight systems, and (4) implementation of tasks 1, 2, and 3 into GAMES.
Attacker Simulation
Section II of this report is devoted to the description of the attacker simulation. The attacker is a full six-degree-of-freedom airframe model with a zero time lag pilot and control system. All data defining the attacker is read in from the input file and defines a three control surface airframe. The aerodynamics data is stored in table form, and a table lookup scheme is used to extract information.
[■ifiirmmnifttirfMfdTinr- *■*-*********•****-**•* liMätdlit«a«lkMto»ka^^ ,. ^ ^
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I': ! Target Simulation
The target simulation Is described In detail In Section III of this report. The target Is a psuedo six-degree-of-freedom model In that coordinated flight Is assumed and attitude Is computed in a dependent fashion from the lineal velocity and acceleration. Acceleration Is computed as a demand quantity or as an input quantity based upon the type of maneuver specified.
Target maneuvers are defined by preprogramming a battery of sequentially activated maneuvers. Up to 10 steps or maneuvers may be programmed to define the target motion profile with the sequencing being influenced by what the attacker and target do. Tabular data Is also required to define the perform- ance envelope of the target.
Sight Systems
The sight systems have been Implemented in subroutine format, and first and second order perfect sights as well as mechanization of one other sight have been structured. Section IV of this report gives the details of the sight system implementation.
GAMES
The final product of the effort is documented in Section V of this report. The attacker-pilot, target, and sight systems are imbedded into the GAMES program as a subunit that updates the state vector for both attacker and target on demand from the executive part of the simulation. GAMES it- self has been minimally modified to accept this alternative to Its present approach to defining the engagement.
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SECTION II
ATTACKER
PURPOSE
The attacker simulation is a stx-degree-of-freedom digital model of an airframe and a controller. The controller simulates a pilot whose aim is to maneuver the attacking airframe into firing position. Firing position is achieved by nulling the tracking errors between the line of sight to the target and the pipper position in the heads up display (HUD) computed by the sight system.
SUBPROGRAM PILOT
Subprogram PILOT is an optimum controller for the airframe simulated in the subroutine TURKEY. The task of PILOT is to maneuver, by setting the control surfaces, the airframe into the best position for a successful aerial engagement with the target. All control decisions are made utilizing current information about the attacker and the target, i.e., PILOT does not have access to information concerning the future conditions of either the airframe or the target.
PILOT utilizes the fact that the most rapid means of minimizing the integral of the error is to use maximal rectilinear and angular accelerations and decelerations for the airframe. PILOT communicates to TURKEY by means of a control vector composed of aileron setting, stabilator setting, thrust or throttle control setting, and rudder setting. Therefore, the Individual components will, in general, be set at their limits while maneuvering to achieve near aerodynamic lead pursuit. Only in the final stages of the engagement, when the magnitude of the error and its first derivative is small, will the components of the control vector be at some intermediate value.
ERROR COMPUTATION
The error vector is composed of roll error, pitch error, range error, and yaw error. These quantities are computed from the elevation and traverse tracking errors and the range to the target (see Figure 1).
SINGLE CHANNEL CONTROLLER
PILOT uses four single channel controllers, each responsive to a single component of the error vector. Roll error controls the aileron deflections; pitch error controls the stabilator deflections. The thrust is controlled by the range error. Rudder deflections are controlled by the yaw error. In effect, the control vector is the sum of the output of each individual
Mmmgii^Msmii^^ ^ „^ ,
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Y i ■ Yaw i
-^ Error ^;rget
Plpper / Pitch Error
a i j / 1 «
y
f -/--I J-^-W Roll Error
!/
y Pseudo Zero of Head Up Display
.,
Figure 1, View Through Heads Up Display
— ^ - ■ ■ ^•-
_ , —— —.—r.— --. -. ■ ■ ■■ '— -' '
MiiiiMih
MIWWKWWipiftWiwwyB^^
controller. Each controller assumes that the other components of the control vector have a negligible effect on the error which it is trying to control.
CONTROLLER LOGIC
In PILOT each controller tries to minimize the integral of the error which it senses. This is accomplished by nulling the error and its first derivative as rapidly as possible. The controller treats the response of the airframe as an unknown transfer function. The controller, sensing the error and the first derivative of the error, is able to sample the range of second derivatives of the error by changing its respective component of the control vector. This enables the controller to choose an appropriate value for the control vector component.
The controller is at liberty to adjust its control parameter and is able to obtain a complete range of values for the second derivative of the error. In general, these will have extreme magnitudes when the control vector is at its limits.
Control Decision If the error at any time t be denoted by x, its first derivative Is denoted by x and its second derivative is denoted b> x. The controller has at its command all available values of x. The optimal choice will be. In general, between the maximal positive and the maximal negative values of x. These values are assumed to be constant over an interval in time. X- and x. is the error and its first derivative at the start of the time interval. x* is judiciously chosen as the second derivative which will improve the situation over the next time interval, t... x» and x. are the error and its first derivative at the end of the time interval tj^ and at the start of the second time interval t,.. x, is the second derivative of the error to be used during this second time interval, t, t. can be obtained from Equations (1) through TA)
The magnitudes of t, and
2 1/2 x" t- + x t, + x1 = x-
Vl + ^ = ^2
2 1/2 x2t2 + x2t2 + x2
x2t2 + x2 = 0
(1)
(2)
(3)
(4)
At the end of the second time interval, both the error and its first derivative will be zero if x* and *x'- were constant over the two time Intervals.
This method will give reasonable results, but it is more economical,
^Hk^^AtMmM^mmM..: ;~ l^«k^^,i)m*iiM^i^.:toi%^^^
since the simulation marches in time, to merely ask if the simulation has reached the end of the first interval. This is accomplished by assuming that the first interval is over and by using Equations (3) and (4) to evaluate the projected error at the end of the time interval t.« obtained from Equation (4).
-*2/x,,
is
(5)
Equation (5) is obtained from Equation (4) by the requirement that at the end of the interval t_ the derivative of the error should be zero. The projected error is then calculated.
If the projected error is sufficiently small, then the assumption that the end of t.. has been reached is correct. The component of the control vector is set such that the second derivative is x-.
If the magnitude of the projected error is greater than specified limits and if the value is of the same sign as the present value of the error, the end of the interval t. has not been reached. In this case the control vector should be set such that the second derivative is equal to x' .
However, if the projected error at t2 has the opposite sign of Its present value, then the airframe is predicted to overshoot the desired state. This means that the roles of x* and x' must be interchanged. The component of the control vector again should cause the second derivative of the state vector to equal the new x' .
.
The algorithm used in choosing the proper extreme second derivatives is shown in the flow chart in the Figure 2. The assumption that x* and x- are constant is permissible because they are updated, and the above test is made frequently.
TOTAL CONTROLLER
The assumption that other components of the control vector do not noticeably affect the error sensed by any individual controller is permissible because the errors and their respective derivatives are updated, and adjust- ments to the control vector are made frequently.
If the magnitude of the component of the error vector and the magnitude of the derivative of that error which a controller is sensing are sufficiently small, that component of the control vector is attenuated.
If the total error, pitch error plus the yaw error, is large, the rudder is not operational. However, if the error is sufficiently small, the rudder is used and the aileron deflections are set to zero.
^.^.■. ■■;,.^:^-..l. r.. . ■■*—~~~r,. ^-^V-^^^^j , .'■■:. ^ ■■ ^i :__ __^ 1_
^#^^-W^¥^^^ W'l^^.^W^pf^^ .Vim .^mv Kmj ^^^^i^^^^i^ j tij )|W
• • • • • R, R, R(l), R(2), J Are defined
a )
1 Assumes Most Positive R Rules
<^<f" |R| .LT. ep y=^
T .GT :"~ö:ö>^ | Switch K, Most negative governs j
R(l) * R(2) .GT. oTÖ^>
815
R£ t = Sign (R) (R + R * T + R * T * T / 2) future * v /
R * R(K) .GT. 0.0 ^—»■
R * R(K) .GT. 0.0
Figure 2. Flow Chart of Controller Logic
^wwwgwwapwpffl«^^ .- 5---—~" ■ -' ■■^T.....;..,..
Aerodynamic Simulation Subproeram TURKEY
The airframe subprogram is a generalized six-degree-of-freadom simula- tion. This subprogram is based on the airframe subprogram in IMAGE (Improved Model for Aerial Gunnery Effectiveness). This program was rewritten for the sake of economy and to allow the calling program to efficiently obtain the derivatives of the state vector of the airframe for various configurations of the control vector. This subprogram simulates the airframe rectilinear and angular accelerations and the wind angle and euler angle rates.
The forward acceleration and the wind angle rates of the airframe are calculated in the reference frame of the wind by the equations:
v = cos 0 [T cos (a + 6 ) - q SCj /m + q S sin ß C /m - g sin Y (6)
ß - sin ß [-T cos (a + 6 ) + q SC- 1/mv + q S cos ß] C /mv
+ g [cos a sin ß sin 6 + cos ß cos 9 sin <t) - sin a sin ß cos 9 cos <|)]/v
+ (P sin a - R cos a) (7)
a = [- T sin (a + 6 ) - q SC + mg (sin a sin 9 + cos a cos 9 cos 4»)]/
(rav cos ß) + [Q - R sin a tan ß - P cos a tan ß] (8)
The flight path angle, y, is defined by the equation:
Y • ARSIN (-sin <|» cos 9 sin ß - cos ß sin o cos 9 cos ((i + cos a cos ß sin 9) (9)
The transformation relating the wind axis coordinate system to the body axis coordinate system is defined as:
TWB
cos a cos ß -cos a sin ß sin a
sin ß cos ß 0
sin a cos ß -sin a sin ß -cos a
The angular accelerations and euler angle rates are calculated In the body axis coordinated system by the equations:
lil
^^^liii161^^ M<mm
w*pmw«.ww/w«pjwp'w^^ Mtmmjmmm
i
I - I
i XX
I - I
p = _2)L zi QR + _2Lz (R + PQ) + 1^ [cos g cos a öä . 8in a cn] (10) XX XX XX
Q = _5i^ xx Rp + .J« (R2 _ p?) + Sac c + M T/! ^ I I I m t yy
yy yy yy
XX j S PQ + Y^- [P - QR] + ^ [cos ß sin a C^ + cos a Cn] zz zz zz
= P + i^ sin 0
6 = Q cos (J) - R sin (|)
t|) = (R cos <|» + Q sin (j))/ cos 0
(ID
(12)
(13)
(U)
(15)
The transformation relating the body axis coordinate system to the Inertlal coordinate system Is defined as:
TBE =
cos 4/ cos 0
cos $ sin 0 sin $ - sin t|» cos <()
cos \\i sin 0 cos (f) _+ sin ^ sin 4»
sin iji cos 0
sin tj; sin 0 sin 4» + cos ty cos ()>
sin \\i sin 0 cos ip -cos i// sin ((>
-sin 6
cos 0 sin (|)
cos 0 cos $
The rectilinear velocities and accelerations in the Inertlal reference frame are obtained by the transformation of the velocity vector and its derivative from the wind axis coordinate system into the inertlal reference frame.
v = FT ITT Iv E L EBJl WBJ w where v = w
^E = AE = ITEB]fTWB]vw + tTEB][TWB]vw + [TEB][TWB]\
(16)
(17)
(18)
where
~.-— »« HUI ■ ■.■^■-^--■' '■- iim.1 ■- »~r~~—"—'-■■ ' ■ ■—rr ^—'i ""—-".w:.
la^lt^ai^afli
■s^^-w^^'T^w«^^
— [T 1 dt l WBJ
-sin a cosß a -cos o sin 08
co833
cos a cos ßa, -sin a sin 3ß
-sin a slnß ä +cos a cos ßß
-sin ßß
-cos a sin ßa -sin a cos ßß
cosa a
+sln aa
and
0 -R +Q
Tt "BE" ■ 'W +R 0 -P
--Q +P 0
The airframe simulation subprogram is constructed so that the recalculation of the derivative of the state vector is done efficiently for various control vectors. The majority of the calculations not involving the control vector are saved in dummy variables. Figure 3 is a flow diagram of the airframe simulation.
Data for the Attacker The data to describe the attacker is read by subprograms PILOT and TURKEY. In the read sequence PILOT reads first, then calls ESCAPE which then reads Its data to describe the target. ESCAPE is described in Section III of this report. Subsequent to ESCAPE reading data, the SSIGHT subprogram reads data as defined in Section IV of this report. Finally TURKEY reads data to define the airframe.
Data Read by PILOT PILOT reads a minimal amount of data ~ only that necessary to define the integration, control, print out, and initial conditions of the attacker.
CARD
1 2,3,4
FORMAT QUANTITIES READ
(AID, 215, E10.2) LABEL, NF1, NF9, DTIME (A10,7E10.2)/10X,7E10.2) LABEL, (SV(I),I=1,15)
The quantities read from the four cards are:
LABEL
NF1
Any identifying label up to 10 characters long.
Control frequency indicator. Sets the number of integration steps between control cycles.
.. -. ..J.J.^.-..^.........^ ;.,.
T '■■■■'" l^"^J™^^?^^^'^'^''^1V';^;V^^';' ■■■'■■■■' ^^-.—^rv;-'-:.-^^^w^^.i^jirmw:w^ww..wm?^ -■■^wwmw^MWMwmm^
NF9
DTIME
SV(1)
SV(2)
SV(3)
SV(A)
SV(5)
SV(6)
SV(7)
SV(8)
SV(9)
SV(10)
SV(ll)
SV(12)
SV(13)
SV(U)
SV(15)
Print out indicator. Sets the number of control cycles between printout by PILOT.
The integration step size to be used by the Runge-Kutta integration algorithm.
X1 position of attacker
X- position of attacker
X, position of attacker
X,
(X* + x* + **)*
Roll Euler Angle, 0
Pitch Euler Angle, 6
Heading Euler Angle, f
Angle of Attack, ct
Side Slip Angle, ß
Angular Velocity, Roll Axis
Angular Velocity, Pitch Axis
Angular Velocity, Yaw Axis
Data Read by TURKEY All of the aerodynamic performance tables used by TURKEY to simulate the airframe are read on the first call to TURKEY. Four separate reads are involved for the four COMMON arrays: IDUM1, TDUM1, TDUM2, and DUM. IDUM1, TDUM1, TDUM2, and DUM are only read once. The read sequence is IDUM1, TDUM1, TDUM2, and then DUM. IDUMl is integer, and contains 131 integers that describe the data made up of TDUM1 and TDUM2. TDUM1 and TDUM2 store REAL data and have 550 and 4700 words, respectively. IDUMl, TDUM1, and TDUM2 are punched into cards by the data input program from the modified IMAGE program described by Reference 5.
Array DUM contains the following data:
11
Ut^, ...—^»..^^-g^^^p.^^ **^*. ftuute
DUM
1
2
3
5
6
7
13
16
19
20
21
22
23
24
25
DATA
Angular orientation of the thrust vector
Wing surface area
Wing span
Mass of airframe, slugs
Acceleration of gravity
Mean aerodynamic chord length
2 Moment of inertia XX, slug ft
2 Moment of inertia YY, slug ft
2 Moment of inertia ZZ, slug ft
2 Product of inertia XZ, slug ft
Angle of wing with respect to body
Moment arm of thrust vector
Rudder upper limit, degrees
Rudder lower limit, degrees
Stabilator upper limit, degrees
Stabilator lower limit, degrees
Aeleron upper limit, degrees
Aeleron low6r limit, degrees
Thrust value 1, pounds
Thrust value 2, pounds
Thrust value 3, pounds
Thrust value 4, pounds
Maximum angle of attack, degrees
Maximum side slip, degrees
Maximum normal acceleration, G's.
12
mmmmmmimämM aag&m
r i.i i JBI|ltl||ipwuHl|Jll,JIIJIU.,|i,.l.ll,ll|ll.|l,ll III, lipjljpilipi wrnmr-' '—'■—■'■•i- " ."'.•..."■M.i.i., li:iWXiptWpK|iipi||Vipii||RH,jm „„,..,i,ii.uiiWpip
I
: !
DUM is read under a FORMAT of (8E10.2). Subsequent to the initial read of DUM, selected parts of DUM are re-read for each initialization of a new case, including the first. The re-read uses the same format, and the quantities re-read are DUM(A), DUM(7), DUM(8), DUM(9), DUM(IO), which
are the inertia parameters.
13
'Vr-wmmMnirin w iumMiifrrii I nw friiiliiiiritiftma«^ -^ mm
i"11 mmm^^mmmmmmm
Read Data Defining
Airframe Dynamics
I Transform Degrees to
Radians In DUM
1000W
^JTRY. LT. -l\
Read Inertias
Set Control Vector
to Lower Limits
( Return j
(1100^»--
Set Control Vector to
Upper Limits
J
Calculate Body to
Earth Transformation
TBE
I Calculate Wind to
Body Transformation
TWB
{
(wo)
Calculate Wind to
Earth Transformation
TWE • TBE*TWB
NTRY .EQ.oN-
Make Table Look up
for Aerodynamic Coef-
ficients
(jSo) Figure 3. Airframe Simulation
14
•' if iiiiiMiMiiiMiiiiM laiHfiiiiiifiiidraMniimi ;tMa'iifa«^Jii!i!äli^
^■■.—„^■.■■■"-■■.II™.. I „ y ||Jj!l||||ll|||l|!||[|ll||[||||||||,UtJ|jJjp|||CTCT> f (2ÜJÖ)
Calculate all Simulation Terms
That do not Depend Upon Control
Surface Deflections
.W Return
NTRY.EQ.2 J
Set Control Surface Deflections
Calculate VD from Summation
of Forces In the Direction of the
Velocity of the Aircraft
I Calculate Rate of Change of Angle
of Attack from Sum of Forces in Wind
Axes Vertical Direction
I Calculate Rate of Change of Side
Slip Angle from Sum of Forces in
Wind Axes Horizontal Direction
Figure 3. Airframe Simulation (Continued)
15
At^aMtaMM^^^^g^iii! |rr1| j
■i--''r^f-,':",'V'!""-""".iI ■ i **wml''■mv>^^wfmm.mml'•.l ■»^■^■p^^^^^^^» BH^POBI
i Calculate Angular Accelerations from
Sums of Moments about Body Axes
I
SL
Calculate Lineal Accelerations from
VD, Angle of Attack Rate, and Side Slip
Rate. Set Derivative of State Vector
Set Rotation Acceleration Matrix
Truncate Acceleration if Needed
(4003)
( Return 1
Figure 3. Airframe Simulation (Concluded)
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SECTION III
TARGET EVASIVE MANEUVERS
INTRODUCTION
Subroutine ESCAPE was written to simulate the motion and decision of the target aircraft. The target defined by ESCAPE Is a slx-degree-of- freedom aircraft with realistic aerodynamic characteristics. Basically, the target files coordinated flight along a flight trajectory that has been predetermined In a generalized fashion by the Input data.
Within the target simulation, note Is made of the state of both target and attacker, and the target makes evasive decisions based upon those states and bounds established by the Input data. A serial decision sequence with no branching Is defined such that at each decision point the simulation decides to either continue with the presently defined maneuver or to proceed to the next maneuver in the program stack of maneuvers. If the target completely exhausts the program stack of maneuvers. It simply vanishes by exiting to infinity.
Within the above concept, the analyst is able to program the target to the extent of defining the sequence of maneuvers in the program stack and defining the attacker/target state vector limits that dictate the termination of each step of the target program. There are seven basic maneuvers defined for the analyst to use to program the target. These are described below. Any component of the target or attacker statt vector may be used as an upper or lower operating limit for each step of the program. A detailed listing of the index numbers of the state vector components is also given below.
TARGET MANEUVERS
Target maneuvers are designated by their index number, IZG, with Integer value 1 through 7. The following gives a detail description of each maneuver:
IZG Maneuver
Fly toward a specified point in space making changes in direction at a specified acceleration. This maneuver can be used to cause the target to fly a straight and level course as well as a circle in some circumstances.
17
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IZG
2
Maneuver
Fly toward a point specified In space as an Increment away from the target's position at the beginning of this maneuver. This maneuver becomes maneuver 1 after the new point Is defined.
Fly toward a moving point a specified Increment away from the target using a specified acceleration. This maneuver differs from 1 only In that the point always moves with the attacker. In the limit, this maneuver will result In a target velocity vector In the direction of the Incremental position vector.
Change the direction of the target velocity vector to a new specified direction In a specified amount of time.
Make an incremental change in velocity vector direction where the Increment is specified and the time to change is specified.
Chase an Incremental change in velocity direction. The change is a constant, and the limiting velocity is parallel to the change vector.
Fly with a specified roll angle and normal acceleration. A linear function of time may be specified as the roll program for this maneuver.
EQUATIONS OF MOTION
For IZG =1, 2, 3 the target is attempting a change in position. Over an Interval of time. At, a change in position, AX, would be accomplished with constant kinematic acceleration according to
AX = 1/2 AvAt2 or A= -^
-K IC At2
where AX and A^. are both vectors in the earth system.
The sensible acceleration would then be given by
AS = ^ + G
(19)
(20)
18
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where AQ and G are vectors, and specifically G is the vector repreoentation of the acceleration of gravity.
The target is assumed to have small angle of attack so that the normal acceleration is considered normal to the wind or the target velocity vector. As such, the normal direction, N, is defined by the vector product (V x A-) x V where V is the velocity vector for the target. To achieve an acceleration of A- then requires a normal acceleration. A.,, given by
AN = AS.N (21)
In the event that the calculated normal acceleration is in excess of the maximum allowed, the normal component of acceleration is truncated and the normal direction maintained.
The tangential component of acceleration is calculated by
A^, = AS-V/|V| (22)
where V is the vector velocicy of the target and |v| is the scalar speed of the target. If this acceleration is not within the performance limits, it is truncated and the simulation continued.
For IZG ■ 4, 5, 6, the acceleration is computed for a change in target velocity rather than a change in target position. To this end
A mH **. At
(23)
where AV is the vector change in velocity to occur over At change in time. The same analysis and constraints for A„ and A- are used in cases 4, 5, and 6 as were used in cases 1, 2, and 3.
IZG =• 7 is essentially a maneuver where the roll angle, and therefore N, is specified as a control. AN is specified rather than being calculated, A_ is specified by means of throttle setting. Using A-, AN, and the roll angle, the kinematic acceleration is established and the motion of the target set.
INTEGRATION OF EQUATIONS OF MOTION
In all maneuver cases a program of acceleration is established for a small interval of time. The equation'for velocity then becomes
V(t) - v(t0) + Ag^Xt-^) (24)
and for the displacement
19
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yes First Call?
Initialize
TAAF, FAN, FAVD j
^>
Read JMX
3
:> ^/jMX.EO.r x T Use 01d "N
Manuever
Read Data to Define New
Manuever Program
/Read Starting Point,
Initialize
..-'
Calculate New
Position, Velocity
for Target
315
i Calculate Wind
Axes Transformation
Unit Vectors
Matrix TUV
£.
EL
Calculate Body Axes
Transformation from Angle of Attack
RTUV
l
345
Figure 4. Flow Diagram of ESCAPE
20
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i Calculate Euler Angles
I NTRY.GT.
>
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Pass
Pass
Save Target Vector
1 Test State Vector\
gainst Lower Limits)
Fall
Test State Vector
iAgainst Upper Limits
Fall
Increment MNVR
I £
■/MNVR.GT.NMNVRS \.
Zero KIK
I Load Manuever Vectors
From Program Arrays
Inltlllze IZG
I
Return
-^
900
Figure 4. Flow Diagram of ESCAPE (Continued)
21.
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Target State Vector Add F to Target
Old State Vector
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Figure 4. Flow Diagram of ESCAPE (Continued)
22
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Calculate Acceleration
Based on Incremental
Position
,.
<580>»-
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Calculate Acceleration
Based on Increaental
Velocity
J
Calculate Wind Axes
Unit Vectors ^-—^KlK.NE.o\
Calculate Roll Rates
C^> Calculate Roll Angle
I Calculate Wind Aces
Transformation TUV
I Set Normal Acceleration AN
Get ^ from FAVD
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Figure A. Flow Diagram of ESCAPE (Continued) 23
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Get Max Normal Acceleration
From FAN
Truncate AN If Heeded
Get MAX V From FAVD
Truncate AV if Needed
I Calculate Sensible Acceleration
^610 3 From AN and AV
Calculate Kinematic Acceleration
KIK =» KIK +1
I (Return )
Set Position and Velocity to
Large Values, Null Remainder
of State Vector, Print Message
f Return j
Figure 4. Flow Diagram of ESCAPE (Concluded)
24
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x(t) = x(to) + ^(t^-^-
In use, the maximum value that t-t will normally attain is 0.1
(25)
second, ^(t ) is repeatedly updated as the simulation proceeds and, for V >, wh instance, when IZG = 1, a feedback loop is established and the acceleration
A^-Ct ) and time t are continually being updated based on the present posi?ion of the target. Figure 4 is a flow diagram of the logic of ESCAPE.
INPUT DATA TO DEFINE A MANEUVER PROGRAM
Card No. Format Data
1. A6, 14
2. A6, 14, 5E10.2
3. A6, 14, 4(15,E10.2) /(10x4(I5,E10.2))
4. A6, 14, 4(15, E10.2)
/(10x4(I5,E10.2))
Card title, number of maneuvers in motion program. Maximum number of maneuvers is 10.
Card title, maneuvers index, maneuver parameters. Maneuver parameters vary with index.
Card title, number of lower limits, sequence of (state vector index, lower limit value) pairs. State vector indices are defined below. Maximum number of limits is 10.
Card title, number of upper limits, sequence of (state vector index, upper limit value) pairs. State vector indices are defined below. Maximum number of limits is 10.
Cards 2, 3, and 4 are repeated in sequence for each maneuver in the program.
5. A6, 14, 6E10.2 Card title, starting maneuver index less 1, initial conditions of target, x1, x_, x», V-, V?, V». The simulation
uses X- down.
Card sequence [1, (2, 3, 4), (2, 3, 4), (2, 3, 4)] may be repeated for additional runs of the target. The minimum number of cards in a data sequence is 5.
MANEUVER PARAMETERS
There are five maneuver parameters read from each No. 2 card, and
25
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the role played by each parameter depends upon the maneuver being defined. In all cases parameter 5 Is the throttle setting. Negative values for IZG Indicate that the parameters are defined in the target wind coordinate system.
IZG 1, or -1
IZG = 2, or -2
IZG = 3, or -3
IZG = 4, or -4
IZG ■ 5, or -5
IZG = 6, or -6
IZG = 7
Parameter 1, 2, and 3 designate a point in space x-, x_, and x_ toward which the
target will fly. Parameter 4 is the time allowed for the maneuver.
Parameters 1, 2, and 3 locate a point in space an increment Ax.., Ax», Ax» away
from the Initialization of this maneuver. The target will try to fly to this point in the amount of time given by parameter 4.
Parameters 1, 2, and 3 locate a moving point that in the limit leads the target parallel to Ax.., Ax_, Ax. specified by
the parameters. Again parameter 4 is the time allotted to perform the maneuver. In effect, a constant acceleration is specified.
■
Parameters 1, 2, and 3 define a velocity vector that the target will attempt to achieve in parameter 4 number of seconds.
Parameters 1, 2, and 3 define an incremental velocity vector that will be added to the present velocity over para- meter 4 seconds.
Parameters 1, 2, and 3 define an incre- mental velocity that is used with para- meter 4 to define a constant acceleration. This case is essentially the same as IZG = 3 except velocity rather than displace- ment Is used to define acceleration.
Parameter 1 is the initial roll angle in degrees. Parameter 2 is the roll rate In degrees if parameter 4 is zero. If parameter 4 is not zero, the roll rate is computed as (parameter 2 minus parameter 1)/parameter 4. Parameter 3 is the specified normal acceleration in g's. Tangential acceleration Is controlled by parameter 5 as a throttle setting. Para- meter 5 has values between 0. and 1.0.
26
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STATE VECTOR INDICES
As described in the data and programming subsection, the target motion program steps up to the next maneuver in the sequence whenever a lower or upper limit is violated. A maximum of 10 upper and 10 lower limits is allowed per maneuver. At least one upper and one lower limit must be specified. The state vector quantity desired as a maneuver trigger is specified by state vector component index. The following list of indices must be used when formulating the limit control cards:
State Vector Quantity
Simulation time
Attacker x.. position
Attacker x- position
Attacker x,. position
Target x.. position
Target x- position
Target x- position
Range, attacker to target
Attacker velocity V.
Attacker velocity V»
Attacker velocity V-
Attacker speed
Target velocity V.,
Target velocity V-
Target velocity V-
Target speed
Closing rate, attacker to target
Attacker roll angle $
Attacker pitch angle 9
Attacker heading angle 4"
Index
1
2
3
4
32
33
34
31
5
6
7
8
35
36
37
38
56
9
10
11
27
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Target roll angle <|) 46
Target pitch angle 6 45
Target heading angle 4* 44
Angle off, attacker to target 57
Target normal acceleration (lift) 42
Target tangential acceleration (drag),
(thrust) 43
ADDITIONAL DATA
In addition to the target motion program control data described above, the target simulation requires tables of performance data. Specifically, four tables of data are required so that the aerodynamic performance of the target may be realistically constrained.
Maximum Normal Acceleration A two-dimensional table of maximum normal acceleration in feet/second^ versus mach number and altitude is required. This table gives the maximum available normal acceleration as a function of the target's mach number and altitutde. It is used to make sure that the target does not outperform its capabilities. This table is described by the ordinate data arranged to vary with mach number most rapidly (down the columns) and the two abscissa arrays, mach number and altitude in feet. Formats for all are (10x7E10.2), with read order of mach vector, altitude vector, and then table.
Maximum Thrust To simulate the speed characteristics of the target properly, a table of maximum available thrust versus mach number and altitude is needed. Thrust in feet/second2 is used with throttle position to control the tangential 7, acceleration of the target. This table is also two-dimens- ional with mach number as the column variable and altitude as the row variable, The formats are also (10x,7E10.2), with reading in the order mach vector, altitude vector, then table.
Drag Drag coefficient as a function of normal acceleration, mach number, and altitude is required in a three-dimensional format. The table defines a volume with each vertical slice defining a two-dimensional table. In the two-dimensional table the data varies down the columns with normal acceleration and from column to column with mach number. Each two-dimen- sional table is associated with an altitude. The read details are a format
28
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of (10x7E10.2) and read sequence is normal acceleration vector, mach vector, altitude vector, and then table.
Angle of Attack The target simulation does not need the angle of attack for aerodynamic purposes. However, the actual attitude of the target with respect to the wind axes may affect the evaluation of a gun system. For this reason the target angle of attack is used to complete the attitudinal picture. For this purpose, angle of attack is considered a function of normal acceleration, mach number, and altitude. A three-dimensional table is used with column-wise organization with respect to varying normal acceleration, row-wise organization with respect to increasing mach number, and slice-wise organization with respect to increasing altitude.
ANCILLARY PROGRAMS
The target simulation uses three ancillary programs to do the data reading and table look up for the normal acceleration, thrust, drag and angle of attack. These programs are described briefly In the following paragraphs.
Function FAN handles the data manipulation used to describe the maximum normal acceleration available as a function of mach number and altitude. Upon the first call to FAN, data describing a table of normal acceleration versus mach number and altitude is read and stored. In the read sequence, the reference values for the mach number are read first and stored in array AM in ascending order according to magnitude. Next the reference values for the altitude in feet are read and stored in the array AH according to ascending Index and magnitude. Finally the tabular values for normal acceleration in feet per second are read and stored in FMH. FMH is assumed to be structured as a two-dimensional array with the column entries indexed to the mach number array and the row entries indexed to the altitude array. Each data card has the first ten columns reserved for a label which is read and pointed via LABEL. The presently Implemented program has three
data entries in AM and AH and nine entries in FMH. Variables NM and NH indicate that the data is 3X3.
On calls subsequent to the initial call, a value for the normal acceleration, FAN, is calculated by the two variable table look-up program L00K2 using VM and H as input values for mach number and altitude.
Function FAVD controls the data and calculations needed to obtain the maximum available tangential, or V, acceleration. On the first call to FAVD data is read and stored that defines two tables; One for maximum available thrust as a function of mach number and altitude, and one for drag- to-lift ratio as a function of normal acceleration, mach number and altitude.
29
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The read sequence first reads the reference values of normal accele- ration in ft /S^ and stores them in the array AAN. Next reference values for the mach number are read and stored in array AM. The third read fills the array AH with the reference values of the altitude in feet. In the fourth read the tabular values of the maximum available thrust are read into array TRST in a two-dimensional array format. Row-wise organization is indexed according to the reference values stored in AM, the mach number, and column-wise organization is indexed according to the values stored in AH, altitude.
The fifth read ingests and stores the table of drag ratios into array DRG. These are nondimensional ratios of the drag to lift at the various normal acceleration (lift), mach number, and altitude reference points stored in AAN, AM, and AH,respectively. The array DRG varies most rapidly with normal acceleration (row-wise organization), next most rapidly with mach number (column-wise organization) and least rapidly with altitude (slice-wise variation). DRG is structured as a three-dimensional array with first subscript associated with altitude. Again the first 10 columns of the data cards are reserved for LABEL to be used strictly as a label.
On subsequent calls to FAVID, AN, VM and H are used by LOOK3 to look up and interpolate a value for DRAG, and VM#and H are used by L00K2 to look up and interpolate a value for THRST. The V acceleration for the target is calculated as
FAVD = THRST * TP - DRAG * AN
where 0. £ TP £ 1. and TP is the throttle position variable.
NA, NM, and NH show that the implemented program expects a 3 X 3 TRST and a 3 X 3 X 3 DRG.
Function TAAF is used to read and control the data for the definition of the target angle of attack. The angle of attack is considered as a function of three variables: normal acceleration, mach number, and altitude.
Upon the first call to TAAF the following read and store sequence is _ activated: first reference values for target normal acceleration in ft /S are read and stored in array TAN; second reference values for mach number are read and stored in array TM; third reference values for altitude in feet are read and stored in array TH; and finally the three-dimensional table of angle of attack in degrees is read and stored in TAA. The assumed organi- zation of TAA is that of a three-subscripted array with the first index linked to the values in TAN, the second index linked to the values in TM, and the third index linked to the reference values in TH. Each data card has the first 10 columns reserved for a label which is read and printed from LABEL. The expected data organization for the implemented program is 3 X 3 X 3 as indicated by NA, NM and NH.
On subsequent calls L00K3 uses normal acceleration, AN, mach number, VM, and altitude, H, to look up and interpolate a value for angle of attack TAAF.
30
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SECTION IV
SIGHT SYSTEM
SIGHT MODES
Three basic sight modes were adapted for implementation in the lead pursuit model: (1) A perfect first order prediction using the basic methodology present in GAMES (Reference 1); (2) a second order modification of the linear prediction model; and (3) an existing sight simulation. Modes (1) and (2) are perfect systems in that they assume position, velocity, and accelerations of the target are all known and available. Mode (3) is the disturbed-reticle sight supplied by AFATL personnel (AFAL-TR-75-52).
SIGHT ALGORITHM 1
In the first algorithm, the perfect first order prediction, the time of flight, and range are determined using the iterative procedure described in GAMES (Reference 1). The relative position, relative velocity, and acceleration vectors in the inertial system are calculated from
P , = P - P rel targ att
V = V - V rel targ att
(26)
The initializing range is taken as the present range from attacker to target.
The projectile average velocity is calculated as was done in GAMES using the appropriate projectile drag coefficients from subroutine DRAG (in GAMES). From these, a time of flight is calculated and used to calculate a new range. This procedure is repeated until the change in range is sufficiently small. The final range and time of flight values are used with attacker position and velocity vectors and gun information (muzzle velocity and position) to calculate the future position of the projectile one time of flight in the future. The proper pipper position is then calculated by backing up from the projectile future position an amount and in a direction determined from the target velocity and position.
SIGHT ALGORITHM 2
The second order approximation is accomplished by the addition of acceleration terms during calculation of both target and attacker positions after one time of flight. Otherwise, the algorithm is exactly the same as algorithm 1. In fact, the second order algorithm is imbedded in the linear prediction model and controlled by a flag.
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The entire first and second order algorithm was extracted from GAMES, modified and installed in a separate subroutine called SSIGhT. Information describing the gun is transmitted through common block GUN while encounter data is transmitted through common block STATE.
SIGHT ALGORITHM 3
Subroutine SIGHT contains the disturbed-reticle sight algorithm. This routine was taken from technical report AFAL-TR-75-52 (Reference 4) and modified to accept encounter information externally through common STATE. The algorithm presented in Reference 4 assumed a particular encounter geometry and contained a loop which carried out the encounter. The modified routine uses the attacker information available in STATE, and makes one pass using the lead angles calculated from the previous pass through the algorithm and stored. The routine does not utilize the target information available in STATE. Thus, the algorithm assumes no target information is available and positions the pipper to indicate the position in the HUD of the Impact point of a projectile fired one time of flight prior.
DATA REQUIREMENTS
The general data requirements are that, in the event that sight para- meters are not fixed, they will be read in upon the first call to the sight program. This means that the subprogram writer will have to include logic in the sight program to recognize the first call. Further, some sight systems
may require some standard initialization whenever a new case Is begun. This report contains three implementations that can serve as examples for the programmer.
The first order sight requires a minimum amount of data. The gun muzzle velocity and the gun angle are the only data needed for'the first order sight.
The second order sight is imbedded within the same program as the first order sight and consequently its data is taken care of by that program.
The disturbed reticle sight program SGHT is an example of a mechanization of a sight system. It is Included as the third option for this attacker- target simulation. For this program, the program listing provides the best display of the needed information. For a different sight, this program would be rewritten and subroutine SGHT mi^ht read different data entirely, although there would be obvious similarities.
DATA FOR THE SIGHT PROGRAMS
Upon the first call to SSIGHT in ehe initialization phase of each new engagement, data defining the sight system is read and stored. There is one
-...-.-. —■-iillii[IMIali
READ command using the FORMAT (A6,IA,7E10.2). The following quantities are read from one card in the card in the card input file:
LABEL
IORD
VELMUZ
GUNALP
GHR
DA
DE
HALF
SIC
a six character identifier,
order of sight system.
IORD = 1 = first order perfect.
IORD = 2 " second order perfect.
IORD = 3 = sight Implemented in
subprogram SGHT.
muzzle velocity, feet per second
gun angle, degrees,
gun harmonization range, feet,
location of gun in azimuth direction
from HUD, feet,
location of gun in elevation direction
from HUD, feet.
HUD angular displacement from airframe
longitudinal axis, degrees.
Sight system damping factor.
33
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SECTION V
IMPLEMENTATION INTO GAMES
GAMES
The Joint Technical Coordinating Group (JTCG) guns study program GAMES is essentially a design program for aerial gunnery systems whereby the effects of gun system parameters can be studied. The effective procedure of using the program is to set the gun system parameters and then evaluate their effectiveness by running a spectrum of engagements. The relevance of this concept to the present effort is that provision had to be made for a sequence of initial conditions and engagement descriptors to be read in by the simulation.
STRUCTURE OF GAMES
The structure of the GAMES program was not violated by the present effort. In fact, the program resulting from the inclusion of aerodynamic lead pursuit into GAMES still has all of the features and capabilities of the original version. This was accomplished by taking advantage of the fact that GAMES was written to be able to receive flight path data for both target and attacker from an outside source. The present attacker and target modelling program simply becomes another outside source of data. In this manner, GAMES itself was only modified to the extent of a third read option, a call to PILOT, and a few branches to take advantage of the fact that the new simulation produces more data than before.
PILOT
Subroutine PILOT has been explained in some detail in Section II of this report, especially with respect to the control algorithm aspects. PILOT as a subprogram also has executive duties. It must make appropriate initiation reads when a new case is started as well as initiation calls to TURKEY ESCAPE and SSIGHT. It also must envoke ESCAPE and SSIGHT after an integration of the equation of motion has been made and a reference state reached.
As indicated above, reinitialization is needed each time GAMES goes on to its next case. This is accomplished by calling PILOT with time set to zero. Upon this call PILOT calls the other programs in the attacker-target simulation with the initialization flag set, as well as reading its own initialization data.
For regular calls, time greater than zero, the PILOT program is first called and after integration of the simulation by PILOT, a call to ESCAPE is with the reference point flag set.
34
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Subroutine PILOT is a slave to the main program of GAMES and does not have the capability of terminating the simulation. A listing of the main program of GAMES is included in the appendix along with PILOT and the other
programs used in the simulation.
CDC 6600 RUNS
The modified GAMES program was implemented on the Eglin AFB CDC 6600 digital computer system. Test cases using engagements and data supplied by DLYD were run. Sample output from the simulation is included in the appendix
to this report.
35
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SECTION VI
OVERVIEW OF INPUT FILE STRUCTURE
INITIAL CALL TO PILOT
Upon the first call to PILOT with zero argument, a sequence of reads is initiated. The structure of the input file must be consistent with this sequence of reads. The basic initial sequence is as follows.
PILOT
Integration and prints out parameters and attacker initial conditions as described in Section II. Requires 4 cards.
ESCAPE
Data as described in detail in Section III. Upon the initialization of ESCAPE as now written a minimum of 25 cards will be read.
SSIGHT
Each time PILOT is called with zero argument SSIGHT will read one card as described in Section IV.
TURKEY
Upon the initial call to PILOT, all of the tabular data described in the IMAGE (Reference 1) program will be read. The card file must contain the following data sequences'.
IDUM1
TDUM1
TDUM2
DUM
Integer data totaling 7 cards.
Real data totaling 69 cards.
Real data totaling 588 cards.
Real data totaling 4 cards.
Additions to DUM totaling 1 card
Total Cards on Initial Read
The above described card files give a minimum card set of 699 cards to be read as the initial data.
36
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SUBSEQUENT RE-RUNS
Should reinitialization of the simulation be required, a call to PILOT with zero for argument will cause reinitialization of the programs. A much reduced data file is required as follows:
PILOT
ESCAPE
SSIGHT
TURKEY
3 cards, initial conditions only.
2 cards minimum (see Section III).
1 card
1 card, update on DUM only.
37
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1 REFERENCES
1. Solomon, G., Caluda, M. J., Gunnery Analysis. Modular Effectiveness Simulation (GAMES) AFATL-TR-75-118, September, 1975.
2. Berger, J. B. , M. Meyers, R. R. Wallace, Improved Model for Aerial Gunnery Effectiveness. AFATL-TR-68-112, September, 1968.
3. Whitehouse, G. D. , A. J. McPhate, L. Theriot, A Research and Analysis Program of Studies on the Analysis of Weapon Effectiveness. Phase II Results.'ÄFATL-TR-71-110. August, 1971.
4. Manske, Robert A., Air to Air Gunfire Control Equations for Digital Lead Computing Optical Sights. AFAL-TR-75-52, January, 1975.
5. McDonnel-Douglas Corporation, IMAGE User's Manual. Supplement to AFATL-TR-68-112, September, 1968.
38
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