Attachment Attach D-ODAR

This document pretains to SAT-LOA-20190807-00072 for Application to Launch and Operate on a Satellite Space Stations filing.

IBFS_SATLOA2019080700072_1833524

YAM ODAR – Version 1.0 ATTACHMENT D YAM Orbital Debris Assessment Report (ODAR) YAM-ODAR-1.0 This report is presented as compliance with NASA-STD-8719.14, APPENDIX A. Report Version: 1.2, 8/21/2017 Loft Orbital Solutions Inc. (Loft Orbital) 715 Bryant Street, Suite 202 San Francisco, CA 94107 Document data is not restricted. This document contains no proprietary, International Traffic in Arms Regulations, or export-controlled information. Debris Assessment Software (DAS) version used in analysis: v2.1.1 Revision Record Revision: Date: Affected Pages: Changes: Author(s): 1.0 5/3/2019 All –Initial DAS Software D. Morse Results Orbit Lifetime Analysis 1

YAM ODAR – Version 1.0 Contents Self-assessment of the ODAR using the format in Appendix A.2 of NASA-STD-8719.14: ............................................................................................................................................. 3 ODAR Section 1: Program Management and Mission Overview ..................................... 4 ODAR Section 2: Spacecraft Description: ......................................................................... 5 ODAR Section 3: Assessment of Spacecraft Debris Released during Normal Operations:7 ODAR Section 4: Assessment of Spacecraft Intentional Breakups and Potential for Explosions. .......................................................................................................................... 8 ODAR Section 5: Assessment of Spacecraft Potential for On-Orbit Collisions .............. 10 ODAR Section 6: Assessment of Spacecraft Post-Mission Disposal Plans and Procedures ........................................................................................................................................... 11 ODAR Section 7: Assessment of Spacecraft Reentry Hazards: ....................................... 13 ODAR Section 8: Assessment for Tether Missions .......................................................... 24 Appendix A: Acronyms ................................................................................................... 24 2

YAM ODAR – Version 1.0 Self-assessment of the ODAR using the format in Appendix A.2 of NASA-STD-8719.14: A self-assessment is provided below in accordance with the assessment format provided in Appendix A.2 of NASA-STD-8719.14. Section Status Comments 4.3-1, Mission-Related Debris Passing Through COMPLIANT LEO 4.3-2, Mission-Related Debris Passing Near GEO COMPLIANT 4.4-1, Limiting the risk to other space systems COMPLIANT from accidental explosions during deployment and mission operations while in orbit about Earth or the Moon 4.4-2, Design for passivation after completion of N/A mission operations while in orbit about Earth or the Moon 4.4-3, Limiting the long-term risk to other space COMPLIANT systems from planned breakups 4.4-4, Limiting the short-term risk to other space COMPLIANT systems from planned breakups 4.5-1, Probability of Collision with Large Objects COMPLIANT 4.5-2, Probability of Damage from Small Objects COMPLIANT System will passively deorbit; therefore, no components are critical to deorbit. 4.6-1, Disposal for space structures passing COMPLIANT through LEO 4.6-2, Disposal for space structures passing N/A through GEO 4.6-3, Disposal for space structures between LEO N/A and GEO 4.6-4, Reliability of post-mission disposal COMPLIANT operations 4.8-1, Collision Hazards of Space Tethers N/A 3

YAM ODAR – Version 1.0 Assessment Report Format: ODAR Technical Sections Format Requirements: Loft Orbital is a U.S. company. This ODAR follows the format in NASA-STD-8719.14, Appendix A.1 and includes the content indicated as a minimum in each of sections 2 through 8 below for the YAM constellation. Sections 9 through 14 apply to the launch vehicle ODAR and are not covered here. ODAR Section 1: Program Management and Mission Overview Program/project manager: Pieter van Duijn Senior Management: Alexander B. Greenberg (Co-founder & Chief Operating Officer) Launch and deployment profile, including all parking, transfer, and operational orbits with apogee, perigee, and inclination: The YAM constellation will consist of approximately 10 satellites launched into sun-synchronous circular orbits with orbit altitudes between 425 and 570 km. The first satellite in the constellation to be launch will be YAM-2 which is discussed in further detail below. The remaining orbital debris analysis assumes the worst-case orbit altitude of 570 km circular SSO. The orbital decay of the YAM constellation is provided for completeness. Schedule of upcoming mission milestones: Loft Orbital has contracted Spaceflight Services to broker the YAM-2 launch. Spaceflight’s most recent manifest indicates a launch window of February 1, 2020 – April 30, 2020. Mission Overview: Each YAM satellite will be launched into a sun-synchronous, Low Earth Orbit (LEO). Each satellite bus will use reaction wheels, magnetic torque coils, a star tracker, magnetometers, sun sensors, and an inertial measurement unit to enable precision 3-axis pointing without the use of propellant. Launch Vehicle and Launch Site: YAM-2: Polar Satellite Launch Vehicle, Operated by the Indian Space Research Organization. The launch site is the Satish Dhawan Space Centre in Srihrikota, India. The PSLV launch vehicle will transport multiple mission payloads to orbit. YAM-2 will be deployed into an approximately sun synchronous circular low Earth orbit. Once the final stage has burned out, the primary payloads will be dispensed. After the primary payloads are clear, the secondary payload will separate. YAM-2 will deploy one 4

YAM ODAR – Version 1.0 solar panel once deployed from the MkII Motorized Light Band (MLB) deployer. The spacecraft is expected to be deployed with the following orbital parameters:1 Highest Apogee: 550 km Highest Perigee: 550 km Target Inclination: 97.5° ± 0.3° YAM-2 has no on-board propulsion and therefore does not actively change its orbit. There is no parking or transfer orbit. Mission Duration: The anticipated lifetime of the spacecraft is less than 6 years in LEO. ODAR Section 2: Spacecraft Description: Physical description of the constellation: At present, each YAM satellite is based on the Blue Canyon Technologies (BCT) MicroSat bus. Basic physical dimensions are 750 mm x 1300 mm x 600 mm with a mass of approximately 78.8 kg. The satellite is composed of the BCT bus, deployable solar panel, solar array drive assembly, and Payload Hub. The solar panel generates up to 200W of electric power which is stored in a 300Wh COTS Li- Ion unpressurized battery assembly. Solar array is deployed using a TiNi Aerospace, Inc. (TiNi) frangibolts. The bus is 3-axis stabilized, employing star trackers and sun sensor for attitude knowledge and reaction wheels and torque rods for attitude control. Loft Orbital will seek additional approval if it chooses to deploy a different bus. The YAM-2 satellite will be separated from the PSLV launch vehicle using the MkII MLB, which provides debris free actuation. Power is locked away from all spacecraft platform and payload components by means of redundant series separation switches on the MkII MLB. These switches cannot be activated until the spacecraft separates from the deployer structure. The YAM spacecraft is depicted in Figure 1. 1 The YAM-2 satellite will be deployed between 500 km and 550 km at the discretion of the launch service provider. Loft Orbital has assumed a 550 km deployment orbital altitude for purposes of this orbital debris analysis. 5

YAM ODAR – Version 1.0 Figure 1 YAM Spacecraft Configuration Total satellite mass at launch, including all propellants and fluids: 78.8 kg. Dry mass of satellites at launch: 78.8 kg (no propellants on board) Description of all propulsion systems (cold gas, mono-propellant, bi-propellant, electric, nuclear): None Identification, including mass and pressure, of all fluids (liquids and gases) planned to be on board and a description of the fluid loading plan or strategies, excluding fluids in sealed heat pipes: None Fluids in Pressurized Batteries: None The YAM satellites use an 8-cell unpressurized standard COTS Lithium-Ion battery cells in each spacecraft. The total capacity energy capacity per spacecraft is 300 W-h. Description of attitude control system and indication of the normal attitude of the spacecraft with respect to the velocity vector: The YAM spacecraft attitude will be controlled initially by 3 torque rods, which will allow the satellite to be aligned relative to 6

YAM ODAR – Version 1.0 the Earth’s magnetic field. These will allow the satellite to detumble and align with the magnetic field.  A safe mode is optimized for solar power generation from the satellite. The spacecraft’s deployable panel will be oriented towards the sun. This mode will make use of magnetometers, sun sensors, reaction wheels, and magnetic torquers to orient the spacecraft correctly.  A targeted tracking mode will allow the satellite Nadir panel to be directed at any location on the Earth’s surface. This mode will make use of reaction wheels and a star tracker to orient the spacecraft.  An LVLH mode keeps the Nadir panel pointed towards the Earth’s surface. This mode will make use of reaction wheels and a star tracker to orient the spacecraft. Description of any range safety or other pyrotechnic devices: None The spacecraft deploys its solar panels using a frangibolt system (manufactured by TiNi), which does not release any debris. The YAM-2 satellite will be released from the PSLV launch vehicle using the MkII MLB separation system which provides debris-free actuation. The solar panel spring constant is very low. Description of the electrical generation and storage system: Standard COTS Lithium- Ion battery cells are charged before payload integration and provide 300 W-h of electrical energy during the eclipse portion of the satellite’s orbit. A series of Triple Junction Solar Cells generate a maximum on-orbit power of approximately 200 W at the end-of-life of the mission (5 years for calculation purposes). The charge/discharge cycle is managed by a power management system overseen by the Flight Computer. Identification of any other sources of stored energy not noted above: None Identification of any radioactive materials on board: None ODAR Section 3: Assessment of Spacecraft Debris Released during Normal Operations: Identification of any object (>1 mm) expected to be released from the spacecraft any time after launch, including object dimensions, mass, and material: None. Rationale/necessity for release of each object: N/A Time of release of each object, relative to launch time: N/A 7

YAM ODAR – Version 1.0 Release velocity of each object with respect to spacecraft: N/A. Expected orbital parameters (apogee, perigee, and inclination) of each object after release: N/A Calculated orbital lifetime of each object, including time spent in Low Earth Orbit (LEO): N/A Assessment of spacecraft compliance with Requirements 4.3-1 and 4.3-2 (per DAS v2.1.1) 4.3-1, Mission Related Debris Passing Through LEO: COMPLIANT 4.3-2, Mission Related Debris Passing Near GEO: COMPLIANT ODAR Section 4: Assessment of Spacecraft Intentional Breakups and Potential for Explosions. Potential causes of spacecraft breakup during deployment and mission operations: There is no credible scenario that would result in spacecraft breakup during normal deployment and operations. Summary of failure modes and effects analyses of all credible failure modes which may lead to an accidental explosion: The in-orbit failure of a battery cell protection circuit could lead to a short circuit resulting in overheating and a very remote possibility of battery cell explosion. Detailed plan for any designed spacecraft breakup, including explosions and intentional collisions: There are no planned breakups. List of components which shall be passivated at End of Mission (EOM) including method of passivation and amount which cannot be passivated:  Eight (8) Lithium Ion Battery Cells – configure spacecraft to keep solar array pointed away from sun and let batteries deplete  Reaction wheels – remove power and configure spacecraft to keep solar array pointed away from sun  Sealed heat pipe – no passivation is planned or required Rationale for all items which are required to be passivated, but cannot be due to their design: None Assessment of spacecraft compliance with Requirements 4.4-1 through 4.4-4: Requirement 4.4-1: Limiting the risk to other space systems from accidental explosions during deployment and mission operations while in orbit about Earth or 8

YAM ODAR – Version 1.0 the Moon: “For each spacecraft and launch vehicle orbital stage employed for a mission, the program or project shall demonstrate, via failure mode and effects analyses or equivalent analyses, that the integrated probability of explosion for all credible failure modes of each spacecraft and launch vehicle is less than 0.001 (excluding small particle impacts) (Requirement 56449).” Compliance statement: Required Probability: 0.001 Expected probability: 0.000; COMPLIANT. Furthermore, the combined probability of the entire constellation of 10 YAM satellites is 0.000 which is also COMPLIANT. Supporting Rationale and FMEA details: Battery explosion: On-orbit failure of a battery cell protection circuit could lead to a short circuit resulting in overheating and a very remote possibility of battery cell deflagration. Multiple independent failures must first occur for this effect. In the event of an unlikely explosion, the effect to the far-term LEO environment is considered negligible due to the following:  YAM satellites have a short orbital life due to the low orbital altitude (<6 years)  YAM satellites have relatively low mass  YAM satellites have spacecraft structural aluminum covers, which will likely contain debris results from a battery rupturing, except for those that may be vented through small orifices Requirement 4.4-2: Design for passivation after completion of mission operations while in orbit about Earth or the Moon: ‘Design of all spacecraft and launch vehicle orbital stages shall include the ability to deplete all onboard sources of stored energy and disconnect all energy generation sources when they are no longer required for mission operations or post-mission disposal or control to a level which can not cause an explosion or deflagration large enough to release orbital debris or break up the spacecraft (Requirement 56450).” Compliance statement: At EOM, the flight software will be updated to point the solar arrays away from the sun, momentum bias the satellite, turn off the reaction wheels, and shed power from all electronics. In the unlikely event that a battery cell does explosively rupture, the small size, mass, and potential energy of these small batteries is such that while the spacecraft could be expected to vent gases, most debris from the battery rupture should be contained within the spacecraft due to the lack of penetration energy to the multiple enclosures surrounding the batteries. 9

YAM ODAR – Version 1.0 Requirement 4.4-3. Limiting the long-term risk to other space systems from planned breakups: Compliance statement: This requirement is not applicable. There are no planned breakups. Requirement 4.4-4: Limiting the short-term risk to other space systems from planned breakups: Compliance statement: This requirement is not applicable. There are no planned breakups. ODAR Section 5: Assessment of Spacecraft Potential for On-Orbit Collisions Assessment of spacecraft compliance with Requirements 4.5-1 and 4.5-2 (per DAS v2.1.1, and calculation methods provided in NASA-STD-8719.14, section 4.5.4): Requirement 4.5-1. Limiting debris generated by collisions with large objects when operating in Earth orbit: “For each spacecraft and launch vehicle orbital stage in or passing through LEO, the program or project shall demonstrate that, during the orbital lifetime of each spacecraft and orbital stage, the probability of accidental collision with space objects larger than 10 cm in diameter is less than 0.001 (Requirement 56506).” Large Object Impact and Debris Generation Probability: 0.00001; COMPLIANT. Furthermore, the combined probability of the entire constellation of 10 YAM satellites is 0.0001, which is also COMPLIANT. Requirement 4.5-2. Limiting debris generated by collisions with small objects when operating in Earth or lunar orbit: “For each spacecraft, the program or project shall demonstrate that, during the mission of the spacecraft, the probability of accidental collision with orbital debris and meteoroids sufficient to prevent compliance with the applicable postmission disposal requirements is less than 0.01 (Requirement 56507).” Small Object Impact and Debris Generation Probability: Not applicable; the spacecraft will be disposed of by atmospheric entry and does not require a specific spacecraft orientation and drag state to meet the disposal requirements. Therefore, no element or component of the spacecraft system is required to complete post-mission operations. Identification of all systems or components required to accomplish any post-mission disposal operation, including passivation and maneuvering: None 10

YAM ODAR – Version 1.0 ODAR Section 6: Assessment of Spacecraft Post-Mission Disposal Plans and Procedures 6.1 Description of spacecraft disposal option selected: The satellite will de-orbit naturally by atmospheric re-entry. There is no propulsion system. 6.2 Plan for any spacecraft maneuvers required to accomplish post-mission disposal: None 6.3 Calculation of area-to-mass ratio after post-mission disposal, if the controlled reentry option is not selected: Spacecraft Mass: 78.8 kg Cross-sectional Area: 0.883 m2 (Calculated by DAS 2.1.1). Area to mass ratio: 0.88/78.8 = 0.0112 m2/kg 6.4 Assessment of spacecraft compliance with Requirements 4.6-1 through 4.6-5 (per DAS v2.1.1 and NASA-STD-8719.14 section): Requirement 4.6-1. Disposal for space structures passing through LEO: “A spacecraft or orbital stage with a perigee altitude below 2000 km shall be disposed of by one of three methods: (Requirement 56557) a. Atmospheric reentry option: Leave the space structure in an orbit in which natural forces will lead to atmospheric reentry within 25 years after the completion of mission but no more than 30 years after launch; or Maneuver the space structure into a controlled de-orbit trajectory as soon as practical after completion of mission. b. Storage orbit option: Maneuver the space structure into an orbit with perigee altitude greater than 2000 km and apogee less than GEO - 500 km. c. Direct retrieval: Retrieve the space structure and remove it from orbit within 10 years after completion of mission.” Analysis: The YAM satellites’ method of disposal is COMPLIANT using method “a.” In the worst-case orbit altitude of 570 x 570 km near-circular orbit, the passive deorbit time is 5.3 years after launch with orbit history as shown in Figure 2. It should be noted that this is assuming a launch date of January 2021. Because de-orbit lifetime will vary depending on the launch date, Loft Orbital will select launch opportunities that ensure 11

YAM ODAR – Version 1.0 that each YAM satellite will meet the FCC’s 6-year de-orbit requirement for satellites authorized under the FCC’s new small satellite streamlined licensing rules.2 The first spacecraft, YAM-2, will be deployed in a 550 x 550 km near-circular orbit, reentering in approximately 4.375 years after launch with orbit history as shown in Figure 3 (analysis assumes a noon-midnight Sun synchronous orbit with solar array tracking). Figure 2 YAM Orbit History – at Maximum Orbit Altitude of 570 km x 570 km SSO 2 See Streamlining Licensing Procedures for Small Satellites, Report and Order, IB Docket No. 18-86 (rel. Aug. 2, 2019) (new 47 C.F.R. § 25.122); see also Attachment A, Narrative § II(A). 12

YAM ODAR – Version 1.0 Figure 3 YAM-2 Orbit History Requirement 4.6-2. Disposal for space structures near GEO: Analysis is not applicable. Requirement 4.6-3. Disposal for space structures between LEO and GEO: Analysis is not applicable. Requirement 4.6-4. Reliability of Post-mission Disposal Operations: Analysis is not applicable. The satellite will reenter passively without post-mission disposal operations within the allowable timeframe. ODAR Section 7: Assessment of Spacecraft Reentry Hazards: Assessment of spacecraft compliance with Requirement 4.7-1: Requirement 4.7-1. Limit the risk of human casualty: 13

YAM ODAR – Version 1.0 “The potential for human casualty is assumed for any object with an impacting kinetic energy in excess of 15 joules: a) For uncontrolled reentry, the risk of human casualty from surviving debris shall not exceed 0.0001 (1:10,000) (Requirement 56626).” Summary Analysis Results: DAS reports that the YAM satellites are COMPLIANT with the requirement with a per satellite casualty risk of 1:100000000. Experimentation has demonstrated that 1:100000000 is the smallest human casualty risk that the DAS software will report. Since the analysis shows all components of the YAM satellites demising above an altitude of 60 km and both the Debris Casualty Area and the Impact Kinetic Energy are reported as 0.0 in all cases, this reflects 0 chance of human casualty. For the same reasons, the total constellation casualty risk is also 0%. The DAS Output Summary Follows: 07 26 2019; 06:35:04AM Processing Requirement 4.3-2: Return Status : Passed ===================== No Project Data Available ===================== =============== End of Requirement 4.3-2 =============== 07 26 2019; 06:35:10AM Requirement 4.4-3: Compliant =============== End of Requirement 4.4-3 =============== 07 26 2019; 06:44:16AM Processing Requirement 4.5-1: Return Status : Passed ============== Run Data ============== **INPUT** Space Structure Name = YAM Space Structure Type = Payload Perigee Altitude = 570.000000 (km) Apogee Altitude = 570.000000 (km) Inclination = 97.700000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass Ratio = 0.011200 (m^2/kg) Start Year = 2021.000000 (yr) Initial Mass = 78.800000 (kg) Final Mass = 78.800000 (kg) Duration = 5.000000 (yr) Station-Kept = False Abandoned = True PMD Perigee Altitude = -1.000000 (km) 14

YAM ODAR – Version 1.0 PMD Apogee Altitude = -1.000000 (km) PMD Inclination = 0.000000 (deg) PMD RAAN = 0.000000 (deg) PMD Argument of Perigee = 0.000000 (deg) PMD Mean Anomaly = 0.000000 (deg) **OUTPUT** Collision Probability = 0.000011 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range Status = Pass ============== =============== End of Requirement 4.5-1 =============== 07 26 2019; 06:50:23AM Requirement 4.5-2: Compliant 07 26 2019; 06:50:39AM Processing Requirement 4.6 Return Status : Passed ============== Project Data ============== **INPUT** Space Structure Name = YAM Space Structure Type = Payload Perigee Altitude = 570.000000 (km) Apogee Altitude = 570.000000 (km) Inclination = 97.700000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.011200 (m^2/kg) Start Year = 2021.000000 (yr) Initial Mass = 78.800000 (kg) Final Mass = 78.800000 (kg) Duration = 5.000000 (yr) Station Kept = False Abandoned = True PMD Perigee Altitude = 383.753632 (km) PMD Apogee Altitude = 383.753632 (km) PMD Inclination = 97.653241 (deg) PMD RAAN = 57.516157 (deg) PMD Argument of Perigee = 322.623706 (deg) PMD Mean Anomaly = 0.000000 (deg) **OUTPUT** Suggested Perigee Altitude = 383.753632 (km) 15

YAM ODAR – Version 1.0 Suggested Apogee Altitude = 383.753632 (km) Returned Error Message = Passes LEO reentry orbit criteria. Released Year = 2026 (yr) Requirement = 61 Compliance Status = Pass ============== =============== End of Requirement 4.6 =============== 07 26 2019; 06:50:50AM *********Processing Requirement 4.7-1 Return Status : Passed ***********INPUT**** Item Number = 1 name = YAM quantity = 1 parent = 0 materialID = 8 type = Box Aero Mass = 78.800003 Thermal Mass = 78.800003 Diameter/Width = 0.750000 Length = 1.300000 Height = 0.600000 name = Solar Array Support quantity = 3 parent = 1 materialID = 8 type = Flat Plate Aero Mass = 0.670000 Thermal Mass = 0.670000 Diameter/Width = 0.250000 Length = 0.800000 name = Solar Array Panel quantity = 3 parent = 1 materialID = 27 type = Flat Plate Aero Mass = 1.660000 Thermal Mass = 1.660000 Diameter/Width = 0.250000 Length = 0.800000 name = Solar Array Drive quantity = 1 parent = 1 materialID = 8 16

YAM ODAR – Version 1.0 type = Cylinder Aero Mass = 1.650000 Thermal Mass = 1.650000 Diameter/Width = 0.093000 Length = 0.108000 name = Internal Bus Components quantity = 1 parent = 1 materialID = 8 type = Box Aero Mass = 4.270000 Thermal Mass = 4.270000 Diameter/Width = 0.500000 Length = 0.500000 Height = 0.200000 name = Bus Structure - Outside Components quantity = 1 parent = 1 materialID = 8 type = Box Aero Mass = 6.900000 Thermal Mass = 6.900000 Diameter/Width = 0.500000 Length = 0.500000 Height = 0.200000 name = Payload Wire Harness quantity = 1 parent = 1 materialID = 19 type = Box Aero Mass = 3.000000 Thermal Mass = 3.000000 Diameter/Width = 0.100000 Length = 0.300000 Height = 0.100000 name = Sep System quantity = 1 parent = 1 materialID = 8 type = Cylinder Aero Mass = 4.700000 Thermal Mass = 4.700000 Diameter/Width = 0.500000 Length = 0.200000 name = Payload Panels quantity = 6 17

YAM ODAR – Version 1.0 parent = 1 materialID = 8 type = Flat Plate Aero Mass = 2.600000 Thermal Mass = 2.600000 Diameter/Width = 0.500000 Length = 0.500000 name = Bus Panels 1 quantity = 4 parent = 1 materialID = 8 type = Flat Plate Aero Mass = 1.500000 Thermal Mass = 1.500000 Diameter/Width = 0.200000 Length = 0.500000 name = Bus Panels 2 quantity = 2 parent = 1 materialID = 8 type = Flat Plate Aero Mass = 3.000000 Thermal Mass = 3.000000 Diameter/Width = 0.500000 Length = 0.500000 name = Reaction Wheels quantity = 4 parent = 1 materialID = 8 type = Box Aero Mass = 0.828000 Thermal Mass = 0.828000 Diameter/Width = 0.112000 Length = 0.112000 Height = 0.038000 name = Battery quantity = 3 parent = 1 materialID = 8 type = Box Aero Mass = 0.770000 Thermal Mass = 0.770000 Diameter/Width = 0.100000 Length = 0.200000 Height = 0.100000 name = Torque Rod 18

YAM ODAR – Version 1.0 quantity = 3 parent = 1 materialID = 60 type = Cylinder Aero Mass = 0.550000 Thermal Mass = 0.550000 Diameter/Width = 0.038000 Length = 0.194000 name = Payload1 quantity = 1 parent = 1 materialID = 8 type = Box Aero Mass = 4.750000 Thermal Mass = 4.750000 Diameter/Width = 0.241000 Length = 0.257000 Height = 0.140000 name = Payload2_1 quantity = 2 parent = 1 materialID = 8 type = Box Aero Mass = 1.310000 Thermal Mass = 1.310000 Diameter/Width = 0.100000 Length = 0.100000 Height = 0.100000 name = Payload3 quantity = 1 parent = 1 materialID = 8 type = Box Aero Mass = 0.450000 Thermal Mass = 0.450000 Diameter/Width = 0.080000 Length = 0.100000 Height = 0.070000 name = Paylaod4 quantity = 1 parent = 1 materialID = 8 type = Box Aero Mass = 3.000000 Thermal Mass = 3.000000 Diameter/Width = 0.114000 Length = 0.191000 19

YAM ODAR – Version 1.0 Height = 0.114000 name = Payload5 quantity = 1 parent = 1 materialID = 8 type = Box Aero Mass = 1.000000 Thermal Mass = 1.000000 Diameter/Width = 0.100000 Length = 0.100000 Height = 0.100000 name = Paylaod2_2 quantity = 1 parent = 1 materialID = 8 type = Flat Plate Aero Mass = 2.010000 Thermal Mass = 1.010000 Diameter/Width = 0.401000 Length = 0.401000 name = Paylaod6 quantity = 1 parent = 20 materialID = 8 type = Box Aero Mass = 1.000000 Thermal Mass = 1.000000 Diameter/Width = 0.100000 Length = 0.100000 Height = 0.100000 name = PCU quantity = 1 parent = 1 materialID = 8 type = Box Aero Mass = 0.850000 Thermal Mass = 0.850000 Diameter/Width = 0.114000 Length = 0.114000 Height = 0.114000 **************OUTPUT**** Item Number = 1 name = YAM Demise Altitude = 77.993408 Debris Casualty Area = 0.000000 20

YAM ODAR – Version 1.0 Impact Kinetic Energy = 0.000000 ************************************* name = Solar Array Support Demise Altitude = 76.314751 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Solar Array Panel Demise Altitude = 77.228142 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Solar Array Drive Demise Altitude = 63.911160 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Internal Bus Components Demise Altitude = 70.411758 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Bus Structure - Outside Components Demise Altitude = 65.743874 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Payload Wire Harness Demise Altitude = 69.807449 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Sep System Demise Altitude = 72.632133 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Payload Panels Demise Altitude = 70.173592 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* 21

YAM ODAR – Version 1.0 name = Bus Panels 1 Demise Altitude = 72.244080 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Bus Panels 2 Demise Altitude = 68.915451 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Reaction Wheels Demise Altitude = 67.996529 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Battery Demise Altitude = 73.965691 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Torque Rod Demise Altitude = 66.128578 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Payload1 Demise Altitude = 63.509769 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Payload2_1 Demise Altitude = 66.981331 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Payload3 Demise Altitude = 72.790085 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Paylaod4 Demise Altitude = 65.330566 Debris Casualty Area = 0.000000 22

YAM ODAR – Version 1.0 Impact Kinetic Energy = 0.000000 ************************************* name = Payload5 Demise Altitude = 69.199936 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Paylaod2_2 Demise Altitude = 75.120552 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Paylaod6 Demise Altitude = 62.046406 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = PCU Demise Altitude = 71.542015 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* =============== End of Requirement 4.7-1 =============== Requirements 4.7-1b, and 4.7-1c: These requirements are non-applicable requirements because the YAM constellation does not use controlled reentry. 4.7-1, b): “For controlled reentry, the selected trajectory shall ensure that no surviving debris impact with a kinetic energy greater than 15 joules is closer than 370 km from foreign landmasses, or is within 50 km from the continental U.S., territories of the U.S., and the permanent ice pack of Antarctica (Requirement 56627).” Not applicable to YAM. The spacecraft does not use controlled reentry and no debris is expected to survive. 4.7-1 c): “For controlled reentries, the product of the probability of failure of the reentry burn (from Requirement 4.6-4.b) and the risk of human casualty assuming uncontrolled reentry shall not exceed 0.0001 (1:10,000) (Requirement 56628).” Not applicable to YAM. It does not use controlled reentry and no debris is expected to survive. 23

YAM ODAR – Version 1.0 ODAR Section 8: Assessment for Tether Missions Not applicable. There are no tethers used in the YAM mission. END of ODAR for YAM -------------------------------------------------------------- Appendix A: Acronyms Arg peri Argument of Perigee CDR Critical Design Review cm centimeter COTS Commercial Off-The-Shelf (items) DAS Debris Assessment Software EOM End Of Mission FRR Flight Readiness Review GEO Geosynchronous Earth Orbit ITAR International Traffic In Arms Regulations kg kilogram km kilometer LEO Low Earth Orbit Li-Ion Lithium Ion m2 Meters squared ml milliliter mm millimeter N/A Not Applicable. NET Not Earlier Than ODAR Orbital Debris Assessment Report OSMA Office of Safety and Mission Assurance PDR Preliminary Design Review PL Payload ISIPOD ISIS CubeSat Deployer PSIa Pounds Per Square Inch, absolute RAAN Right Ascension of the Ascending Node SMA Safety and Mission Assurance Ti Titanium Yr year 24


Document Created: 2019-08-07 17:00:09
Document Modified: 2019-08-07 17:00:09
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