SOL-S-ASTR-TN-0010 Solar Orbiteremits.sso.esa.int/emits-doc/ESTEC/AO6309_AD2.pdf · SOL-S-ASTR-TN-0010 - Solar Orbiter System Budgets - Issue 2.doc 2.2 Mass Budget The mass budget

Solar Orbiter SOL-S-ASTR-TN-0010

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SOL-S-ASTR-TN-0010 - Solar Orbiter System Budgets - Issue 2.doc

Solar Orbiter System Budgets

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Date: 28/07/2009

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Date: 28/07/2009

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DOCUMENT CHANGE DETAILS

ISSUE CHANGE AUTHORITY CLASS RELEVANT INFORMATION/INSTRUCTIONS

A - - Initial Issue

1.0 - - Updated first official issue for SRR

2 - - Updated to include DSR comments (correction of PCDU dissipation, clarification of CPS budget)

2.1 - - Corrected captions for tables for 2018 science window definitions

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CONTENTS

SOLAR ORBITER SYSTEM BUDGETS ..........................................................................................................1

INTENTIONALLY BLANK..................................................................................................................................2

DOCUMENT CHANGE DETAILS.....................................................................................................................3

CONTENTS .......................................................................................................................................................4

1. APPLICABLE AND REFERENCE DOCUMENTS ........................................................................................5

2. SOLAR ORBITER BUDGETS .......................................................................................................................6 2.1 Introduction.............................................................................................................................................6 2.2 Mass Budget...........................................................................................................................................7 2.3 RF-Link Budget.....................................................................................................................................15

2.3.1 X-Band Down-link via LGA, Groundstation Kourou ..................................................................19 2.3.2 X-Band Down-link via LGA, Groundstation New Norkia ............................................................20 2.3.3 X-Band Down-link via MGA, Groundstation New Norkia ...........................................................21 2.3.4 X-Band and Ka-Band Downlink via HGA, Groundstation New Norcia.......................................22 2.3.5 X-Band and Ka-Band Downlink via HGA, Groundstation Cebreros ..........................................24 2.3.6 X-Band Up-link via LGA, Groundstation Kourou........................................................................26 2.3.7 X-Band Up-link via LGA, Groundstation New Norcia.................................................................27 2.3.8 X-Band Up-link via MGA, Groundstation New Norcia................................................................28 2.3.9 X-Band Up-link via MGA, Groundstation New Norcia................................................................29 2.3.10 X-Band Up/Down-Link Ranging via HGA, Groundstation New Norcia ....................................30 2.3.11 X/Ka-Band Up/Down-Link Ranging via HGA, GrSt New Norcia ..............................................32 2.3.12 DOR tone via HGA...................................................................................................................34

2.4 Power Budget .......................................................................................................................................36 2.5 Modes 1, 2............................................................................................................................................39 2.6 Modes 3, 12..........................................................................................................................................41 2.7 Modes 4, 11..........................................................................................................................................43 2.8 Modes 15, 5..........................................................................................................................................45 2.9 Modes 7, 8............................................................................................................................................47 2.10 Modes 10, 13......................................................................................................................................49 2.11 Mode 14..............................................................................................................................................51 2.12 Delta V and Attitude Control Budget ..................................................................................................53 2.13 Pointing Budget ..................................................................................................................................56

2.13.1 RPE Budget [POIN30c] ............................................................................................................56 2.13.2 APE Budget [POIN30a] ............................................................................................................58 2.13.3 PDE Budget [POIN30b]............................................................................................................63 2.13.4 Instrument Co-alignment Budget .............................................................................................64

2.14 Science Windows ...............................................................................................................................67 2.15 2017 Mission ......................................................................................................................................67 2.16 2018 Mission ......................................................................................................................................69 2.17 Mass Memory Usage Profile ..............................................................................................................71





1. APPLICABLE AND REFERENCE DOCUMENTS

RD01 Solar Orbiter Mission Requirements Document RD02 Solar Orbiter Engineering Change Request RD03 Solar Orbiter RF-link Budget RD04 ECSS-E-50-50A RD05 Communications Subsystem Architecture SOL-T-ASTR-TN-0019 RD06 Solar Orbiter Delta V and Attitude Control Budget RD07 Solar Orbiter Thermal Design Report





2. SOLAR ORBITER BUDGETS

2.1 Introduction

This document collates and presents all the budgets that are currently tracked for the Solar Orbiter SC. These are the following:

• Mass (inc. propellant loading) • RF-link • Power • Delta V and Attitude Control • Pointing

o APE o PDE o RPE o RS-instrument coalignment

• Science Window definition • Mass Memory budget and profile.

In all cases, the budget requirements, philosophy, including relevant standards and margins, is specified, along with references to supporting documentation. This document serves as a controlling document, and will supersede any document that contains conflicting budget information.





2.2 Mass Budget

The mass budget is driven by the need to satisfy the requirements LAUN05 and LAUN10 in the MRD [RD01]. It has been computed according to the requirements MASS05, MASS10, MASS15, MASS20, and MASS25 in the MRD, and the additional requirements specified in the ECR [RD02], according to the definitions shown in the following figure.

Figure 2.2-1: Mass margin

The ECR requirements specify a 30% system margin for the baseline launch case using the Atlas launcher from KSC, and a 0% system margin for the backup launch case on Soyuz-Fregat from Kourou was requested at PM7 of the study. Note also that for those BepiColombo units under development, the margins applied according to the figure above are applied in addition to the unit margins used within the BepiColombo programme. The current mass budgets presented are for the worst-case 2018 mission scenario (325 m/s effective delta V is used to determine the propellant loading) and baseline 2017 launch case are shown in the following tables. The capacity of the Atlas 401 (2500kg) is estimated from the Launch Vehicle User’s Manual (a precise estimate will require consultation with the Atlas launch authority due to insufficient information in the User’s Manual). The capacity of Soyuz-Fregat (1318kg) is as specified to be used by the ESA project team within the frame of the current study, and should be regarded as a preliminary estimate only, due to uncertainties in the projected performance of Soyuz-Fregat from Kourou into high declinations.





Solar Orbiter Estimated Mass

System NO. Unit Name Basic Unit Mass

Maturity margin Nominal Mass

Design Mass

[kg] [%] [kg] [kg] [kg]

Structure

Main Structure

1 LVA Ring Assy (incl. Tank beams)

26.54 7.0% 1.9 28.4 28.4

1 Lower Floor Assembly 11.94 10.0% 1.2 13.1 13.1

1 +Y Shear wall Assembly 13.46 10.0% 1.3 14.8 14.8

1 -Y-Z Shear wall assembly 11.23 10.0% 1.1 12.3 12.3

1 +Y-Z Shear wall assembly 13.07 10.0% 1.3 14.4 14.4

1 -Y+Z Shear wall assembly 11.74 10.0% 1.2 12.9 12.9

1 +Y+Z Shear wall assembly

11.45 10.0% 1.1 12.6 12.6

1 Misc cleats & fixings - Shear Walls

1.23 10.0% 0.1 1.4 1.4

1 Tank Floor -Z (incl. fittings)

1.69 10.0% 0.2 1.9 1.9

1 Tank Floor +Z (incl. fittings)

1.70 10.0% 0.2 1.9 1.9

1 ��

0.10 10.0% 0.0 0.1 0.1

1 Top Floor assembly

13.45 10.0% 1.3 14.8 14.8

1 ��

0.61 10.0% 0.1 0.7 0.7

1 '+Y side wall assembly

7.62 10.0% 0.8 8.4 8.4

1 '-Y side wall assembly

6.20 10.0% 0.6 6.8 6.8

1 Structural Fixings

0.33 10.0% 0.0 0.4 0.4

1 Panel +Z -Y (incl. fixings)

7.44 10.0% 0.7 8.2 8.2

1 Panel -Z -Y (incl. fixings)

7.44 10.0% 0.7 8.2 8.2

1 Panel +Z +Y (incl. fixings)

7.44 10.0% 0.7 8.2 8.2

1 Panel -Z +Y (incl. fixings)

7.44 10.0% 0.7 8.2 8.2

Main Structure 162.1 9.5% 15.41 177.5 177.5

Brackets & Supports

4 Reaction wheel brackets 1.42 25.0% 0.4 7.1 7.1

2 Star-Tracker supports & bkts 0.56 25.0% 0.1 1.4 1.4

8 Thruster brackets & fixings 0.44 25.0% 0.1 4.4 4.4

2 SADM supports 1.35 25.0% 0.3 3.4 3.4

3 HGA HDRM Brackets 0.07 25.0% 0.0 0.2 0.2

3 HGA I/F Support Brackets (excl. struts) 0.07 25.0% 0.0 0.2 0.2

1 MGA Support Brackets 0.15 25.0% 0.0 0.2 0.2

6 RPW I/F Support Brackets 0.15 25.0% 0.0 1.1 1.1

2 Umbilical connector bracket 0.16 25.0% 0.0 0.4 0.4

4 MGSE brackets 0.30 25.0% 0.1 1.5 1.5

2 LGA Support brackets 0.41 25.0% 0.1 1.0 1.0

2 Mirror Cube Assembly 0.06 25.0% 0.0 0.1 0.1

2 IMU/Gyro bracket(s) 0.15 25.0% 0.0 0.4 0.4

1 Pressurant Tank support 1.11 25.0% 0.3 1.4 1.4

1 Instrument shims 0.40 25.0% 0.1 0.5 0.5

1 Equipment fasteners 3.57 25.0% 0.9 4.5 4.5

200 Grounding straps for equipments 0.00 25.0% 0.0 0.2 0.2

2 Skin connector bkts 0.06 25.0% 0.0 0.2 0.2

1 Screws? (don't know if included) 7.50 25.0% 1.9 9.4 9.4





3 Boom Brackets 0.07 25.0% 0.0 0.2 0.2

1 STR panel extension + brackets 2.40 25.0% 0.6 3.0 3.0

8 Heatshield interface bkts 0.07 25.0% 0.0 0.7 0.7

3 Sun Sensor Support Brackets? 0.20 25.0% 0.1 0.8 0.8

2 SWA PAS + HIS Support Brackets 1.56 25.0% 0.4 3.9 3.9

2 Solo HI + EPD SIS Brackets 0.30 25.0% 0.1 0.8 0.8

5 Other EPD Brackets 0.15 25.0% 0.0 0.9 0.9

4 HS back protective MLI support brackets 0.3 25.0% 0.1 1.3 1.3

Brackets & Supports 39.3 25.0% 9.8 49.1 49.1

1 Boom Assembly 7.89 25.0% 2.0 9.9 9.9

Boom Assembly 7.9 25.0% 2.0 9.9 9.9

Structure Subtotal 209.3 13.0% 27.2 236.5 236.5

Thermal

2.81 Thermal Radiators 0.57 25.0% 0.1 2.0 2.0

16.52 External MLI (S/C) 0.50 25.0% 0.1 10.3 10.3

2.40 External MLI (Equipment) 0.50 25.0% 0.1 1.5 1.5

2.00 External MLI (Protection from reflections) 1.80 25.0% 0.5 4.5 4.5

27.00 Black Paint 0.09 25.0% 0.0 3.0 3.0

0.30 Internal MLI (Equipment) 0.30 25.0% 0.1 0.1 0.1

4.00 Prop Tank MLI 0.30 25.0% 0.1 1.5 1.5

0.20 Press Tank MLI 0.30 25.0% 0.1 0.1 0.1

1.50 CPS Pipework MLI 0.30 25.0% 0.1 0.6 0.6

4 TWT Doublers 0.69 25.0% 0.2 3.5 3.5

8 Fluid loops (cold fingers) 0.47 25.0% 0.1 4.7 4.7

120 Heaters 0.00 25.0% 0.0 0.3 0.3

212 Thermistors 0.00 25.0% 0.0 0.5 0.5

1 Sigraflex 0.40 25.0% 0.1 0.5 0.5

23 Surface Heat Pipes 0.29 25.0% 0.1 8.3 8.3

15.25 Embedded Heater Pipes 0.20 25.0% 0.1 3.8 3.8

Thermal Subtotal 36.2 25.0% 9.0 45.2 45.2

Communications

HGA RF Assy

1 ARA

2 Boom I/F brackets 1.0 25.0% 0.3 2.5 2.5

1 APM - S/C I/F brackets 1.5 25.0% 0.4 1.9 1.9

1 Sub Reflector Assembly 0.4 7.0% 0.0 0.4 0.4

1 Tripod Struts Assembly 1.1 7.0% 0.1 1.2 1.2

1 Main Reflector 14.0 7.0% 1.0 15.0 15.0

1 Inserts (S/C & Struts) 1.4 7.0% 0.1 1.5 1.5

1 Bonding 0.1 7.0% 0.0 0.1 0.1

1 Bolts, nuts, washers 0.6 7.0% 0.0 0.6 0.6

1 MLI & coatings (Frame, Reflector) 0.7 7.0% 0.0 0.8 0.8

1 HRM (mobile & fixed parts) 3.6 7.0% 0.3 3.9 3.9

0.0 0.0 0.0

RF Chain





1 Feed & Supports 3.7 7.0% 0.3 3.9 3.9

1 HGA HTWG incl brackets 3.5 10.0% 0.3 3.8 3.8

HGA RF Assy 32.6 0.0% 0.0 35.6 35.6

HGA APA

1 Azimuth stage 4.6 7.0% 0.3 4.9 4.9

1 Elevation stage 4.5 7.0% 0.3 4.8 4.8

1 Harness 0.2 7.0% 0.0 0.2 0.2

1 Mechanisms IF parts 1.1 7.0% 0.1 1.2 1.2

1 APME (1/2) 3.3 7.0% 0.2 3.5 3.5

1 HGA Boom 4.0 25.0% 1.0 5.0 5.0

0.15 MLI for HGA Boom 1.8 25.0% 0.5 0.3 0.3

HGA APA 18.0 0.0% 0.0 20.0 20.0

HTHGA Assembly 50.6 0.0% 0.0 55.6 55.6

MGA RF Assy

1 Horn Assy 2.5 7.0% 0.2 2.7 2.7

1 MGA WG 1.5 25.0% 0.4 1.9 1.9

MGA RF Assy 4.0 0.0% 0.0 4.6 4.6

MGA APA

0 APM1 Azimuth 4.1 7.0% 0.3 0.0 0.0

1 APM2 Elevation 5.5 7.0% 0.4 5.9 5.9

1 APM Brackets 3.6 7.0% 0.3 3.9 3.9

0.15 Thermal Hardware: MLI for MGA boom 1.8 25.0% 0.5 0.3 0.3

1 HDRM 1.1 7.0% 0.1 1.2 1.2

1 MGA Boom 5.6 7.0% 0.4 6.0 6.0

1 APME (1/2) 3.3 7.0% 0.2 3.5 3.5

0.0 0.0 0.0

0.0 0.0 0.0

0.0 0.0 0.0

MGA APA 19.4 0.0% 0.0 20.8 20.8

MGA Assembly 23.4 0.0% 0.0 25.3 25.3

Deep Space Transponder

2 X/X&Ka Band Receiver 3.7 7.0% 0.3 8.0 8.0

X Band Transmitter 0.0 0.0 0.0

Ka Band Transmitter 0.0 0.0 0.0

DST 7.5 0.0% 0.0 8.0 8.0

X-Band TWTA (35W RF, 54% Eff.)

2 X-Band EPC 1.6 7.0% 0.1 3.4 3.4

2 X-Band TWT 0.8 7.0% 0.1 1.8 1.8

X-Band TWTA 4.8 0.0% 0.0 5.2 5.2

Ka-Band TWTA (35W RF, 50% Eff.)





2 Ka-Band EPC 1.6 7.0% 0.1 3.4 3.4

2 Ka-Band TWT 0.7 7.0% 0.1 1.6 1.6

Ka-Band TWTA 4.6 0.0% 0.0 4.9 4.9

Cabling 0.0 0.0 0.0

1 RF-Distribution Assembly incl Cables (RFDA) 10.0 10.0% 1.0 11.0 11.0

2 X-band low gain antenna (LGA) 0.9 7.0% 0.1 1.9 1.9

misc 11.8 0.0% 0.0 12.9 12.9

Communication Subtotal 102.6 0.0% 0.0 111.9 111.9

DHS

1 On-Board Computer 8.4 7.0% 0.6 9.0 9.0

1 Solid State Mass Memory 11.3 10.0% 1.1 12.4 12.4

1 Remote Interface Unit 9.6 10.0% 1.0 10.6 10.6

DHS Subtotal 29.3 9.1% 2.7 32.0 32.0

AOCS

3 Star Tracker (No extended baffle or shutter needed) 2.8 7.0% 0.2 9.1 9.1

1 IMU ( W/O accelerometers) 7.1 7.0% 0.5 7.6 7.6

3 RMU (containing 3 gyros) 0.8 10.0% 0.1 2.6 2.6

0 CSS Electronics 1.26 25.0% 0.1 0.0 0.0

3 CSS heads 0.50 25.0% 0.2 2.0 2.0

1 FCE 4.00 25.0% 1.0 5.0 5.0

4 Reaction Wheels with integrated WDE 8.5 7.0% 0.6 36.4 36.4

4 Wheel Dampers 2.6 25.0% 0.6 12.9 12.9

AOCS Subtotal 67.8 11.5% 7.8 75.6 75.6

Power

8.4 Solar Array (8.4 m2)

8.4 Cells Assembly (Cold face) 1.1 25.0% 0.3 11.6 11.6

8.4 Cells Assembly (Hot face) 0.6 25.0% 0.2 6.4 6.4

8.4 Optical Solar Reflectors 0.5 25.0% 0.1 5.3 5.3

8.4 Solar Array substrate 5.2 25.0% 1.3 54.6 54.6

2 Yoke 4.0 25.0% 1.0 10.0 10.0

1 Hinges & mechanisms 6.4 25.0% 1.6 8.0 8.0

1 Edge shields 5.9 25.0% 1.5 7.3 7.3

2 cables & connectors 2.3 25.0% 0.6 5.7 5.7

2 Miscellaneous 0.3 25.0% 0.1 0.8 0.8

Solar Orbiter SA 87.7 0.0% 0.0 109.6 109.6

SADA

2 Solar Array Drive Mechanism 3.6 7.0% 0.3 7.7 7.7

2 Solar Array Drive Electronics 1.6 7.0% 0.1 3.4 3.4

Solar Orbiter SADA 10.4 0.0% 0.0 11.1 11.1

1 Power Control and Distribution Unit 26.0 25.0% 6.5 32.6 32.6





1 Battery 12.0 10.0% 1.2 13.2 13.2

Power Subtotal 136.0 5.7% 7.7 166.4 166.4

CPS

2 Propellant tanks 11.47 7.0% 0.8 24.5 24.5

1 Pressurant tank 2.90 7.0% 0.2 3.1 3.1

8 Pyrovalves 0.16 7.0% 0.0 1.4 1.4

3 Pressure Transducer 0.29 7.0% 0.0 0.9 0.9

4 Non Return Valves 0.09 7.0% 0.0 0.4 0.4

4 Pyrovalves 0.16 7.0% 0.0 0.7 0.7

8 Service Valves 0.06 7.0% 0.0 0.5 0.5

2 Filters 0.16 7.0% 0.0 0.3 0.3

16 Biprop Thruster 10N 0.65 7.0% 0.0 11.1 11.1

1 Pipework 3.90 25.0% 1.0 4.9 4.9

1 Pipe & components supports 6.52 25.0% 1.6 8.2 8.2

Propulsion Subtotal 50.6 10.7% 5.4 56.0 56.0

Payload

1 Payload allocation 124.8 25.0% 31.2 156.0 156.0

1 Filters 0.0 25.0% 0.0 0.0 0.0

Payload Subtotal 124.8 25.0% 31.2 156.0 156.0

Harness

1 Power Harness 19.8 25.0% 5.0 24.8 24.8

1 DHS Harness 19.8 25.0% 5.0 24.8 24.8

1 Comms Harness 19.8 25.0% 5.0 24.8 24.8

1 Thermal Harness 19.8 25.0% 5.0 24.8 24.8

Harness Subtotal 79.2 25.0% 19.8 99.0 99.0

Misc

1 N2 purging lines 3.0 25.0% 0.8 3.8 3.8

1 FM non-removable test HW 3.0 25.0% 0.8 3.8 3.8

1 CoG Balance masses 8.0 25.0% 2.0 10.0 10.0

Misc Subtotal 14.0 25.0% 3.5 17.5 17.5

Feedthroughs

1 STIX FT (without filter) 1.26 25.0% 0.3 1.6 1.6

1 PHI-HRT (without filter) 2.45 25.0% 0.6 3.1 3.1

1 PHI-FDT (without filter) 1.26 25.0% 0.3 1.6 1.6

1 EUI-HRI alpha + HRI 174 1.83 25.0% 0.5 2.3 2.3

1 EUI-FSI + HRI 195 2.03 25.0% 0.5 2.5 2.5

1 COR-Main 2.13 25.0% 0.5 2.7 2.7

1 SPICE 1.55 25.0% 0.4 1.9 1.9

1 FT Doors drive electronics 1.60 25.0% 0.4 2.0 2.0

Cylindrical Feedthroughs with Doors 14.1 25.0% 3.5 17.6 17.6





1 SWA-PAS 1.23 25.0% 0.3 1.5 1.5

1 SWA-HIS 1.28 25.0% 0.3 1.6 1.6

1 Sun Sensor FT 0.93 25.0% 0.2 1.2 1.2

1 Sun Sensor Thermal HW 0.35 25.0% 0.1 0.4 0.4

Corner Feedthroughs 3.8 25.0% 0.9 4.7 4.7

Feedthroughs Subtotal 17.9 25.0% 4.5 22.4 22.4

Heatshield

1 Heatshield allocation 66.0 25.0% 16.5 82.5 82.5

Heatshield Subtotal 66.0 25.0% 16.5 82.5 82.5

Total Dry (w/o adapter) 933.7 14.5% 135.3 1100.9 1100.9

System Margin 30.0% 330.3

Total Dry with Margin (w/o adapter) 1431.2

Consumables

1 Propellant load - Transfer 177.0 0.0% 0.0 177.0 177.0

1 Propellant load - RCS 8.0 100.0% 8.0 16.0 16.0

1 Pressurant load 1.2 0.0% 0.0 1.2 1.2

Consumables subtotal 186.2 4.3% 8.0 194.2 194.2

Total Wet with Margin (w/o adapter) 1625.4

Adapter Mass 41.0

Total Launch Mass 1666.4

Target Launch Mass (Atlas)

2500.0

Difference

833.6

Table 2.2-1: Solar Orbiter mass budget (2018 backup mission scenario) for the baseline Atlas launch case





Solar Orbiter Estimated Mass

System NO. Unit Name Basic Unit Mass

Maturity margin Nominal Mass

Design Mass

[kg] [%] [kg] [kg] [kg]

Total Dry (w/o adapter) 933.7 14.5% 135.3 1100.9 1100.9

System Margin 0.0% 0.0

Total Dry with Margin (w/o adapter) 1100.9

Consumables

1 Propellant load - Transfer 136.2 0.0% 0.0 136.2 136.2

1 Propellant load - RCS 8.0 100.0% 8.0 16.0 16.0

1 Pressurant load 1.2 0.0% 0.0 1.2 1.2

Consumables subtotal 145.3 5.5% 8.0 153.3 153.3

Total Wet with Margin (w/o adapter) 1254.2

Adapter Mass 41.0

Total Launch Mass 1295.2

Target Launch Mass (Soyuz)

1318.0

Difference

22.8

Table 2.2-2: Solar Orbiter mass budget (2018 backup mission scenario) for the backup Soyuz-Fregat launch case





2.3 RF-Link Budget

The RF-link budgets for Solar Orbiter are driven by the requirements COMS10 and COMS55 in the MRD [RD01]; note that the requirement COMS10 has been updated in agreement with the ESA project team for a TM total data-rate target of 150 kbps at 1 AU. The budgets are shown in the following tables. The link budgets are computed according to the Mission Requirement COMS70 and are defined in [RD04], including margin for nominal, adverse, favourable, mean -3 sigma and worst case RSS (Root Sum Square). The minimum values of these margins are:

• Nominal: > 3 dB • RSS worst case: > 0 dB • Mean - 3 sigma: > 0 dB.

The link budget margins are computed under the following assumptions: Telemetry:

• Telemetry bit error rate associated with 99.999% of transfer frame delivery for turbo coding 1/4 (probability of frame loss FER = 10-5, required Eb/No = 0.3 dB).

Telecommand: • The requirements of ECSS-E-50-05A, chapter 6 are applicable. The required bit error rate is BER is

10-5. Ranging:

• A maximum distance of 2.0 AU • PN and STD ranging • DOR ranging.

Ground Station: • ESA Ground Station New Norcia 35m Antenna X/Ka-Band • ESA Ground Station Cerberos 35m Antenna X/Ka-Band • ESA Ground Station Kourou 15m Antenna X-Band.

Please refer to [RD03] for a detailed description of the link budgets, including explicit declaration of the methodology used to calculate antenna noise temperature, atmospheric attenuation, RF-losses, ground station characteristics and other parameter assumptions. Many of the parameters used are derived from the BepiColombo design and link budgets, which Solar Orbiter shall completely reuse.

Ground station

S/C Antenna

Bitrate [Bps]

S/C- Earth [AU]

Mod. In. [rad]

S/C EIRP

[dBW]

Margin [dB]

Downlink X - Band

LGA 8000 0,007 1,25

LGA 500 0,028 1,25 Kourou 15m

LGA 10 0,195 1,25

Nom 3,4 3Sig 1,9 RSS 3,0

LGA 8000 0,033 1,25

LGA 500 0,127 1,25 New

Norcia 35m

LGA 10 0,9 1,25

No 13,4 Ad 13,4 Fa 19,1

Nom 3,1 3Sig 1,3 RSS 2,5

Kourou MGA 8000 0,1 1,25 No 36,3 Nom 3,5





Ground station

S/C Antenna

Bitrate [Bps]

S/C- Earth [AU]

Mod. In. [rad]

S/C EIRP

[dBW]

Margin [dB]

MGA 500 0,39 1,25 15m

MGA 75 1,0 1,25

3Sig 2,4 RSS 2,7

MGA 8000 0,5 1,25

MGA 2000 1,0 1,25 New

Norcia 35m

MGA 400 2,0 1,0

Ad 35,3 Fa 37,1

Nom 3,4 3Sig 2,4 RSS 2,5

HGA 8000 0,55 1,25

HGA 2000 1,1 1,25 Kourou 15m

HGA 500 2,0 1,25

Nom 3,1 3Sig 2,0 RSS 2,6

HGA 150000 0,82 1,25

HGA 100000*)

1,0 1,25 Cebreros 35m

HGA 25000 2,0 1,25

Nom 3,1 3Sig 2,5 RSS 2,6

HGA 150000 0,72 1,25

HGA 79.000**)

1,0 1,25 New

Norcia 35m

HGA 20.00 2,0 1,25

No 50,7 Ad 50,6 Fa 50,6

Nom 3,1 3Sig 2,0 RSS 2,5

Downlink Ka - Band

HGA 150.000 0,68 1,25

HGA 72.000**)

1,0 1,25 New

Norcia 35m

HGA 18.000 2,0 1,25

No 58,5 Ad 58,3 Fa 59,6

Nom 3,1 3Sig 2,7 RSS 2,6

HGA 150.000 0,8 1,25

HGA 120.000*)

1,0 1,25 Cebreros 35m

HGA 20.000 2,0 1,25

No 58,5 Ad 58,3 Fa 59,6

Nom 3,2 3Sig 2,8 RSS 2,7

*) New Norcia Groundstation: 79 Kbps (X-Band) + 72 Kbps (Ka-Band ) = 151 Kbps

**) Cebreros Groundstation: 100 Kbps (X-Band) + 120 Kbps (Ka-Band ) = 220 Kbps

Table 2.3-1: Solar Orbiter downlink budget summary

Ground station

S/C Antenna

Bitrate [Bps]

S/C- Earth [AU]

Mod. Index [rad]

S/C G/T

[dB/K]

TC Margin [dB]

Uplink X - Band

LGA 4000 0,006 1,4

LGA 250 0,025 1,4 Kourou 15m

LGA 7,6 0,06 1,0

No -28,1 Ad -28,6 Fa -22,8

Nom 3,6 3Sig 1,0 RSS 2,5





Ground station

S/C Antenna

Bitrate [Bps]

S/C- Earth [AU]

Mod. Index [rad]

S/C G/T

[dB/K]

TC Margin [dB]

LGA 4000 0,1 1,4

LGA 250 0,4 1,4 New

Norcia 35m

LGA 7,6 1,4 0,7

Nom 3,4 3Sig 1,0 RSS 2,2

MGA 4000 0,07 1,4

MGA 250 0,28 1,4

Kourou 15m

MGA 7,6 0,97 0,7

Nom 3,2 3Sig 1,7 RSS 2,1

MGA 4000 1,29 1,4

MGA 2000 1,8 1,4

New Norcia 35m

MGA 1000 2,0 1,4

No -7,3 Ad -7,8 Fa -6,8

Nom 3,1 3Sig 1,6 RSS 2,0

HGA 4000 0,38 1,4

HGA 250 1,4 1,2

Kourou 15m

HGA 16 2,0 0,5

Nom 3,0 3Sig 1,7 RSS 2,0

Cebreros 35m HGA 4000 2,0 1,4

Nom 13,8 3Sig 12,5 RSS 12,8

New Norcia 35m

HGA 4000 2,0 2,0

No 7,3 Ad 7,3 Fa 7,6

Nom 12,7 3Sig 11,6 RSS 11,7

Table 2.3-2: Solar Orbiter uplink budget summary





Uplink Bitrate [Bps]

Uplink Mod Index

[rad]

TC Margin

[dB]

Down link

Bitrate [Bps]

Down link

Mod Ind. [rad]

TM Margin

[dB]

Rang. Margin

[dB]

RNG Noise Accuracy

[m]

X-Band Uplink, X-Band Downlink Ranging via HGA, Distance 2 AU, Groundstation New Norcia

4000 TC 0,7 RNG 0,8

Nom 6,9 3Sig 5,7 RSS 5,8

8000 TM 0,8 RNG 0,7

Nom 3,1 3Sig 2,2 RSS 2,3

Nom 9,8 3Sig 7,8 RSS 8,1

Nom 0,2 Adv 0,3 Fav 0,2

X-Band Uplink, Ka-Band Downlink Ranging via HGA, Distance 2 AU, Groundstation New Norcia

4000 TC 0,5 RNG 1,0

Nom 3,4 3Sig 2,1 RSS 2,3

8000 TM 1,2 RNG 0,2

Nom 4,8 3Sig 4,2 RSS 4,2

Nom 9,8 3Sig 6,4 RSS 6,8

Nom 1,6 Adv 2,3 Fav 1,0

Table 2.3-3: Solar Orbiter ranging budget summary





2.3.1 X-Band Down-link via LGA, Groundstation Kourou

DOWNLINK BUDGET Version : 1.0

S/C data sheet : [Spacecraft.xls]SOLO_LGA_XGround Station data Sheet : [Groundstation.xls]Kourou15mX Date: 10.02.2009

LINK PARAMETERS UNIT Nominal Adverse Favour Mean Variance Delta Distr.

Frequency MHz 8425 8425 8425 8425,000Power at XPDR Output dBm 45,50 45,50 46,00 45,67 0,01389 0,00000 Triang.Tx circuit losses from XPDR to Antennae dB 1,10 1,10 0,90 1,00 0,00333 0,00000 UniVSWR, overall :1 1,16 1,17 1,14VSWR loss dB 0,02 0,03 0,02 0,02 0,00000 0,00001 Triang.S/C TX Ant. gain dBi -1,00 -1,00 4,00 0,67 1,38889 0,00000 Triang.S/C TX Ant. Axial ratio dB 4,00 4,00 4,00S/C TX Ant. pointing loss dB 0,00 0,00 0,00 0,00 0,00000 0,00000 Triang.Satellite EIRP dBW 13,38 13,37 19,08 15,31

Elevation angle ° 10,00 10,00 10,00 10,00Satelite/Earth Distance AU 0,007000 0,007000 0,007000 0,01Satellite/Earth Distance 1000xkm 1052,44 1052,44 1052,44 1052,44Free space losses dB 231,40 231,40 231,40 231,40 0,00000 0,00000 Triang.Atm. & Rain Attenuation dB 1,05 1,05 1,05 1,05 0,00000 0,00000 Gauss.Ionospheric losses dB 0,00 0,00 0,00 0,00 0,00000 0,00000 Gauss.Polarisation losses dB 0,33 0,38 0,22 0,30 0,00226 0,00257 UniPower Flux at G/S dBW/m2 -178,06 -178,06 -172,35 -176,13

Power Flux Density (4 kHz) dBW/m2 -178,06 -180,90 -188,32Power Flux Density Limit (4 KHz) dBW/m2 -147,50 -147,50 -147,50Power Flux Density Margin dB 30,56 33,40 40,82

G/S RX Ant. gain dBi 59,30 59,30 59,30 59,30 0,00000 0,00000 UniG/S RX Ant. Axial ratio dB 0,90 1,25 0,00G/S RX Ant. Pointing losses dB 0,00 0,00 0,00 0,00 0,00000 0,00000 UniG/S System noise Temperature dBK 22,40 22,70 22,20 22,45 0,00694 0,09000 Gauss.Earth Station G/T dB/°K 36,90 36,60 37,10 36,85

Boltzmanns const. dBW/Hz.K -228,60 -228,60 -228,60 -228,60

DOWNLINK C/No dBHz 46,09 45,74 52,11 48,01

Modulation Index rad pk 1,25 1,31 1,19

CARRIER RECOVERYCarrier Suppression dB 10,02 11,85 8,54 10,14 0,45857 3,34718 Triang.PLL Bandwidth, 2BLo Hz 1,00 1,20 0,80PLL Bandwidth, 2BLo dBHz 0,00 0,79 -0,97 -0,06 0,12964 0,62697 Triang.Required C/N in PLL dB 17,00 17,00 17,00 17,00 0,00000 0,00000 Triang.Carrier Recovery Margin dB 19,07 16,09 27,54 20,93 Mean-3sigma Margin dB 16,68Worst Case RSS dB 17,05

TELEMETRY RECOVERYModulation Losses dB 0,45 0,65 0,29 0,47 0,00546 0,03980 Triang.TM Demodulation Techno. Losses dB 2,90 3,00 2,00 2,63 0,05056 0,01000 Triang.TM Bit Rate (net) bps 8000,0 8000,0 8000,0Information Rate dBHz 39,03 39,03 39,03 39,03Required Eb/No dB 0,30 0,30 0,30 0,30TM recovery Margin dB 3,41 2,75 10,49 5,58 Mean-3sigma Margin dB 1,94Worst Case RSS dB 3,03





2.3.2 X-Band Down-link via LGA, Groundstation New Norkia


S/C data sheet : [Spacecraft.xls]SOLO_LGA_X

Ground Station data Sheet : [Groundstation.xls]NNO35mX Date: 10.02.2009


Frequency MHz 8425 8425 8425 8425,000Power at XPDR Output dBm 45,50 45,50 46,00 45,67 0,01389 0,00000 Triang.Tx circuit losses from XPDR to Antennae dB 1,10 1,10 0,90 1,00 0,00333 0,00000 UniVSWR, overall :1 1,16 1,17 1,14VSWR loss dB 0,02 0,03 0,02 0,02 0,00000 0,00001 Triang.S/C TX Ant. gain dBi -1,00 -1,00 4,00 0,67 1,38889 0,00000 Triang.S/C TX Ant. Axial ratio dB 4,00 4,00 4,00S/C TX Ant. pointing loss dB 0,00 0,00 0,00 0,00 0,00000 0,00000 Triang.Satellite EIRP dBW 13,38 13,37 19,08 15,31







CARRIER RECOVERYCarrier Suppression dB 10,02 11,85 8,54 10,14 0,45857 3,34718 Triang.PLL Bandwidth, 2BLo Hz 1,00 1,20 0,80PLL Bandwidth, 2BLo dBHz 0,00 0,79 -0,97 -0,06 0,12964 0,62697 Triang.Required C/N in PLL dB 17,00 17,00 17,00 17,00 0,00000 0,00000 Triang.Carrier Recovery Margin dB 18,76 15,46 26,98 20,33 Mean-3sigma Margin dB 16,08Worst Case RSS dB 16,68






2.3.3 X-Band Down-link via MGA, Groundstation New Norkia


S/C data sheet : [Spacecraft.xls]SOLO_MGA_X



Frequency MHz 8425 8425 8425 8425,000Power at XPDR Output dBm 45,50 45,50 46,00 45,67 0,01389 0,00000 Triang.Tx circuit losses from XPDR to Antennae dB 1,50 2,20 1,30 1,75 0,06750 0,49000 UniVSWR, overall :1 1,50 2,00 1,30VSWR loss dB 0,18 0,51 0,07 0,25 0,00870 0,11171 Triang.S/C TX Ant. gain dBi 22,50 22,50 22,50 22,50 0,00000 0,00000 Triang.S/C TX Ant. Axial ratio dB 1,40 1,50 1,40S/C TX Ant. pointing loss dB 0,00 0,00 0,00 0,00 0,00000 0,00000 Triang.Satellite EIRP dBW 36,32 35,29 37,13 36,16







CARRIER RECOVERYCarrier Suppression dB 10,02 11,85 8,54 10,14 0,45857 3,34718 Triang.PLL Bandwidth, 2BLo Hz 5,00 6,00 4,00PLL Bandwidth, 2BLo dBHz 6,99 7,78 6,02 6,93 0,12964 0,62697 Triang.Required C/N in PLL dB 17,00 17,00 17,00 17,00 0,00000 0,00000 Triang.Carrier Recovery Margin dB 11,38 7,08 14,66 10,85 Mean-3sigma Margin dB 8,36Worst Case RSS dB 9,16






2.3.4 X-Band and Ka-Band Downlink via HGA, Groundstation New Norcia

2.3.4.1 X-Band Down-link





2.3.4.2 Ka-Band Down-link


S/C data sheet : [Spacecraft.xls]SOLO_HGA_Ka

Ground Station data Sheet : [Groundstation.xls]NNO35mKa Date: 10.02.2009




Power Flux Density (1 MHz) dBW/m2 -175,50 -182,95 -187,56Power Flux Density Limit (1 MHz) dBW/m2 -108,75 -108,75 -108,75Power Flux Density Margin dB 66,75 74,20 78,81











2.3.5 X-Band and Ka-Band Downlink via HGA, Groundstation Cebreros

2.3.5.1 X-Band Down-link


S/C data sheet : [Spacecraft.xls]SOLO_HGA_X

Ground Station data Sheet : [Groundstation.xls]Cebreros35mX Date: 10.02.2009















2.3.5.2 Ka-Band Down-link



Ground Station data Sheet : [Groundstation.xls]Cebreros35mKa Date: 10.02.2009




Power Flux Density (1 MHz) dBW/m2 -175,50 -182,95 -187,56Power Flux Density Limit (1 MHz) dBW/m2 -108,75 -108,75 -108,75Power Flux Density Margin dB 66,75 74,20 78,81











2.3.6 X-Band Up-link via LGA, Groundstation Kourou

UPLINK BUDGET ASTROLINK

S/C data sheet : [Spacecraft.xls]SOLO_LGA_X DS form Version : 1.0

Ground Station data Sheet : [Groundstation.xls]Kourou15mX Date: 10.2.09


Frequency MHz 7170 7170 7170 7170,000G/S TX power dBW 26,60 26,60 26,60 26,60 0,00000 0,00000 Triang.Circuit loss dB 0,50 1,50 0,50 1,00 0,08333 1,00000 Uni.Antenna gain dBi 56,70 56,70 56,70 56,70 0,00000 0,00000 Uni.G/S Ant TX axial ratio dB 0,90 1,25 0,00G/S Pointing loss dB 0,00 0,00 0,00 0,00 0,00000 0,00000 Uni.EIRP of Ground Station dBW 82,80 81,80 82,80 82,30

Min elevation angle ° 10,00 10,00 10,00 10,00Satellite/Earth Distance AU 0,0060 0,0060 0,0060 0,01Slant Range 1000xkm 902,84 902,84 902,84 902,84Free space losses dB 228,67 228,67 228,67 228,67 0,00000 0,00000 Triang.Atm. & Rain Attenuation dB 1,05 1,05 1,05 1,05 0,00000 0,00000 Gauss.Ionospheric loss dB 0,00 0,00 0,00 0,00 0,00000 0,00000 Gauss.Polarisation losses dB 0,33 0,38 0,22 0,30 0,00226 0,00257 Uni.Input power Flux Density dBm/m2 -77,30 -78,30 -77,30 -77,80

Power at satellite dBW -147,25 -148,30 -147,14 -147,72

S/C Ant. gain dBi -1,00 -1,00 4,00 0,67 1,38889 0,00000 Triang.S/C Ant. Axial Ratio dB 4,00 4,00 4,00S/C Pointing loss dB 0,00 0,00 0,00 0,00 0,00000 0,00000 Triang.S/C Ant. VSWR :1 1,20 1,20 1,20S/C VSWR Loss dB 0,04 0,04 0,04 0,04 0,00000 0,00000 Triang.Rx circuit losses dB 1,20 1,20 1,00 1,10 0,00333 0,00000 Uni.Total received Power at receiver Input dBm -119,49 -120,54 -114,17 -118,19 Receiver Threshold dBm -143,00 -143,00 -143,00 -143,00Margin at Receiver Input dB 23,51 22,46 28,83 24,81 Mean - 3 Sigma dB 21,16Worst Case RSS dB 22,51

Antenna noise temp. K 150,00 150,00 150,00Feeder temperature K 310,00 470,00 330,00Receiver noise figure dB 2,00 2,00 2,00Receiver noise temp. K 169,62 169,62 169,62System noise temp. K 358,25 396,87 356,64System noise temp. dBK 25,54 25,99 25,52 25,75 0,00599 0,19776 Gauss.G/T dB/K -28,11 -28,60 -22,78Boltzmanns cons. dBW/HzK -228,60 -228,60 -228,60 -228,60

UPLINK C/No dBHz 53,57 52,08 58,90 54,66


CARRIER RECOVERYCarrier Suppression dB 4,93 5,54 4,37 4,95 0,05655 0,37030 Triang.Implementation Losses dB 1,00 1,10 0,90 1,00 0,00167 0,01000 Triang.PLL Bandwidth, 2BLo Hz 30,00 36,00 24,00PLL Bandwidth, 2BLo dBHz 14,77 15,56 13,80 14,71 0,12964 0,62697 Triang.Required C/N in PLL dB 10,00 10,00 10,00 10,00 0,00000 0,00000 Triang.Carrier Recovery Margin dB 22,87 19,87 29,83 24,00 Mean - 3 Sigma dB 20,12Worst Case RSS dB 21,38

TELECOMMAND RECOVERYModulation Losses dB 2,31 2,53 2,13 2,32 0,00682 0,04830 Triang.TC Demodulation Techno. Losses dB 2,00 2,10 1,90 2,00 0,00167 0,01000 Triang.TC Bit Rate bps 4000,0 4000,0 4000,0TC Bit Rate dBHz 36,02 36,02 36,02 36,02Required Eb/No dB 9,60 9,60 9,60 9,60TC recovery Margin dB 3,64 1,82 9,26 4,71 Mean - 3 Sigma dB 1,05Worst Case RSS dB 2,52





2.3.7 X-Band Up-link via LGA, Groundstation New Norcia


S/C data sheet : [Spacecraft.xls]SOLO_LGA_X DS form Version : 1.0

Ground Station data Sheet : [Groundstation.xls]NNO35mX Date: 10.2.09LINK PARAMETERS UNIT Nominal Adverse Favour Mean Variance Delta Distr.




S/C Ant. gain dBi -1,00 -1,00 4,00 0,67 1,38889 0,00000 Triang.S/C Ant. Axial Ratio dB 4,00 4,00 4,00S/C Pointing loss dB 0,00 0,00 0,00 0,00 0,00000 0,00000 Triang.S/C Ant. VSWR :1 1,20 1,20 1,20S/C VSWR Loss dB 0,04 0,04 0,04 0,04 0,00000 0,00000 Triang.Rx circuit losses dB 1,20 1,20 1,00 1,10 0,00333 0,00000 Uni.Total received Power at receiver Input dBm -119,75 -120,83 -113,78 -118,14 Receiver Threshold dBm -143,00 -143,00 -143,00 -143,00Margin at Receiver Input dB 23,25 22,17 29,22 24,86 Mean - 3 Sigma dB 21,17Worst Case RSS dB 22,25


UPLINK C/No dBHz 53,31 51,79 59,29 54,71








2.3.8 X-Band Up-link via MGA, Groundstation New Norcia


S/C data sheet : [Spacecraft.xls]SOLO_MGA_X DS form Version : 1.0

Ground Station data Sheet : [Groundstation.xls]Cebreros35mX Date: 10.2.09LINK PARAMETERS UNIT Nominal Adverse Favour Mean Variance Delta Distr.




S/C Ant. gain dBi 20,50 20,50 20,50 20,50 0,00000 0,00000 Triang.S/C Ant. Axial Ratio dB 1,40 1,50 1,40S/C Pointing loss dB 0,00 0,00 0,00 0,00 0,00000 0,00000 Triang.S/C Ant. VSWR :1 1,50 2,00 1,22S/C VSWR Loss dB 0,18 0,51 0,04 0,24 0,00971 0,11171 Triang.Rx circuit losses dB 1,50 1,60 1,30 1,45 0,00750 0,01000 Uni.Total received Power at receiver Input dBm -119,33 -120,81 -118,97 -119,86 Receiver Threshold dBm -143,00 -143,00 -143,00 -143,00Margin at Receiver Input dB 23,67 22,19 24,03 23,14 Mean - 3 Sigma dB 22,19Worst Case RSS dB 22,61


UPLINK C/No dBHz 53,23 51,73 53,66 52,73








2.3.9 X-Band Up-link via MGA, Groundstation New Norcia


S/C data sheet : [Spacecraft.xls]SOLO_HGA_X DS form Version : 1.0






Antenna noise temp. K 250,00 250,00 250,00Feeder temperature K 310,00 310,00 300,00Receiver noise figure dB 2,00 2,00 2,00Receiver noise temp. K 169,62 169,62 169,62System noise temp. K 434,10 434,10 429,90System noise temp. dBK 26,38 26,38 26,33 26,35 0,00005 0,00000 Gauss.G/T dB/K 7,29 7,24 7,56Boltzmanns cons. dBW/HzK -228,60 -228,60 -228,60 -228,60

UPLINK C/No dBHz 62,65 61,55 63,67 62,61








2.3.10 X-Band Up/Down-Link Ranging via HGA, Groundstation New Norcia

UPLINK BUDGET with RNG Table 1 of 2 Version : 1.0








UPLINK C/No dBHz 62,65 61,55 63,67 62,61

TC Modulation Index rad pk 0,70 0,74 0,67Ranging Modulation Index radpk 0,80 0,84 0,76

CARRIER RECOVERYTC Carrier Suppression dB 1,10 1,22 0,99 1,10 0,00215 0,01363 Triang.Ranging Carrier Suppression Losses dB 1,45 1,61 1,30 1,45 0,00382 0,02432 Triang.Carrier Implementation Losses dB 1,00 1,10 0,90 1,00 0,00167 0,01000 Triang.PLL Bandwidth, 2BLo Hz 200,00 240,00 160,00PLL Bandwidth, 2BLo dBHz 23,01 23,80 22,04 22,95 0,12964 0,62697 Triang.Required C/N in PLL dB 10,00 10,00 10,00 10,00 0,00000 0,00000 Triang.Carrier Recovery Margin dB 26,09 23,83 28,44 26,11 Mean - 3 Sigma dB 24,57Worst Case RSS dB 24,81

TELECOMMAND RECOVERYTC Modulation Losses dB 6,65 7,04 6,28 6,65 0,02412 0,15415 Triang.Ranging Modulation Losses dB 1,45 1,61 1,30 1,45 0,00382 0,02432 Triang.TC Demodulation Techno. Losses dB 2,00 2,10 1,90 2,00 0,00167 0,01000 Triang.TC Bit Rate bps 4000,0 4000,0 4000,0TC Bit Rate dBHz 36,02 36,02 36,02 36,02Required Eb/No dB 9,60 9,60 9,60 9,60TC recovery Margin dB 6,93 5,19 8,57 6,89 Mean - 3 Sigma dB 5,69Worst Case RSS dB 5,84

RANGING RECOVERYTC Modulation Losses dB 1,10 1,22 0,99 1,10 0,00215 0,01363 Triang.Ranging Modulation Losses dB 5,65 6,03 5,30 5,66 0,02200 0,14137 Triang.Ranging Implementation Losses dB 1,00 1,10 0,90 1,00 0,00167 0,01000 Triang.Ranging Bandwidth MHz 5,75 6,33 5,18 5,76Ranging Bandwidth dBHz 67,60 68,01 67,14 67,58 0,03161 0,17419 Triang.TC S/N in Videoband dB -14,04 -16,20 -11,95 -14,08 Ranging S/N in Videoband dB -12,70 -14,80 -10,66 -12,73





DOWNLINK BUDGET with RNG Table 2 of 2 Version : 1.0









TC S/N in Video Band dB -14,04 -16,20 -11,95 -14,08Ranging S/N in Video Band dB -12,70 -14,80 -10,66 -12,73TC Modulation Index rad pk 0,70 0,74 0,67TC echo Index rad pk 0,13 0,11 0,16TM Modulation Index rad pk 0,75 0,79 0,71Ranging Modulation Index rad pk 0,70 0,74 0,67Effective Ranging Modulation Index rad pk 0,16 0,13 0,18Noise Index rad pk 0,67 0,71 0,62



RANGING RECOVERYTM Mod. Losses incl RNG / noise / TC echo degr dB 22,94 24,94 21,14 23,01 0,60236 3,98178 Triang.Ranging Loop BW Hz 0,01 0,01 0,01Ranging Loop BW dBHz -20,00 -20,00 -20,00 -20,00Required Ranging Loop S/N dB 19,00 19,00 19,00 19,00Ranging recovery Margin dB 25,78 22,99 28,37 25,63 Mean-3sigma Margin dB 23,24Worst Case RSS dB 23,69

RANGING ACCURACYRNG S/No dB 24,78 21,99 27,37Integration time s 10 10 10RNG tone MHz 1,4 1,4 1,4RNG Noise (accuracy) m 0,2443 0,3369 0,1814





2.3.11 X/Ka-Band Up/Down-Link Ranging via HGA, GrSt New Norcia

Table 1 of 2 Version : 1.0








UPLINK C/No dBHz 62,65 61,55 63,67 62,61

TC Modulation Index rad pk 0,50 0,53 0,48Ranging Modulation Index radpk 1,00 1,05 0,95

CARRIER RECOVERYTC Carrier Suppression dB 0,55 0,61 0,50 0,55 0,00052 0,00331 Triang.Ranging Carrier Suppression Losses dB 2,32 2,58 2,08 2,33 0,01041 0,06661 Triang.Carrier Implementation Losses dB 1,00 1,10 0,90 1,00 0,00167 0,01000 Triang.PLL Bandwidth, 2BLo Hz 200,00 240,00 160,00PLL Bandwidth, 2BLo dBHz 23,01 23,80 22,04 22,95 0,12964 0,62697 Triang.Required C/N in PLL dB 10,00 10,00 10,00 10,00 0,00000 0,00000 Triang.Carrier Recovery Margin dB 25,76 23,46 28,15 25,78 Mean - 3 Sigma dB 24,25Worst Case RSS dB 24,48

TELECOMMAND RECOVERYTC Modulation Losses dB 9,30 9,72 8,91 9,31 0,02765 0,17539 Triang.Ranging Modulation Losses dB 2,32 2,58 2,08 2,33 0,01041 0,06661 Triang.TC Demodulation Techno. Losses dB 2,00 2,10 1,90 2,00 0,00167 0,01000 Triang.TC Bit Rate bps 4000,0 4000,0 4000,0TC Bit Rate dBHz 36,02 36,02 36,02 36,02Required Eb/No dB 9,60 9,60 9,60 9,60TC recovery Margin dB 3,40 1,53 5,16 3,35 Mean - 3 Sigma dB 2,12Worst Case RSS dB 2,28

RANGING RECOVERYTC Modulation Losses dB 0,55 0,61 0,50 0,55 0,00052 0,00331 Triang.Ranging Modulation Losses dB 4,12 4,45 3,81 4,13 0,01721 0,11236 Triang.Ranging Implementation Losses dB 1,00 1,10 0,90 1,00 0,00167 0,01000 Triang.Ranging Bandwidth MHz 5,75 6,33 5,18 5,76Ranging Bandwidth dBHz 67,60 68,01 67,14 67,58 0,03161 0,17419 Triang.TC S/N in Videoband dB -17,57 -19,87 -15,36 -17,61 Ranging S/N in Videoband dB -10,62 -12,62 -8,68 -10,65

UPLINK BUDGET with RNG





DOWNLINK BUDGET with RNG Table 2 of 2 Version : 1.0


Ground Station data Sheet : [Groundstation.xls]NNO35mka Date: 11.3.04








TC S/N in Video Band dB -17,57 -19,87 -15,36 -17,61Ranging S/N in Video Band dB -10,62 -12,62 -8,68 -10,65TC Modulation Index rad pk 0,50 0,53 0,48TC echo Index rad pk 0,03 0,02 0,03TM Modulation Index rad pk 1,20 1,26 1,14Ranging Modulation Index rad pk 0,20 0,21 0,19Effective Ranging Modulation Index rad pk 0,06 0,05 0,06Noise Index rad pk 0,19 0,20 0,18



RANGING RECOVERYTM Mod. Losses incl RNG / noise / TC echo degr dB 36,94 39,85 34,43 37,07 1,22373 8,46714 Triang.Ranging Loop BW Hz 0,01 0,01 0,01Ranging Loop BW dBHz -20,00 -20,00 -20,00 -20,00Required Ranging Loop S/N dB 19,00 19,00 19,00 19,00Ranging recovery Margin dB 9,79 6,14 13,43 9,77 Mean-3sigma Margin dB 6,39Worst Case RSS dB 6,83

RANGING ACCURACYRNG S/No dB 8,79 5,14 12,43Integration time s 10 10 10RNG tone MHz 1,4 1,4 1,4RNG Noise (accuracy) m 1,5387 2,3440 1,0125





2.3.12 DOR tone via HGA

Version : 1.0












DOR Tone RECOVERYModulation Losses dB 17,03 16,61 17,47 17,04 0,03087 0,17583 Triang.TM Demodulation Techno. Losses dB 1,00 1,00 1,00 1,00 0,00000 0,00000 Triang.

Required S/No dBHz 13,00 13,00 13,00 13,00Provided S/No dB 29,69 0,30 0,30 0,30TM recovery Margin dB 16,69 16,01 16,73 16,29 Mean-3sigma Margin dB 15,54Worst Case RSS dB 15,95

DOWNLINK BUDGET DOR Tone





Version : 1.0

S/C data sheet : [Spacecraft.xls]SOLO_HGA_KaGround Station data Sheet : [Groundstation.xls]NNO35mKa Date: 19.3.04










DOR Tone RECOVERYModulation Losses dB 17,03 16,61 17,47 17,04 0,03087 0,17583 Triang.TM Demodulation Techno. Losses dB 1,00 1,00 1,00 1,00 0,00000 0,00000 Triang.

Required S/No dBHz 13,00 13,00 13,00 13,00Provided S/No dB 27,70 0,30 0,30 0,30TM recovery Margin dB 14,70 14,07 15,09 14,50 Mean-3sigma Margin dB 13,70Worst Case RSS dB 14,02

DOWNLINK BUDGET DOR Tone





2.4 Power Budget

The power budget has been calculated according to the requirements POWM05, POWM10, POWM15, POWM20, POWM25 and POWM30 in the MRD [RD01], according to the definitions shown in the following figure.

Figure 2.4-1: Power Margin Philosophy

Because of the wide range of Sun distances experienced over the mission, there are 13 defined power modes for Solar Orbiter. Many of the power modes are identical from the perspective of unit function on-board the SC, but differ in heater power due to the varying thermal environments encountered. The 13 power modes are described in Table 2.4-1. Table 2.4-2 lists the thermal cases studied and marks their corresponding power modes in the generation of heater power requirements. The following table presents the power budgets by mode.

Mode Description Applicable Sun Distance

(AU) Power (W)

Mode 1

Standby (Launcher) Mode: This is the mode of the SC when on the launcher. The OBC, RIU, PCDU and Transponder (Rx only) are ON drawing power from the Battery. 1.0 156

Mode 2

Rate Reduction Mode: This mode corresponds to the Rate Reduction Mode of the AOCS: during this mode the Propulsion Subsystem, PCDU, OBC, RIU, IMU and X-band communications are operating. 1.0 460

Mode 3

Sun Acquisition Mode: This mode corresponds to the Sun Acquisition Mode of the AOCS: during this mode the Propulsion Subsystem, PCDU, SADE, OBC, RIU, CSS, IMU and X-band communications are operating. 1.0 478

Mode 12

Cruise Mode: This mode is identical to the Operational Mode (7), but with a different range of applicable Sun distances. 0.8 to 1.2 818

Mode 4

Safe Hold mode: This mode corresponds to the Safe Hold Mode of the AOCS: during this mode the Propulsion Subsystem, PCDU, SADE, OBC, RIU, CSS, STR, IMU, HTHGA Mechanism and X-bannd communications are operating. 0.8 to 1.2 730

Mode 11

Anti-Sun Mode: This mode corresponds to the anti-sun period in the CP, when the SC is greater than 1.2 AU from the Sun (TBC): durng this mode the PCDU, SADE, DHS Subsystem, AOCS Subsystem, and Communication subsystem (X+Ka band) and IS-instrument payload are operating. 1.2 to 1.5 756

Mode 15

Anti-Sun Safe Mode: This mode is identical to Mode (4) except with a different heater power due to the altered Sun distance. 1.2 to 1.5 641

Mode 7

Operational Mode: This mode corresponds to the normal Sun-pointing mode of the SC outside of the science windows (i.e. no RS-instrument operation): during this mode the Propulsion Subsystem, the PCDU, SADE, DHS Subsystem, AOCS Subsystem, and Communication subsystem (X+Ka band) and IS-instrument payload are operating. 0.234 to 0.8 925

Mode 5 Sun Keeping Mode: This mode corresponds to the Survival Mode of the AOCS: during this mode the 0.234 to 0.8 839





Propulsion Subsystem, PCDU, SADE, OBC, RIU, CSS, IMU, RMU, FCE and X-band communications are operating.

Mode 14

Venus Flyby Mode: This mode represents the Venus Flyby manouevres: During this mode the Propulsion subsystem and payloads are switched off. 0.72 750

Mode 8

Science with Comms: This mode corresponds to the Fine Sun Pointing AOCS mode, when the platform is stabilised for operation of the Remote Sensing payload, and the SC is above 0.28 AU and therefore the HTHGA is deployed and active: during this mode the PCDU, SADE, DHS Subsystem, AOCS Subsystem, Communication Subsystem (X+Ka band) and IS-instrument payload are operating. 0.28 to 0.8 993

Mode 10

Science No Comms: This mode corresponds to the Fine Sun Pointing AOCS mode, when the platform is stabilised for operation of the Remote Sensing payload, and the SC is below 0.28 AU and therefore the HTHGA is shielded behind the SC: during this mode the PCDU, SADE, DHS Subsystem, AOCS Subsystem, and IS-instrument payload are operating. 0.234 to 0.28 722

Mode 13

Cold Science Case: This mode is identical to the Science with Comms Mode (10), except that the heater power is different due to the greater Sun distance. 0.8 832

Table 2.4-1: Power mode descriptions

Design Cases

Sun Distance

(AU)

HGA deployed

RPW deployed

Solar Array

Angle (°)

SC Temp

SC pointing

Power Budget Case Purpose Notes

D1 0.2343 N Y 78 40 Sun Mode 10 Radiator sizing

Fine Sun pointing, non-comms: Science, perihelion case, dish behind heatshield (HOT OP CASE) - 2017 baseline, interpolated from ESOC supplied data

D2 0.28 Y Y 75 40 Sun Mode 8 Radiator sizing

Fine Sun pointing, with comms: Science, Limiting case with HGA exposed to Sun (i.e. minimum distance at which HGA is out in flux) (HOT OP CASE)

D3 DELETED

D4a 1.5 Y Y 0 10 Anti-Sun Mode 11 Heater sizing (ANTI_SUN HEATER SIZING)

Anti-Sun mode (COLD CASE)

D4b DELETED

D4c 1.5 Y Y 0 10 Sun Mode 11 Alt. Heater sizing (SUN-POINTING HEATER SIZING)

As a comparator against case D4a to assess benefit of AntiSun strategy





D4d 1.5 Y Y 0 10 Anti-Sun Mode 15

Alt. Heater sizing (ANTISUN-POINTING HEATER SIZING)

Sizing heaters of survival. Solar array sizing case.

D5 1.2 Y Y 0 10 Sun Mode 12 Heater sizing (NON-SCIENCE)

Limit of Sun-pointing case (COLD CASE) - max heater power required before pointing anti-sun

D6 0.8 Y Y 70 30 Sun Mode 13 Heater sizing (SCIENCE)

Fine Sun pointing aphelion: science cold case, max heater power required during science

D9 0.8 y y 70 30 Sun Mode 5 Heater sizing (SAFE)

Sun-keeping mode: safe mode heater power

Table 2.4-2: Thermal case definitions and corresponding power modes





2.5 Modes 1, 2

Mode 1 Mode 2

1 AU (LEOP) 1 AU (LEOP)

Standby (Launcher) Mode Rate Reduction Mode

SOLAR ORBITER Unit Name Nominal Power Power Margin NO. Nominal Power

Unit dissipation NO. Nominal

Power Unit level

dissipation

[W] [%] [W] [W] [W] [W] Thermal 0.0 0.0 65.0 65.0

Heaters 65 0.0 0 0.0 0.0 1 65.0 65.0

Harness 3% of total power 4.7 4.7 13.8 13.8

Propulsion 0.0 0.0 32.6 32.6

10N Thrusters 3.5 5.0 0 0.0 0.0 8 29.4 29.4

Pressure Transducers 1.0 5.0 0 0.0 0.0 3 3.2 3.2

Power 50.8 61.7 50.8 83.0

PCDU 46.2 10.0 1 50.8 50.8 1 50.8 50.8

PCDU Dissipation 0.0 10.9 32.2

SADE 6.6 5.0 0 0.0 0.0 0 0.0 0.0

Data Handling 44.3 44.3 44.3 44.3

OBC 28.4 5.0 1 29.8 29.8 1 29.8 29.8

RIU 13.2 10.0 1 14.5 14.5 1 14.5 14.5

SSMM 47.0 10.0 0 0.0 0.0 0 0.0 0.0

AOCS 0.0 0.0 43.0 43.0

Coarse Sun Sensor 0.2 20.0 0 0.0 0.0 0 0.0 0.0

Star Tracker 6.7 5.0 0 0.0 0.0 0 0.0 0.0

IMU 40.95 5.0 0 0.0 0.0 1 43.0 43.0

RMU 5.0 10.0 0 0.0 0.0 0 0.0 0.0

Reaction Wheels 20.0 5.0 0 0.0 0.0 0 0.0 0.0

FCE 15.0 20.0 0 0.0 0.0 0 0.0 0.0

Communications 30.0 30.0 133.6 133.6





HGA Mechanism 12.9 5.0 0 0.0 0.0 0 0.0 0.0

MGA Mechanism 4.0 20.0 0 0.0 0.0 0 0.0 0.0

X/X & Ka Transponder 27.0 5.0 2 30.0 30.0 2 50.8 50.8

TWT X-band 70.4 5.0 0 0.0 0.0 1 73.9 73.9

X-band EPC 8.4 5.0 0 0.0 0.0 1 8.8 8.8

TWT Ka-band 80.9 5.0 0 0.0 0.0 0 0.0 0.0

Ka-band EPC 9.5 5.0 0 0.0 0.0 0 0.0 0.0

PAYLOAD 0.0 0.0 0.0 0.0

In Situ Payload 50 0.0 0 0.0 0.0 0 0.0 0.0

Remote sensing 130 0.0 0 0.0 0.0 0 0.0 0.0

TOTAL 129.9 129.9 383.1 383.1

Total Power & Dissipation with 20% system margin

ORBITER 156 W 156 W 460 W 460 W





2.6 Modes 3, 12

Mode 3 Mode 12 (Th D5)

1 AU (LEOP) 0.8 AU to 1.2 AU

Sun Acquisition Mode Cruise Mode


Unit level dissipation NO. Nominal

Power Unit level

dissipation

[W] [%] [W] [W] [W] [W] Thermal 65.0 65.0 250.0 250.0

Heaters 65 0.0 1 65.0 65.0 1 250.0 250.0


Propulsion 32.6 32.6 3.2 3.2

10N Thrusters 3.5 5.0 8 29.4 29.4 0 0.0 0.0


Power 64.7 98.1 50.8 113.3

PCDU 46.2 10.0 1 50.8 50.8 1 50.8 50.8


SADE 6.6 5.0 2 13.9 13.9 0 0.0 0.0

Data Handling 44.3 44.3 96.0 96.0

OBC 28.4 5.0 1 29.8 29.8 1 29.8 29.8

RIU 13.2 10.0 1 14.5 14.5 1 14.5 14.5

SSMM 47.0 10.0 0 0.0 0.0 1 51.7 51.7

AOCS 43.7 43.7 120.1 120.1


Star Tracker 6.7 5.0 0 0.0 0.0 2 14.1 14.1

IMU 40.95 5.0 1 43.0 43.0 1 43.0 43.0

RMU 5.0 10.0 0 0.0 0.0 0 0.0 0.0

Reaction Wheels 20.0 5.0 0 0.0 0.0 3 63.0 63.0

FCE 15.0 20.0 0 0.0 0.0 0 0.0 0.0

Communications 133.6 133.6 147.1 147.1





HGA Mechanism 12.9 5.0 0 0.0 0.0 1 13.5 13.5

MGA Mechanism 4.0 20.0 0 0.0 0.0 0 0.0 0.0


TWT X-band 70.4 5.0 1 73.9 73.9 1 73.9 73.9

X-band EPC 8.4 5.0 1 8.8 8.8 1 8.8 8.8

TWT Ka-band 80.9 5.0 0 0.0 0.0 0 0.0 0.0

Ka-band EPC 9.5 5.0 0 0.0 0.0 0 0.0 0.0

PAYLOAD 0.0 0.0 50.0 50.0

In Situ Payload 50 0.0 0 0.0 0.0 1 50.0 50.0

Remote sensing 130 0.0 0 0.0 0.0 0 0.0 0.0

TOTAL 398.2 398.2

744.0 744.0


ORBITER 478 W 478 W 893 W 893 W





2.7 Modes 4, 11

Mode 4 (Th D8) Mode 11 (Th D4)

0.8 AU to 1.2 AU 1.2 AU to 1.5 AU

Safe Hold Mode Anti-Sun Mode



Power Unit level

dissipation

[W] [%] [W] [W] [W] [W] Thermal 340.0 340.0 180.0 180.0

Heaters 65 0.0 1 340.0 340.0 1 180.0 180.0


Propulsion 32.6 32.6 3.2 3.2

10N Thrusters 3.5 5.0 8 29.4 29.4 0 0.0 0.0


Power 64.7 124.5 50.8 102.8

PCDU 46.2 10.0 1 50.8 50.8 1 50.8 50.8


SADE 6.6 5.0 2 13.9 13.9 0 0.0 0.0

Data Handling 44.3 44.3 96.0 96.0

OBC 28.4 5.0 1 29.8 29.8 1 29.8 29.8

RIU 13.2 10.0 1 14.5 14.5 1 14.5 14.5

SSMM 47.0 10.0 0 0.0 0.0 1 51.7 51.7

AOCS 57.5 57.5 120.1 120.1


Star Tracker 6.7 5.0 2 14.1 14.1 2 14.1 14.1

IMU 40.95 5.0 1 43.0 43.0 1 43.0 43.0

RMU 5.0 10.0 0 0.0 0.0 0 0.0 0.0

Reaction Wheels 20.0 5.0 0 0.0 0.0 3 63.0 63.0

FCE 15.0 20.0 0 0.0 0.0 0 0.0 0.0

Communications 147.1 147.1 147.1 147.1





HGA Mechanism 12.9 5.0 1 13.5 13.5 1 13.5 13.5

MGA Mechanism 4.0 20.0 0 0.0 0.0 0 0.0 0.0


TWT X-band 70.4 5.0 1 73.9 73.9 1 73.9 73.9

X-band EPC 8.4 5.0 1 8.8 8.8 1 8.8 8.8

TWT Ka-band 80.9 5.0 0 0.0 0.0 0 0.0 0.0

Ka-band EPC 9.5 5.0 0 0.0 0.0 0 0.0 0.0

PAYLOAD 0.0 0.0 0.0 0.0

In Situ Payload 50 0.0 0 0.0 0.0 0 0.0 0.0

Remote sensing 130 0.0 0 0.0 0.0 0 0.0 0.0

TOTAL 711.8 711.8

619.5 619.5


ORBITER 854 W 854 W 743 W 743 W

Sol

ar O

rbite

r S

OL-

S-A

STR

-TN

-001

0 Is

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2 P

age

45 o

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and

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oth

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Issu

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2.8

Mod

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5, 5

M

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15

M

ode

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h D

9)

1.

2 A

U to

1.5

AU

0.23

4 A

U to

0.8

AU

A

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Mod

e

Sun

Kee

ping

Mod

e

SO

LAR

OR

BIT

ER

U

nit N

ame

Nom

inal

Pow

er

Pow

er M

argi

n

NO

. N

omin

al

Pow

er

Uni

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el

diss

ipat

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N

O.

Nom

inal

P

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U

nit l

evel

di

ssip

atio

n

[W]

[%]

[W]

[W]

[W]

[W]

Ther

mal

230.

0 23

0.0

340.

0 34

0.0

H

eate

rs

65

0.0

1

230.

0 23

0.0

1

340.

0 34

0.0

Har

ness

3%

of t

otal

pow

er

20.7

20

.7

24.8

24

.8

Pro

puls

ion

32

.6

32.6

32

.6

32.6

10

N T

hrus

ters

3.

5 5.

0

8 29

.4

29.4

8 29

.4

29.4

P

ress

ure

Tran

sduc

ers

1.0

5.0

3

3.2

3.2

3

3.2

3.2

Pow

er

64

.7

113.

1

64

.7

122.

5

P

CD

U

46.2

10

.0

1

50.8

50

.8

1

50.8

50

.8

P

CD

U D

issi

patio

n

0.0

48

.4

57

.8

S

AD

E

6.6

5.0

2

13.9

13

.9

2

13.9

13

.9

Dat

a H

andl

ing

44

.3

44.3

44

.3

44.3

O

BC

28

.4

5.0

1

29.8

29

.8

1

29.8

29

.8

R

IU

13.2

10

.0

1

14.5

14

.5

1

14.5

14

.5

S

SM

M

47.0

10

.0

0

0.0

0.0

0

0.0

0.0

AO

CS

57.3

57

.3

35.0

35

.0

C

oars

e S

un S

enso

r 0.

2 20

.0

1

0.2

0.2

2

0.5

0.5

S

tar T

rack

er

6.7

5.0

2

14.1

14

.1

0

0.0

0.0

IM

U

40.9

5 5.

0

1 43

.0

43.0

0 0.

0 0.

0

R

MU

5.

0 10

.0

0

0.0

0.0

3

16.5

16

.5

R

eact

ion

Whe

els

20.0

5.

0

0 0.

0 0.

0

0 0.

0 0.

0

FC

E

15.0

20

.0

0

0.0

0.0

1

18.0

18

.0

Com

mun

icat

ions

126.

3 12

6.3

147.

1 14

7.1





HGA Mechanism 12.9 5.0 1 13.5 13.5 1 13.5 13.5

MGA Mechanism 4.0 20.0 0 0.0 0.0 0 0.0 0.0


TWT X-band 70.4 5.0 1 73.9 73.9 1 73.9 73.9

X-band EPC 8.4 5.0 1 8.8 8.8 1 8.8 8.8

TWT Ka-band 80.9 5.0 0 0.0 0.0 0 0.0 0.0

Ka-band EPC 9.5 5.0 0 0.0 0.0 0 0.0 0.0

PAYLOAD 0.0 0.0 0.0 0.0

In Situ Payload 50 0.0 0 0.0 0.0 0 0.0 0.0

Remote sensing 130 0.0 0 0.0 0.0 0 0.0 0.0

TOTAL 575.9 575.9 688.4 688.4


ORBITER 691 W 691 W 826 W 826 W

Sol

ar O

rbite

r S

OL-

S-A

STR

-TN

-001

0 Is

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2 P

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47 o

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oth

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AU

to 0

.8 A

U

0.

28 A

U to

0.8

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Sci

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with

Com

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SO

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Pow

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Pow

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Pow

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Uni

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diss

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N

O.

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P

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U

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di

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n

[W]

[%]

[W]

[W]

[W]

[W]

Ther

mal

250.

0 25

0.0

65.0

65

.0

H

eate

rs

65

0.0

1

250.

0 25

0.0

1

65.0

65

.0

Har

ness

3%

of t

otal

pow

er

31.9

31

.9

29.8

29

.8

Pro

puls

ion

3.

2 3.

2

3.

2 3.

2

10

N T

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3.

5 5.

0

0 0.

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0

0 0.

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P

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Tran

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1.0

5.0

3

3.2

3.2

3

3.2

3.2

Pow

er

50

.8

125.

2

50

.8

120.

3

P

CD

U

46.2

10

.0

1

50.8

50

.8

1

50.8

50

.8

P

CD

U D

issi

patio

n

0.0

74

.3

69

.5

S

AD

E

6.6

5.0

0

0.0

0.0

0

0.0

0.0

Dat

a H

andl

ing

96

.0

96.0

96

.0

96.0

O

BC

28

.4

5.0

1

29.8

29

.8

1

29.8

29

.8

R

IU

13.2

10

.0

1

14.5

14

.5

1

14.5

14

.5

S

SM

M

47.0

10

.0

1

51.7

51

.7

1

51.7

51

.7

AO

CS

155.

0 15

5.0

155.

0 15

5.0

C

oars

e S

un S

enso

r 0.

2 20

.0

2

0.5

0.5

2

0.5

0.5

S

tar T

rack

er

6.7

5.0

2

14.1

14

.1

2

14.1

14

.1

IM

U

40.9

5 5.

0

1 43

.0

43.0

1 43

.0

43.0

R

MU

5.

0 10

.0

3

16.5

16

.5

3

16.5

16

.5

R

eact

ion

Whe

els

20.0

5.

0

3 63

.0

63.0

3 63

.0

63.0

FC

E

15.0

20

.0

1

18.0

18

.0

1

18.0

18

.0

Com

mun

icat

ions

247.

9 24

7.9

247.

9 24

7.9





HGA Mechanism 12.9 5.0 1 13.5 13.5 1 13.5 13.5

MGA Mechanism 4.0 20.0 0 0.0 0.0 0 0.0 0.0


TWT X-band 70.4 5.0 1 73.9 73.9 1 73.9 73.9

X-band EPC 8.4 5.0 1 8.8 8.8 1 8.8 8.8

TWT Ka-band 80.9 5.0 1 84.9 84.9 1 84.9 84.9

Ka-band EPC 9.5 5.0 1 10.0 10.0 1 10.0 10.0

PAYLOAD 50.0 50.0 180.0 180.0

In Situ Payload 50 0.0 1 50.0 50.0 1 50.0 50.0

Remote sensing 130 0.0 0 0.0 0.0 1 130.0 130.0

TOTAL 884.8 884.8 827.8 827.8


ORBITER 925 W 925 W 993 W 993 W





2.10 Modes 10, 13

Mode 10 (Th D1) Mode 13 (Th D6)

0.234 AU to 0.28 AU 0.8 AU

Science No Comms Cold Science Case



Power Unit level

dissipation

[W] [%] [W] [W] [W] [W] Thermal 65.0 65.0 230.0 230.0

Heaters 65 0.0 1 65.0 65.0 1 230.0 230.0


Propulsion 3.2 3.2 3.2 3.2

10N Thrusters 3.5 5.0 0 0.0 0.0 0 0.0 0.0


Power 50.8 101.4 50.8 116.9

PCDU 46.2 10.0 1 50.8 50.8 1 50.8 50.8


SADE 6.6 5.0 0 0.0 0.0 0 0.0 0.0

Data Handling 96.0 96.0 96.0 96.0

OBC 28.4 5.0 1 29.8 29.8 1 29.8 29.8

RIU 13.2 10.0 1 14.5 14.5 1 14.5 14.5

SSMM 47.0 10.0 1 51.7 51.7 1 51.7 51.7

AOCS 155.0 155.0 155.0 155.0


Star Tracker 6.7 5.0 2 14.1 14.1 2 14.1 14.1

IMU 40.95 5.0 1 43.0 43.0 1 43.0 43.0

RMU 5.0 10.0 3 16.5 16.5 3 16.5 16.5

Reaction Wheels 20.0 5.0 3 63.0 63.0 3 63.0 63.0

FCE 15.0 20.0 1 18.0 18.0 1 18.0 18.0

Communications 30.0 30.0 43.6 43.6





HGA Mechanism 12.9 5.0 0 0.0 0.0 1 13.5 13.5

MGA Mechanism 4.0 20.0 0 0.0 0.0 0 0.0 0.0


TWT X-band 70.4 5.0 0 0.0 0.0 0 0.0 0.0

X-band EPC 8.4 5.0 0 0.0 0.0 0 0.0 0.0

TWT Ka-band 80.9 5.0 0 0.0 0.0 0 0.0 0.0

Ka-band EPC 9.5 5.0 0 0.0 0.0 0 0.0 0.0

PAYLOAD 180.0 180.0 180.0 180.0

In Situ Payload 50 0.0 1 50.0 50.0 1 50.0 50.0

Remote sensing 130 0.0 1 130.0 130.0 1 130.0 130.0

TOTAL 601.7 601.7

787.0 787.0


ORBITER 722 W 722 W 944 W 944 W





2.11 Mode 14

Mode 14 (Th D7)

0.72 AU

Venus Flyby Mode


Unit level dissipation

[W] [%] [W] [W] Thermal 250.0 250.0

Heaters 65 0.0 1 250.0 250.0

Harness 3% of total power 22.9 22.9

Propulsion 3.2 3.2

10N Thrusters 3.5 5.0 0 0.0 0.0

Pressure Transducers 1.0 5.0 3 3.2 3.2

Power 64.7 118.0

PCDU 46.2 10.0 1 50.8 50.8

PCDU Dissipation 0.0 53.3

SADE 6.6 5.0 2 13.9 13.9

Data Handling 96.0 96.0

OBC 28.4 5.0 1 29.8 29.8

RIU 13.2 10.0 1 14.5 14.5

SSMM 47.0 10.0 1 51.7 51.7

AOCS 155.0 155.0

Coarse Sun Sensor 0.2 20.0 2 0.5 0.5

Star Tracker 6.7 5.0 2 14.1 14.1

IMU 40.95 5.0 1 43.0 43.0

RMU 5.0 10.0 3 16.5 16.5

Reaction Wheels 20.0 5.0 3 63.0 63.0

FCE 15.0 20.0 1 18.0 18.0

Communications 43.6 43.6





HGA Mechanism 12.9 5.0 1 13.5 13.5

MGA Mechanism 4.0 20.0 0 0.0 0.0

X/X & Ka Transponder 27.0 5.0 2 30.0 30.0

TWT X-band 70.4 5.0 0 0.0 0.0

X-band EPC 8.4 5.0 0 0.0 0.0

TWT Ka-band 80.9 5.0 0 0.0 0.0

Ka-band EPC 9.5 5.0 0 0.0 0.0

PAYLOAD 0.0 0.0

In Situ Payload 50 0.0 0 0.0 0.0

Remote sensing 130 0.0 0 0.0 0.0

TOTAL 635.4 635.4


ORBITER 762 W 762 W





2.12 Delta V and Attitude Control Budget

For a full description of the derivation of the delta V and attitude control budget, please refer to [RD06]. The delta V and attitude control budget has been calculated to satisfy the requirement PROP15, according to the requirements PROP05 and PROP10 in the MRD [RD01]. The following definitions are used:

• Nominal Mission Delta V: Basic delta V with no margins applied, or consideration of attitude constraints and thruster inefficiency factors

• Nominal Effective Delta V: Basic delta V with accounting for attitude constraints and thruster inefficiency factors

• Total Effective Delta V: Nominal effective delta V with 5% margin applied.

Figure 2.12-1: Delta V budget philosophy

Table 2.12-1 and Table 2.12-2 present the delta V and attitude control budgets for the nominal 2017 and backup 2018 mission scenarios respectively.





Launch 2017 Best Estimate

Margin/Eff. Factor Value Source

Deterministic Flight Programme Error 25 0 25 m/s VEX error correction precedent [1]

Probabilistic Launcher Error 15 m/s Provided by [1]

DSM for non-optimal launch date 0 m/s 21 day zero penalty window is possible - taken from [2]

Gravity Assist Manoeuvres 15 m/s/GA 8 120 m/s 15m/s allocation for each GAM [3]

Gravity losses 0 m/s Negligible for Solar Orbiter

Total Nominal Mission Delta V 160 m/s Clean nominal mission delta V

AOCS longitudinal thrusters inefficiency 70 m/s 3% 2 m/s Thr. Eff. For longitudinal manoeuvres [4]

AOCS transverse thrusters inefficiency 90.0 m/s 107% 96 m/s Worst-case Thr. Eff. For transverse manoeuvres [4]

Total thrusters configuration effect 98 m/s Calculated for current thruster configuration

Nominal Effective Delta V 258 m/s Nominal effective mission delta V

Total Effective Delta V margin 258 m/s 5% 13 m/s As required by [3]

Total Effective Delta V 271 m/s Total effective mission delta V

Propellant mass for attitude control 8.0 kg 100% 16.0 kg Estimate based on mission angular impulse [4]

Table 2.12-1: Nominal 2017 Mission Scenario





Launch 2018 Best Estimate

Margin/Eff. Factor Value Source

Deterministic Flight Programme Error 25 m/s VEX error correction precedent [1]

Probabilistic Launcher Error 15 m/s Provided by [1]

DSM for non-optimal launch date 50 m/s 50m/s penalty required for 20 day LW [2]

Gravity Assist Manoeuvres 15 m/s/GA 8 120 m/s 15m/s allocation for each GAM [3]

Gravity losses 0 m/s Negligible for Solar Orbiter

Total Nominal Mission Delta V 210 m/s Clean mission delta V

AOCS longitudinal thrusters inefficiency 120 m/s 3% 4 m/s Thr. Eff. For longitudinal manoeuvres [4]

AOCS transverse thrusters inefficiency 90.0 m/s 107% 96 m/s Worst-case Thr. Eff. For transverse manoeuvres [4]

Total thrusters configuration effect 100 m/s Calculated for current thruster configuration

Nominal Effective Delta V 310 m/s Nominal effective mission delta V

Total Effective Delta V margin 310 m/s 5% 15 m/s As required by [3]

Total Effective Delta V 325 m/s Total effective mission delta V

Propellant mass for attitude control 8.0 kg 100% 16.0 kg Estimate based on mission angular impulse [4]

[1] Email correspondance with [email protected], 01/04/2009.

[2] SOL-ESC-RP_GFA-JRC-WP 5XX (draft) - Solar Orbiter Mission Analysis for Launch in 2017-2018.

[3] SOL-EST-RS-00049 Issue 4 - Solar Orbiter Mission Requirements Document.

[4] SOL-S-ASTR-TN-00XX (draft) - Solar Orbiter Delta V and Attitude Control Budgets.

Table 2.12-2: Backup 2018 Mission Scenario





2.13 Pointing Budget

The following section presents the budgets for the various pointing requirements presented in POIN30, and the coalignment requirement POIN45 of the MRD [RD01]. The requirements are reproduced in the following table for convenience. It should be noted that these requirements are considered active only during the science windows of the mission when the RS-payloads are operating.

Table 2.13-1: Solar Orbiter pointing and accuracy requirements during RS-observation

The requirements are interpreted as complete, i.e. the APE requirement applies over the entire alignment-chain, from the STR LoS through to the reference optical LoS of the instrument. Accordingly, budget allocations are included for instrument misalignment. For the APE and Co-alignment budgets, three budgets are presented, corresponding to the three thermal cases D1, D2 and D6 (see Table 2.4-2 for a specification of the thermal cases studied), which have been identified as the extreme thermal cases of the operational phase of the mission, during which the alignment requirements of POIN30 are applicable. These are:

D1 (“Hot1”) 0.2343 AU HTHGA folded, all instruments operating D2 (“Hot2”) 0.28 AU HTHGA exposed, all instruments operating D6 (“Cold”) 0.8 AU HTHGA exposed, all instruments operating

Table 2.13-2: Thermal cases corresponding to alignment budgets

Error-type classifications are as defined in the Aeolus project.

2.13.1 RPE Budget [POIN30c]

2.13.1.1 Line of Sight Y-Axis

Solar Orbiter AOCS Relative Pointing Error Type

LOS Pointing Stability over time (10 sec)

Comments

LOS Y-Axis

Confidence level 95,5 % Proposed SRS Requirement (arcsec) 2.40

Error contributors (in arcsec):

Micrometeorids

B 0.00 negligible (impacts causing 0.1"/s

rate change happen 0.03 times/day

Solar pressure noises R 0.00 Negligible during this period. Wheels Microvibrations (3000 rpm) not part of AOCS Budget R 0.00 HGA pointing mechanism R 0.10 Simulation Result Solar Array rotation H 0.00 No rotation during measurement Orbit Estimation H 0.00 AOCS error: bandwidth = 0.015Hz, gyro stellar estimator B 1.80 Simulation Result AOCS Wheel torque noise (included in R 0.00





AOCS error)

AOCS internal thermal deformations H 0.10 Assumption

Total (linear sum) 2.00 arcsec Proposed SRS Requirement (arcsec) 2.40 arcsec

Table 2.13-3: Line-of-Sight RPE pointing budget

2.13.1.2 Line of Sight Z-Axis



Comments

LOS Z-Axis



Micrometeorids

B 0.00 negligible (impacts causing 0.1"/s

rate change happen 0.03 times/day

Solar pressure noises R 0.00 Negligible during this period. Wheels Microvibrations (3000 rpm) not part of AOCS Budget R 0.00 HGA pointing mechanism R 0.10 Simulation Result Solar Array rotation

H 0.00 No rotation during measurement Orbit Estimation H 0.00 AOCS error: bandwidth = 0.015Hz, gyro stellar estimator B 1.10 Simulation Result AOCS Wheel torque noise (included in AOCS error) R 0.00 AOCS internal thermal deformations H 0.10 Assumption


Table 2.13-4: Line-of-Sight RPE pointing budget

2.13.1.3 Around Line-of-Sight



Comments

Around LOS







Micrometeorids

B 0.00

negligible (impacts causing 0.1"/s rate change happen 0.03

times/day

Solar pressure noises R 0.00 Negligible during this period. Wheels Microvibrations (3000 rpm) not part of AOCS budget R 0.00 HGA pointing mechanism R 0.10 Simulation Result Solar Array rotation

H 0.00 No rotation during measurement Orbit Estimation H 0.00 AOCS error: bandwidth = 0.015Hz, gyro stellar estimator B 1.40 Simulation Result AOCS Wheel torque noise included in AOCS error R 0.00 AOCS internal thermal deformations H 0.10 Assumption


Table 2.13-5: Around Line-of-Sight RPE pointing budget

2.13.2 APE Budget [POIN30a]

The APE and coalignment chain is as presented in the following figure. The APE requirement is interpreted as being between the commanded attitude and the METIS optical LoS, which is the reference optical axis of the SC. Similarly the coalignment requirement is interpreted as being between the LoS of any two instruments. Accordingly, budget allocations are included for instrument alignment.

Figure 2.13-1: APE and co-alignment chain





2.13.2.1 APE LoS

Thermal Case D1 (“Hot1”)

Frequency Class Error Component

Error Type Class

APE Contribut

ion Units Data source

Systematic

Star Tracker Bias G 14.7 arcsec Aeolus measurement mode APE budget

Gravity Release (1g-0g) U 20.0 arcsec ASU estimate (TBC)

Launch Slippage (STR to METIS slippage) B 20.0 arcsec ASU estimate (TBC)

Ageing U 0.0 Waiting on ASU Estimate (TBC)

STR LOS to METIS ILS alignment U 33.0 arcsec Typical achieved by AIT (To include structure build and alignment

requirement/interface alignment?)

Systematic Error Subtotal 45.9 arcsec

Long Term

TE distortion between METIS ILS and STR LOS E 147.0 arcsec Astrium analysis, Case: Hot 1

Pure AOCS errors

(sensors, actuators, control)

H/R 12.6 arcsec ASD analysis 12/05/09

Long Term Error Subtotal 147.5 arcsec

Short Term

Flexible mode and slosh H 1.0 arcsec Aeolus measurement mode APE budget

Estimation noise R 0.0 arcsec Aeolus measurement mode APE budget

Navigation & Guidance noise R 0.4 arcsec Aeolus measurement mode APE budget

Control noise R 2.1 arcsec Aeolus measurement mode APE budget

HGA Pointing Mechanism R 0.4 arcsec ASD RPE budget calculation

Microvibration R 1.0 arcsec ASD RPE budget calculation

Short Term Error Subtotal (RSS) 2.6 arcsec

Total APE 196.0 arcsec

APE Requirement 120.0 arcsec

Budget Margin (Absolute) -76.0 arcsec

Budget Margin (Percentage) -63.3%

Table 2.13-6: LoS APE during thermal case D1 (“Hot1”)





Thermal Case D2 (“Hot2”)


Error Type Class

APE Contribut


Systematic





STR LOS to METIS ILS alignment 33.0 arcsec Typical achieved by AIT (To include structure build and alignment



Long Term

TE distortion between METIS ILS and STR LOS E 39.0 arcsec Astrium analysis, Case: Hot 2

Pure AOCS errors


H/R 12.6 arcsec Aeolus measurement mode APE budget


Short Term










Budget Margin (Absolute) 30.6 arcsec

Budget Margin (Percentage) 25.5%

Table 2.13-7: LoS APE during thermal case D2 (“Hot2”)





Thermal Case D6 (“Cold”)


Error Type Class

APE Contribut


Systematic





STR LOS to METIS ILS alignment 33.0 arcsec Typical achieved by AIT (To include structure build and alignment



Long Term

TE distortion between METIS ILS and STR LOS E 96.0 arcsec Astrium analysis, Case: Cold

Pure AOCS errors


H/R 12.6 arcsec Aeolus measurement mode APE budget


Short Term










Budget Margin (Absolute) -25.3 arcsec

Budget Margin (Percentage) -21.1%

Table 2.13-8: LoS APE during thermal case D6 (“Cold”)





Note that the reported non-compliance of the APE during thermal case D1 (caused by a localised cooling due to the TWTA radiators) could be avoided by leaving the TWTAs on during close-approach to the Sun, or locally heating the area – thereby reproducing the deformation seen during thermal case D2. This will be verified in future work. Also note that the non-compliance of the APE during thermal case D6 should be viewed in the context of the suggested change to the MRD reported in [IR43], whereby the requirement is interpreted to be relaxable as the SC moves away from the Sun (the requirement is driven by the occulter-sizing on the METIS instrument). If the recommended updated APE requirement at ~0.8 AU is taken (~7-8 arcminutes), then the APE is easily compliant also for thermal case D6.

0

1

2

3

4

5

6

7

8

9

0.2343 0.3343 0.4343 0.5343 0.6343 0.7343 0.8343 0.9343

Sun Distance (AU)

AP

E R

equi

rem

ent (

arcm

inut

es)

0

0.5

1

1.5

2

2.5

Sol

ar D

isc

(deg

rees

)

APE RequirementSolar Disc (degrees)

Figure 2.13-2: Assumed relationship between Sun distance and APE LoS requirement





2.13.2.2 APE Around LoS

The APE performance around the LoS has yet to be calculated. However, given that TED contributions are not expected to exceed 2-3 arcmin, the 20’ APE requirement around X is expected to be easily met.

2.13.3 PDE Budget [POIN30b]

2.13.3.1 PDE LoS

TBC.

2.13.3.2 PDE Around LoS

TBC.





2.13.4 Instrument Co-alignment Budget

This budget presents the contributions to the RS-instrument co-alignment requirement POIN45 of within 2 arcminutes. The requirement is interpreted as an allowable misalignment of 2 arcmins between any two of the RS-instruments LoS (SPICE, STIX, METIS, EUI …). Accordingly, in combination with POIN30a, this implies that any one of the instruments can be misaligned from the commanded attitude by up to 4 arcmins. The following figure pictorially represents the interpretation of the requirements.

Figure 2.13-3: POIN45 interpretation and relationship with POIN30a

In addition to the misalignment caused by TED, the following budget items are also included:

• Gravity release • Launch slippage • AIT alignment (including error internal to instrument) • Co-alignment.

When these budget items are added to the TED (quadratically), the total worst-case co-alignment budget (corresponding to Case D1) is as shown in the following tables.

Commanded Attitude

METIS

STIX EUI

SPICE

PHI

2’ 2’

2’

2’

2’

2’ 2’

2’

2’

2’ 2’






Error Type Class

Contribution Units Data source

Systematic




Typical AIT alignment U 33.0 arcsec Typical achieved by AIT (To include structure build and alignment requirement/interface alignment?)

Worst-Case TED between any two instruments 43.0


Allocation 120.0 arcsecs

Table 2.13-9: Worst case coalignment budget, corresponding to thermal case D1 (“Hot1”)





Hot 1 Misalignment in

arcsec

PHI SPICE COR EUI STIX STIX_DET

PHI 0 36 27 15 13 12

SPICE 0 18 21 39 43

COR 0 14 25 30

EUI 0 20 22

STIX 0 5

STIX_DET 0

Table 2.13-10: Thermal case D1 (“Hot1”) RS-instrument TED misalignments

Hot 2 Misalignment in

arcsec


PHI 0 23 25 13 20 16

SPICE 0 4 10 21 19

COR 0 13 20 20

EUI 0 15 12

STIX 0 4

STIX_DET 0

Table 2.13-11: Thermal case D2 (“Hot2”) RS-instrument TED misalignments

Cold Misalignment in

arcsec


PHI 0 16 13 2 11 16

SPICE 0 10 15 10 5

COR 0 11 2 13

EUI 0 9 14

STIX 0 12

STIX_DET 0

Table 2.13-12: Thermal case D6 (“Cold”) RS-instrument TED misalignments





2.14 Science Windows

The following tables present the characteristics of each of the science windows for the 2017 and 2018 mission scenarios, according to a strict interpretation of requirement PERF20 of the MRD [AD01]. The information held here has been generated through interrogation of the trajectory files of which [RD6] is the report. There are two important features to note:

• Several of the early minimum latitude and perihelion science windows are overlapping; as the perihelion of the SC increases, the overlap reduces and eventually disappears

• In the 2017 case a 4:3 resonance is entered after VGAM-2, such that 4 SC orbits are prescribed before the next VGAM – there are thus 14 operational orbits in total for the 2017 mission. This is in comparison to the backup 2018 mission in which a 3:2 resonance is entered directly after VGAM-2 and which therefore contains 13 operational orbits in total.

Colour coding:

• Dark Grey: NMP science windows • Light Grey: EMP science windows.

2.15 2017 Mission

Date (midpoint) Day (midpoint) S/C-E distance (AU) S/C-S dist. (AU) S-S/C-E (°) Solar Latitude (°)

Min Max Min Max Beg. End Begin End

07/05/2021 1584.0 0.819 0.827 0.712 0.800 22.770 23.360 7.700 7.640

22/10/2021 1752.0 0.262 0.354 0.717 0.804 104.710 116.830 7.690 7.650

09/04/2022 1921.0 1.179 1.289 0.712 0.800 7.240 7.090 7.700 7.640

24/09/2022 2089.0 1.424 1.495 0.717 0.804 156.010 159.860 7.690 7.660

09/03/2023 2255.1 0.558 0.614 0.497 0.627 16.330 23.680 16.660 16.310

06/08/2023 2405.1 0.738 0.762 0.494 0.625 81.350 80.650 16.670 16.270

02/01/2024 2554.1 1.223 1.351 0.506 0.634 57.860 70.160 16.630 16.400

26/05/2024 2698.5 0.474 0.524 0.510 0.624 32.590 28.630 25.230 24.680

23/10/2024 2848.5 0.849 0.871 0.508 0.622 126.310 141.440 25.250 24.630

22/03/2025 2998.5 1.187 1.306 0.505 0.620 14.530 21.220 25.270 24.580

09/08/2025 3138.9 0.400 0.436 0.519 0.615 81.110 76.210 31.260 30.450

05/01/2026 3287.9 0.965 0.981 0.528 0.621 57.220 69.710 31.150 30.720

04/06/2026 3437.9 1.147 1.252 0.525 0.620 39.280 34.420 31.180 30.650

22/10/2026 3578.3 0.390 0.393 0.504 0.585 116.830 127.060 34.550 33.610

Table 2.15-1: Maximum latitude science window definition for the 2017 launch case







19/06/2021 1627.0 0.468 0.596 0.257 0.298 25.730 95.970 -2.830 -7.280

04/12/2021 1795.0 0.667 0.962 0.257 0.292 122.730 44.180 -2.290 -7.430

22/05/2022 1964.0 0.929 0.985 0.257 0.298 47.130 125.380 -2.780 -7.300

07/11/2022 2133.0 0.512 0.846 0.257 0.304 85.730 16.970 -3.270 -7.140

04/04/2023 2281.1 0.466 0.750 0.234 0.285 80.100 163.060 -0.190 -16.550

01/09/2023 2431.1 0.889 0.979 0.234 0.288 39.050 34.190 -0.730 -16.480

28/01/2024 2580.1 0.555 0.898 0.234 0.277 147.250 98.050 1.360 -16.710

23/06/2024 2726.5 0.448 0.729 0.270 0.305 18.700 78.000 -1.840 -25.310

20/11/2024 2876.5 0.952 0.998 0.270 0.307 104.360 41.330 -2.500 -25.360

18/04/2025 3025.5 0.579 0.867 0.270 0.299 68.010 136.620 0.140 -25.080

08/09/2025 3168.9 0.458 0.710 0.316 0.337 36.220 17.140 -2.950 -29.320

05/02/2026 3318.9 1.024 1.035 0.316 0.339 155.560 123.130 -3.600 -29.550

05/07/2026 3468.9 0.577 0.799 0.316 0.340 13.480 54.950 -4.250 -29.770

20/11/2026 3607.3 0.504 0.704 0.359 0.372 103.490 68.050 0.920 -26.280

Table 2.15-2: Perihelion science window definition for the 2017 launch case



23/06/2021 1631.0 0.478 0.693 0.257 0.354 54.440 114.210 -6.520 -5.630

08/12/2021 1799.0 0.793 1.050 0.257 0.346 89.220 26.060 -6.140 -5.870

26/05/2022 1968.0 0.899 0.973 0.257 0.353 77.870 148.910 -6.490 -5.660

10/11/2022 2136.0 0.429 0.746 0.257 0.345 63.440 5.300 -6.100 -5.900

09/04/2023 2286.1 0.583 0.892 0.236 0.363 131.680 133.080 -13.280 -13.140

06/09/2023 2436.1 0.950 0.997 0.237 0.366 5.460 51.000 -13.650 -12.980

03/02/2024 2586.1 0.394 0.693 0.238 0.369 139.240 64.140 -14.000 -12.810

30/06/2024 2733.5 0.637 0.912 0.280 0.394 61.100 104.440 -22.480 -21.230

27/11/2024 2883.5 0.992 1.012 0.281 0.396 57.710 18.420 -22.810 -21.030

25/04/2025 3032.5 0.414 0.665 0.276 0.385 117.110 147.180 -21.370 -21.830

18/09/2025 3178.9 0.710 0.940 0.337 0.432 17.140 36.190 -29.320 -28.030

15/02/2026 3328.9 1.030 1.034 0.339 0.434 123.130 78.320 -29.550 -27.840

14/07/2026 3477.9 0.415 0.598 0.333 0.426 51.050 81.090 -28.520 -28.570

05/12/2026 3622.3 0.810 0.990 0.400 0.480 52.940 32.030 -33.390 -32.630

Table 2.15-3: Minimum latitude science window definition for the 2017 launch case





2.16 2018 Mission

Date (midpoint) Day (midpoint) S/C-E distance S/C-S dist. S-S/C-E (°) Solar Latitude (°)


19/02/2022 1300.0 1.202 1.335 0.485 0.614 5.130 10.550 10.060 10.080

19/07/2022 1450.0 0.754 0.779 0.488 0.616 111.270 90.260 10.080 10.070

16/12/2022 1600.0 0.521 0.574 0.491 0.619 51.440 53.320 10.090 10.060

20/05/2023 1755.0 1.201 1.321 0.511 0.625 55.860 44.910 20.090 20.020

17/10/2023 1905.0 0.833 0.864 0.513 0.627 103.510 105.130 20.120 20.000

14/03/2024 2054.0 0.463 0.510 0.503 0.618 14.060 8.830 19.990 20.080

21/08/2024 2214.0 1.167 1.273 0.533 0.626 135.550 117.320 27.530 27.250

18/01/2025 2364.0 0.947 0.975 0.535 0.628 29.630 33.650 27.570 27.210

16/06/2025 2513.0 0.391 0.423 0.527 0.621 76.340 62.680 27.410 27.350

24/11/2025 2674.0 1.075 1.183 0.520 0.598 66.680 72.740 31.790 31.270

22/04/2026 2823.0 1.035 1.046 0.513 0.592 40.350 29.750 31.570 31.480

19/09/2026 2973.0 0.367 0.368 0.515 0.593 123.460 127.010 31.630 31.430

26/02/2027 3133.0 0.952 1.083 0.479 0.551 17.610 19.520 32.820 32.200

Table 2.16-1: Maximum latitude science window definition for the 2018 launch case



27/01/2022 1277.0 0.604 0.938 0.243 0.290 103.500 26.830 -9.580 4.050

26/06/2022 1427.0 0.859 0.975 0.244 0.293 81.730 177.900 -9.460 4.280

22/11/2022 1576.0 0.447 0.692 0.243 0.283 45.900 22.380 -9.870 3.310

24/04/2023 1729.0 0.598 0.897 0.271 0.303 146.150 114.350 -18.540 5.090

21/09/2023 1879.0 0.918 0.994 0.271 0.305 15.180 70.180 -18.300 5.550

18/02/2024 2029.0 0.425 0.668 0.271 0.308 119.000 49.820 -18.050 5.990

23/07/2024 2185.0 0.611 0.849 0.315 0.339 67.930 121.060 -21.980 4.980

19/12/2024 2334.0 1.000 1.030 0.315 0.334 53.510 10.920 -23.410 2.810

18/05/2025 2484.0 0.439 0.684 0.315 0.335 125.180 154.520 -23.070 3.360

26/10/2025 2645.0 0.595 0.779 0.362 0.377 12.530 34.170 -19.440 6.720

24/03/2026 2794.0 1.069 1.074 0.362 0.374 126.180 86.620 -21.180 4.670

21/08/2026 2944.0 0.488 0.691 0.362 0.374 53.360 86.620 -20.760 5.180

02/02/2027 3109.0 0.550 0.717 0.388 0.398 55.150 31.280 -10.580 14.250

Table 2.16-2: Perihelion science window definition for the 2018 launch case







20/01/2022 1270.0 0.401 0.711 0.244 0.356 148.160 77.630 -9.170 -6.650

19/06/2022 1420.0 0.951 1.007 0.244 0.352 40.860 110.440 -9.240 -6.370

16/11/2022 1570.0 0.563 0.870 0.243 0.349 72.020 17.250 -9.320 -6.080

17/04/2023 1722.0 0.416 0.691 0.272 0.365 98.330 168.250 -19.220 -13.340

13/09/2023 1871.0 0.985 1.019 0.274 0.376 21.860 25.070 -18.740 -15.060

10/02/2024 2021.0 0.606 0.892 0.274 0.373 159.680 103.880 -18.860 -14.650

12/07/2024 2174.0 0.391 0.588 0.329 0.418 28.760 63.070 -26.250 -23.730

09/12/2024 2324.0 1.030 1.040 0.327 0.416 84.600 53.510 -26.370 -23.410

08/05/2025 2474.0 0.684 0.926 0.326 0.413 75.850 125.180 -26.490 -23.070

10/10/2025 2629.0 0.378 0.500 0.395 0.472 35.380 19.990 -31.090 -29.450

09/03/2026 2779.0 1.063 1.068 0.394 0.471 128.710 138.600 -31.190 -29.240

06/08/2026 2929.0 0.799 0.985 0.393 0.469 20.620 39.140 -31.280 -29.020

10/01/2027 3086.0 0.363 0.415 0.458 0.529 96.510 82.960 -32.930 -31.560

Table 2.16-3: Minimum latitude science window definition for the 2018 launch case





2.17 Mass Memory Usage Profile

The mass memory profiles are presented here for the baseline operational scenario (stowage of the HTHGA below 0.3 AU.) for the new 2017 baseline mission scenario, and the 2018 backup mission scenario [ref]. The analysis was performed under the following assumptions:

• Data-rates: o 6 kbps for SC housekeeping, which is a constant data-rate o 23 kbps for IS suite observations, which are considered to be permanently collecting data o 77 kbps for RS suite baseline observations, which occur at the points in the trajectory as

defined by the science window schedules given in the previous section o ¼ turbo coding.

• TT&C capability: o 150 kbps @ 1AU reference data rate o 4 hour communication window available per day, subject to the following constraints:

� A minimum visibility of either New Norcia or Cerbera of at least 10º above the local horizon

� Greater than 5º S/SC/E angle (scintillation effects assumed to prevent communication below this).

The baseline sizing of the mass memory is therefore 491Gb, occurring at MoL in the baseline 2017 mission. It should be noted that appropriate use of a 2nd ground station during this critical period will substantially reduce the SSMM peak usage.





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Figure 2-4: SSMM usage for the 2017 baseline mission scenario

333 Gbits

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Figure 2-5: SSMM usage for the 2018 backup mission scenario

Documents

SOL-S-ASTR-TN-0010 Solar Orbiteremits.sso.esa.int/emits-doc/ESTEC/AO6309_AD2.pdf · SOL-S-ASTR-TN-0010 - Solar Orbiter System Budgets - Issue 2.doc 2.2 Mass Budget The mass budget