Attachment Debris mitigation

This document pretains to SES-LFS-20151020-00734 for License to use Foreign Satellite (earth) on a Satellite Earth Station filing.

IBFS_SESLFS2015102000734_1111282

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : I PROBA-V SPACE DEBRIS MITIGATION DOCUMENT EN-34-VES EUROPEAN SPACE AGENCY CONTRACT REPORT This document may only be copied, distributed and utilised or its contents communicated to others either with prior written permission of Verhaert Design & Development or in accordance with the terms of ESA contract no. 22218/09/NL/GLC. Offenders will be held liable for payment of damages. All rights reserved, in particular the right to carry out patent, utility model or ornamental design registration. The work described in this report was done under ESA contract. Responsibility for the contents resides in the author or organisation that prepared it. Company: Signature: Date: Prepared by : D. VRANCKEN QINETIQ SPACE Checked by : D. GERRITS QINETIQ SPACE Approved by : L. BIERQUE QINETIQ SPACE Prod. Ass.: T. DEBRAEKELEER QINETIQ SPACE Proj. Man. D. VRANCKEN QINETIQ SPACE Customer approval: Please insert revised page(s) and remove old page(s) X Re-issued document, distributed in its entirety

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : II DISTRIBUTION LIST Quantity Company Department Name 2 ESA M. SNAAYER 1 QINETIQ SPACE ARCHIVE CHANGE RECORD Iss. Rev. Date # Pages affected P. Description A 0 21/02/200 IX+14 All First issue 9 B 0 23/03/200 IV+14 All Compliance matrix updated 9 C 0 30/06/200 IV+15 Update for PDR 9 16 A waiver request on Requirement OR- 01 is added in Appendix E. D 0 14/07/09 IV+16 16 Signed waiver request by ESA-DG is added in the appendix. Update for CDR, update of the E 0 29/03/10 IV+15 2 applicable documents F 0 30/01/13 IV+16 all Update for FAR G 0 18/02/13 IV+16 10, 15 Updated casualty risk analysis Documentation control procedure: Changes to the present document will be sent to all registered recipients (all persons on the distribution list). Text amendments with respect to the previous issue are identified by a vertical bar in the right margin. Minor text amendments like underlining, punctuation, spelling, page numbers and deletions are not marked however.

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : III TABLE OF CONTENTS 1. SCOPE 1 2. DOCUMENTS 2 2.1 Applicable documents 2 2.2 Reference documents 4 3. INTRODUCTION 5 4. SPACE DEBRIS MITIGATION REQUIREMENTS 6 5. CONCLUSION 11 APPENDIX A: TERMS AND DEFINITIONS 12 APPENDIX B: DESIGN REQUIREMENTS- DEORBITING 13 APPENDIX C: OPERATIONAL REQUIRMENTS-END OF LIFE MEASURES 14 APPENDIX D: RE-ENTRY ANALYSIS 15 APPENDIX E: WAIVER- REQUIREMENT “OR-1” 16

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : IV LIST OF ABBREVIATIONS The complete list of PROBA-V abbreviations is given in PROBAV-LI-00207-VE.

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : 1 1. SCOPE The scope of this document is to formulate and respond to “the requirements for space debris mitigation” for ESA projects. [AD 8] This document primarily deals with the list of compliance and non-compliances with respect to space debris mitigation requirements and it includes a description of design and operational measures. PROBA-V does not include on-board propulsion therefore any requirements relating to propulsion are not relevant to this mission. For example the following manoeuvres shall not be performed on PROBA-V. 1) De-orbiting at EOL and 2) Collision avoidance.

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : 2 2. DOCUMENTS 2.1 APPLICABLE DOCUMENTS The following documents are to be considered as applicable to the extent specified within. AD Doc Nr Issue/ Title Rev. AD-1 RFQ NO.: 3- 3/1 PROBA Vegetation Statement of Work 12558/08/NL/GLC AD-2 PV-RS-ESA-SY-0001 3/0 Draft Mission Requirements Document (MRD) AD-3 PV-RS-ESA-SY-0002 3/0 Draft System Requirements Document (SRD) AD-4 PV-RS-ESA-SY-0003 1/0 PROBA-V PA Requirements + Amended PA Requirements AD-5 PV-RS-ESA-SY-0004 2/0 PROBA-V Management Requirements Document AD-6 PV-LI-ESA-SY-0002 2/0 PROBA-V Document Requirement List and Document Requirement Description AD-7 PV-LI-ESA-LI-0001 2/0 ECSS E Applicability to PROBA-V AD-8 ESA/ADMIN/IPOL 2 2008 Requirements on Space Debris Mitigation for ESA ANNEX 2 projects AD-9 PROBAV-PL-00036-VE E/0 PROBA-V Product Assurance and Safety Plan AD-10 PROBAV-PL-00047-VE A/0 PROBA-V Configuration Management and Control Plan AD-11 PROBAV-SP-00651-VE D/1 Generic Equipment Requirements Specification AD-12 PROBAV-LI-00686-VE A/0 ECSS List of applicability AD-13 PROBAV-TN-00159-VE D/1 Definition of reference frames and control errors AD-14 PROBAV-SP-00085-VE D/0 Reaction wheels unit requirements AD-15 PROBAV-SP-00235-VE C/0 Magnetotorquer unit requirements AD-16 PROBAV-SP-00236-VE C/0 Magnetometer unit requirements AD-17 PROBAV-SP-00238-VE D/0 GPS receiver unit requirements AD-18 PROBAV-SP-00239-VE C/0 GPS antenna unit requirements AD-19 PROBAV-SP-00240-VE C/0 Star tracker unit requirements AD-20 PROBAV-SP-00237-VE C/0 AIE unit requirements AD-21 PROBAV-SP-00087-VE E/1 AOCS SW requirement specification

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : 3 AD Doc Nr Issue/ Title Rev. AD-22 PROBAV-SP-00233-VE D/0 S-band antenna unit requirements AD-23 PROBAV-SP-00214-VE D/1 S-band transceiver unit requirements AD-24 PROBAV-SP-00243-VE C/0 X-band antenna unit requirements AD-25 PROBAV-SP-00215-VE C/2 Battery unit requirements AD-26 PROBAV-SP-00224-VE E/1 Photo Voltaic Assembly unit requirements AD-27 PROBAV-SP-00275-VE C/3 Specific ADPMS requirements AD-28 PROBAV-SP-00766-VE C/0 Specific reaction wheels power supply requirements AD-29 PROBAV-SP-00091-VE A/0 Satellite harness specification AD-30 PROBAV-RP-00273-VE F/0 CDMS use cases AD-31 PROBAV-SP-00242-VE C/0 System requirements specification AD-32 PROBAV-ICD-00126-VE F/0 Vegetation instrument requirements

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : 4 2.2 REFERENCE DOCUMENTS RD Doc Nr Issue Revision Title Date 1 PROBAV-RP-00077-A4-VE 30/06/09 C/0 Mission analysis report 2 Space Mission Analysis and 1999 - Space Mission Analysis and Design Design 3 In-house Matlab Tool 04/2009 1.1 In-house Matlab tool to perform Mission analysis. 4 DAS 2.0.1 05/2008 2.0.1 Debris Assessment Software, NASA, R. O’Hara, M. Matney and P. Anz-Meador.

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : 5 3. INTRODUCTION The PROBA-V (PRoject for On Board Autonomy-Vegetation) mission architecture is based on the PROBA Platform carrying the Vegetation instrument as the main payload. The PROBA-V Platform is a small satellite platform of about 160 kg with a size of 800x800x1000 mm³. The PROBA-V satellite is targeted to be launched by early 2013 as primary passenger of the VEGA launcher; it will be placed directly into its operational orbit, with an altitude of 820 km. The Flight segment is designed to operate for 2 and ½ years in- orbit with the possibility to extend the mission life time up to 5 years. PROBA-V is an ESA project and should comply with the European code of conduct for space debris mitigation. In the next chapter, the requirements of Space Debris Mitigation are specified w.r.t PROBA-V. Director General of ESA shall specifically approve all requirements, when Partial Compliance (PC) or Non Compliance (NC) are stated.

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : 6 4. SPACE DEBRIS MITIGATION REQUIREMENTS General space debris mitigation requirements for the PROBA-V mission are extracted in Table 4.1, Table 4.2 and Table 4.3. They include management requirements, design requirements and operating requirements, respectively. Table 4.1: Space debris mitigation- Management requirements No# REQUIREMENTS C PC NC Comments MANAGEMENT REQUIREMENTS MR-01 The prime contactor of the space project shall be responsible for the implementation of space debris mitigation measures as defined in this document. The prime contractor shall deal with these X requirements using the same engineering methodology and the same reporting as for all other contractually applicable Agency requirements. MR-02 In order to implement the space debris mitigation measures defined in this document the space project prime contractor shall: a) define derived design requirement specifications at system and sub-system level; b) verify compliance with the design requirements; X c) define and verify necessary operational procedures prior to launch; d) document activities and procedures resulting from a, b, and c. MR-03 Verification of and compliance with the applicable space debris mitigation requirements shall be reported by the space project prime contractor as part of the overall space project verification X control up to Flight Acceptance Review. MR-04 The space project prime contractor shall document in a “Space Debris Mitigation Document” the measures put in place to implement and fulfil the applicable requirements. The document X shall be part of the Design Justification File. MR-05 The Space Debris Mitigation Document shall: a) be provided for and reviewed at the space project System Requirements Review; b) be updated for and reviewed at the space project Preliminary Design Review; X c) be updated and revised by the space project prime contractor to follow the design evolution of the space project; d) be updated for and reviewed at the space project Critical Design Review.

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : 7 MR-06 The Space Debris Mitigation Document shall contain as a minimum: a) a table of compliance with the requirements in the present document; b) a description of design and operational measures put in place to achieve compliance; c) a list of objects (mission-related objects or space debris) X released as part of the nominal mission. For these objects, the physical characteristics, the orbital characteristics and the predicted on-orbit lifetime shall be provided; d) a feared-events list of malfunctions of the space system which have the potential to cause space debris, and a description of the characteristics of the debris so caused.

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : 8 Table 4.2: Space debris mitigation - Design requirements [AD 8] No# REQUIREMENTS C PC NC Comments DESIGN REQUIREMENTS DR-01 a) For the launch of a single payload there shall be at most one additional launch vehicle element (for example the To be justified by the insertion stage) injected into orbit. launcher authorities. b) For the launch of multiple payloads there shall be at N/A Launch is not directly most two additional launch vehicle elements (for example procured by the the insertion stage and an adaptation structure for multiple PROBA-V project. payloads) injected into orbit. DR-02 Spacecraft shall be designed such that objects that must be released as part of the nominal mission are retained and do not become detached from the spacecraft. In cases where this is not possible for technical or operational reasons the Point (a) is not following requirements apply: applicable to PROBA-V a) mission-related objects and space debris so generated Point (b) compliant; no shall remain outside the GEO protected region X objects released from b) mission-related objects and space debris so generated the PROBA-V S/C. shall not remain in the LEO protected region for more than Point (c) No debris is 25 years after their release; released from the c) a justification for the implementation shall be given in the PROBA-V. space debris mitigation document DR-03 A space system or any of its parts shall not be intentionally No destruction destroyed in orbit. mechanism is X implemented on the S/C. DR-04 Solid rocket motors releasing burn products larger than No solid propellants are 1mm into orbit shall not be used. X used on PROBA-V DR-05 The use of pyrotechnics (for example, pyrotechnic cutters) No pyrotechnics shall not release into orbit any particles greater than 1 mm. X present on PROBA-V DR-06 The system shall be designed such that the end-of-life Only end-of-life measures shall be fulfilled by the operator. X passivation DR-07 An analysis shall be performed to determine and allocate Analysis has been the amount of propellant needed to perform the required performed and is end-of-life manoeuvres. shown in APPENDIX B: Design X requirements- Deorbiting. However, no propulsion system is implemented on the PROBA-V S/C DR-08 The design shall allow the operator to establish the propellant reserve with accuracy, which is compatible with Not applicable, since performing the end-of-life manoeuvres. there is no onboard N/A propulsion to comply with accuracy and EOL manoeuvres. DR-09 Space system shall be designed such that it can be End-of-life passivation permanently passivated at the end of its disposal phase. C operations are

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : 9 described in the ‘Specific Operations Document’ PROBAV- TN-05177-QS_B0 section 16. DR-10 The reliability of successfully performing the end-of-life disposal and/or passivation shall not be less than the C nominal mission reliability for the operational phase. Table 4.3: Space debris mitigation - Operational requirements [AD 8] No# REQUIREMENTS C PC NC Comments OPERATIONAL REQUIREMENTS OR-01 Space systems operating in the LEO protected region shall Non compliance as be disposed of by re-entry into the Earth’s atmosphere there is no onboard within 25 years after the end of the operational phase. propulsion system. See APPENDIX C: Operational requirments-End X of life measures A waiver has been generated by ESA [APPENDIX E: Waiver- Requirement “OR-1”]. OR-02 Space systems operating in the GEO protected region shall be disposed of by permanently removing them from the N/A PROBA-V is a LEO GEO protected region. satellite. OR-03 Where practicable and economically feasible, space systems outside the LEO and GEO protected regions shall N/A, as PROBA-V is a implement means of end-of-life orbit disposal to avoid long- N/A LEO satellite. term interference with operational orbit regions, such as the Galileo orbit. OR-04 Launcher stages shall satisfy one of the following conditions: a) they shall perform a direct re-entry as part of the To be justified by the launcher sequence; launcher authorities. b) they shall be placed in a LEO orbit where they will re- N/A Launch is not directly enter the Earth’s atmosphere within 25 years; procured by the c) they shall be permanently removed from the LEO and PROBA-V project. GEO protected regions, and from orbits interfering with other operational orbit regions, such as the Galileo orbit. OR-05 Passivation of a space system shall be completed within Compliant for End-of- two months after the end of the operational phase. This Life passivation. For includes launcher stages which remain in orbit. launcher stages: to be justified by the C launcher authorities. Launch is not directly procured by the PROBA-V project.

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : 10 OR-06 For space systems that are disposed of by re-entry, the Casualty risk is prime contractor shall perform an analysis to determine the 1:11700 see characteristics of fragments surviving to ground impact, and X [APPENDIX D: Re- assess the total casualty risk to the population on ground assuming an uncontrolled re-entry. entry analysis] Terms and definitions related to the space debris requirements are in APPENDIX A: Terms and definitions

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : 11 5. CONCLUSION PROBA-V is a mini satellite with a maximum size of 1000 x 800 x 800 mm³. The orbit drift analysis [RD 1] showed that there is no on-board propulsion system needed for orbit correction and maintenance, in case the spacecraft is injected into a quasi SSO. Thus, propulsion on-board has not been considered and PROBA-V shall remain in orbit after EOL. End-of-Life passivation operations have been defined. Passivation of the launch vehicle stages is a concern to launch authorities. It shall be performed by the relevant launch authority. The launch is not directly procured by the PROBA-V project. All requirements are compliant except OR-01, for which ESA-Project has introduced a waiver, which is in Appendix .

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : 12 APPENDIX A: TERMS AND DEFINITIONS Terms and definitions used in the document to represent requirements are: 1. Disposal Phase: Begins at the end of the operational phase of the Space System and ends when either the Space System has performed a direct re- entry or completed its disposal activities (having reached its disposal orbit and having completed its passivation). 2. End of Life: End of the disposal phase. 3. LEO: Low Earth Orbit, with an altitude below 2000 km. 4. Mission-Related Objects: Protection or adaptor structures or mechanisms required for the deployment of one or several payloads into orbit. 5. Operational Phase: The period during which a space system performs its useful function. 6. Orbital Lifetime: The length of time that a space system remains in orbit. 7. Passivation: The elimination of all stored energy on-board of a space system. 8. Space System: Spacecraft, launch vehicle stages, and mission-related objects. 9. Space Debris: Any man-made space object, including fragments and elements thereof, in Earth orbit or re-entering the Earth’s atmosphere that is non- functional.

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : 13 APPENDIX B: DESIGN REQUIREMENTS- DEORBITING According to the space debris mitigation [AD 8], a satellite in a LEO should either re- enter in the earth’s atmosphere or be disposed at an altitude of less than 600km or greater than 2500 km. As, PROBA-V is at an altitude of 820 km, de-orbiting to 600 km is less expensive than boosting the satellite to 2500 km. A single long retro thrust manoeuvre or a high impulse retro thrust manoeuvre at apogee results in a decreased perigee altitude, thus a set of manoeuvres can bring the perigee of the satellite to an altitude of 550-600 km, causing more atmospheric drag on the satellite. This is shown in Figure A.0.1. The final orbit, after de-orbiting shall be an elliptical orbit with apogee at 820 km and perigee at 600km. Delta-V required in this strategy is given by: [RD 2] ⎛ 2 ⋅ (Re + H deorbit ) ⎞ ΔVdeorbit = V ⋅ ⎜1 − ⎟ (0.1) ⎜ (Re + H deorbit ) + r ⎟⎠ ⎝ Where, V is velocity of initial orbit in m/s, r is the radius of the initial orbit in km, Re is the radius of the Earth, 6378 km Hdeorbit = Altitude of the de-orbiting orbit. Table A.0.1 summarizes the delta-V required to de-orbit PROBA-V to various altitudes: Table A.0.1: Delta-V de-orbiting H H deorbit Delta-V [km] [km] [m/s] 820 600 57.84 820 590 60.54 820 580 63.24 820 570 65.95 820 560 68.66 820 550 71.38 Figure A.0.1: Multiple apogee burn strategy Therefore, with a margin of 20%, the total delta-V required to de-orbit to 600km is 69.4m/s.

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : 14 APPENDIX C: OPERATIONAL REQUIRMENTS-END OF LIFE MEASURES According to the European Code of Conduct for Space Debris Mitigation [AD 8] spacecraft in LEO should be de-orbited, i.e. allowed to fall into the atmosphere and burn up, within 25 years of the end of the mission. In other words, the spacecraft should de-orbit to an altitude range of 550 km-600 km at End Of Life (EOL). As there is no propulsion on PROBA-V, natural decay of orbit from 820 km is more than 250 years. Hence the spacecraft is non-compliant to the requirement OR-03 of “European Code Of Conduct For Space Debris Mitigation”. [AD 8]. Natural decay of PROBA-V from an altitude of 820 km is shown in Figure A.0.1 Figure A.0.1: Natural decay of PROBA-V from 820 km for 200 years [RD 3]

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : 15 APPENDIX D: RE-ENTRY ANALYSIS A re-entry analysis has been performed using the “DAS 2.0” (Debris Assessment Software) software. The results are shown in the table below. A casualty risk of 1:11.700 is obtained, which is smaller than the requirement of 1:10.000. The PROBA-V satellite is as such compliant with the requirements. Reentry Data Row Num Name Parent Qty Material Body Type Thermal Mass Diameter/Width Length Height Status Risk Demise Alt Total DCA KE 1 PROBA‐V 0 1 Aluminum (generic) Box 145 0.7 0.834 0.68 Compliant '1:11700' 6.65 2 Bottom Board 1 1 Aluminum (generic) Flat Plate 12.63 0.65 0.68 68.3 0.00 0 3 Bus panel 2 1 Aluminum (generic) Flat Plate 13.92 0.61 0.8 58.6 0.00 0 4 AIE 3 1 Aluminum (generic) Box 3.38 0.2 0.3 0.1 0.0 0.66 2650 5 S‐band transceiver 3 1 Aluminum (generic) Box 6.22 0.187 0.257 0.13 0.0 0.64 9378 6 X‐band transmitters 3 3 Aluminum (generic) Box 1.02 0.115 0.16 0.046 0.0 1.53 826 7 Magneto‐torquers 3 1 Iron Cylinder 0.24 0.014 0.325 0.0 0.45 140 8 ADPMS 3 1 Aluminum (generic) Box 15.4 0.218 0.444 0.212 0.0 0.83 30483 9 Harness 3 1 Copper Alloy Cylinder 5.7 0.02 3 54.4 0.00 0 10 Central panel 2 1 Aluminum (generic) Flat Plate 1.75 0.23 0.8 66.3 0.00 0 11 Reaction wheels 10 4 Aluminum (generic) Box 0.75 0.1 0.105 0.07 59.8 0.00 0 12 EPT 10 1 Aluminum (generic) Box 4.57 0.129 0.242 0.125 51.9 0.00 0 13 Battery 10 1 Aluminum (generic) Box 3.48 0.15 0.2 0.095 48.0 0.00 0 14 Payload panel 2 1 Aluminum (generic) Flat Plate 6.05 0.61 0.8 64.6 0.00 0 15 VI + radiator + Star Tracker 14 1 Aluminum (generic) Box 25.52 0.5 0.8 0.2 0.0 1.27 25096 16 PSU 14 1 Aluminum (generic) Box 3.1 0.2 0.2 0.2 0.0 0.64 1813 17 DHU 14 1 Aluminum (generic) Box 2 0.2 0.25 0.1 0.0 0.63 1021 18 ROEs 14 3 Aluminum (generic) Box 1.2 0.136 0.180 0.04 51.9 0.00 0 19 ADS‐B elec 14 1 Aluminum (generic) Box 1 0.140 0.170 0.06 56.0 0.00 0 20 ST DPU 14 1 Aluminum (generic) Box 0.64 0.1 0.112 0.04 56.5 0.00 0 21 Harness 14 1 Copper Alloy Cylinder 2.12 0.02 2 62.8 0.00 0 22 Flexible Fingers 2 6 Steel A‐286 Box 0.4 0.025 0.1 0.025 62.3 0.00 0 23 S‐band antenna 2 1 Aluminum (generic) Cylinder 0.4 0.06 0.07 63.5 0.00 0 24 GPS antenna 2 2 Aluminum (generic) Cylinder 0.33 0.089 0.03 64.5 0.00 0 25 Satram 2 1 Aluminum (generic) Box 0.38 0.05 0.1 0.05 65.0 0.00 0 26 Top panel 1 1 Aluminum (generic) Flat Plate 3.15 0.61 0.61 74.5 0.00 0 27 Flexible fingers 26 8 Steel A‐286 Box 0.4 0.025 0.1 0.025 62.9 0.00 0 28 Magnetotorquers 26 2 Iron Cylinder 0.24 0.014 0.325 66.0 0.00 0 29 Hermod 26 1 Aluminum (generic) Box 0.9 0.115 0.16 0.046 66.1 0.00 0 30 X‐band antennas 26 3 Aluminum (generic) Cylinder 0.44 0.05 0.2 69.5 0.00 0 31 S‐band antenna 26 1 Aluminum (generic) Cylinder 0.4 0.06 0.07 65.7 0.00 0 32 Nadir panel 1 1 Aluminum (generic) Flat Plate 2.3 0.475 0.820 75.3 0.00 0 33 ADS‐B antenna 32 2 Aluminum (generic) Flat Plate 0.19 0.1 0.1 66.5 0.00 0 34 LRR 32 1 Aluminum (generic) Cylinder 0.33 0.15 0.05 69.3 0.00 0 35 Velocity Panel 1 1 Graphite Epoxy 1 Flat Plate 3.95 0.764 0.834 77.4 0.00 0 36 Zenith Panel 1 1 Graphite Epoxy 1 Flat Plate 3.75 0.68 0.834 77.4 0.00 0 37 Anti‐Velocity Panel 1 1 Graphite Epoxy 1 Flat Plate 3.70 0.68 0.834 77.4 0.00 0

PROBA-V Space Debris Mitigation Document Ref. : PROBAV-RP-00098-QS Iss. : G Rev. :0 Date : 18/02/2013 Page : 16 APPENDIX E: WAIVER- REQUIREMENT “OR-1”


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