LEMUR 2 ODAR

0041-EX-PL-2015 Text Documents

Spire Global, Inc.

2015-01-29ELS_158322

2015 LEMUR-2 Orbital Debris Assessment Report NANOSATISFI MARKET MISSION PROFILE PREPARED BY: NANOSATISFI INC

Summarized List of Compliance Status to Orbital Debris Requirements For convenience, below is a summarized list of the compliance status to orbital debris requirements. Detailed explanations for each of these compliance statements are available in ODAR Sections 1 through 8. 4.3-1, Mission-Related Debris Passing Through LEO: COMPLIANT 4.3-2, Mission-Related Debris Passing Near GEO COMPLIANT 4.4-1, Limiting the risk to other space systems from accidental explosions during COMPLIANT deployment and mission operations while in orbit about Earth or the Moon: 4.4-2, Design for passivation after completion of mission operations while in orbit N/A about Earth or the Moon: 4.4-3, Limiting the long-term risk to other space systems from planned breakups: COMPLIANT 4.4-4, Limiting the short-term risk to other space systems from planned breakups: COMPLIANT 4.5-1, Probability of Collision with Large Objects: COMPLIANT 4.5-2, Probability of Damage from Small Objects: COMPLIANT 4.6-1, Disposal for space structures passing through LEO: COMPLIANT 4.6-2, Disposal for space structures passing through GEO: N/A 4.6-3, Disposal for space structures between LEO and GEO: N/A 4.6-4, Reliability of postmission disposal operations: N/A 4.8-1, Collision Hazards of Space Tethers N/A

ODAR Section 1: Program Management and Mission Overview Program / Project Peter Platzer Manager Mission Description The purpose of the LEMUR-2 nanosatellite fleet is to provide high-revisit maritime domain monitoring data, as part of a market trial to test marked demand in this area. The mission consists of a set of 21 3U Cubesats satellites launched in four separate launch vehicles launches into various orbital planes, to increase average revisit time globally. The LEMUR-2 fleet is a continuation of the market trial currently underway with the single prototype LEMUR-1 satellite. Foreign None Government Involvement Project Milestones: The project milestones for the LEMUR-2 constellations align with the successive launch of vehicles into orbit. The table blow contains launch segment information for each Proposed Launch launch of the constellation. Date: Proposed Launch Proposed Vehicles: Number Launch Launch Date Vehicle of Vehicle Launch Site Altitude Inclination (no earlier Proposed Launch Satellites Operator than) Sites: Launch Vehicle Antrix / Sriharikota, Operator: PSLV Q3 2015 4 650 km 6 deg ISRO India Baikonur, Soyuz Q4 2015 2 Roscosmos 600 km 98 deg Kazakhstan January JAMSS / Tanegashima, HII-A 7 575 km 31 deg 2016 JAXA Japan Vandenberg, 450 x Falcon-9 Q1 2016 8 Space-X 98 deg CA, US 750 km Mission Duration: The operational lifetime of each satellite is estimated to be up to 2 years following deployment from the launch vehicle. The orbital lifetime for the constellation is nominally expected to be between 5-8 years, depending on the vehicle’s orbit, as described in Section 6. Launch / Launch Deployment Profile: LEMUR-2 satellites will be injected directly into the target orbits outlined in the table above. Checkout For up to 1 month following deployment into orbit, LEMUR-2 satellites will remain in checkout phase. During this phase, ground operators will verify correct operation of the satellite and its payloads, and prepare it for the operational phase.

Operations The operational phase of the satellite begins following the successful deployment of the satellite from the launch vehicle, and successful checkout. The operational phase continues until the end of the market study. Postmission Disposal Following the end of the operational phase, the satellites will remain on orbit in a non- transmitting mode while the orbit of the satellite passively decays until the satellite reenters the atmosphere and disintegrates. Other than the satellites launched as part of the PSLV vehicle, each of the satellites are nominally expected to reenter the atmosphere within 10 years following deployment from the launch vehicle, and the satellites launched as part of the PSLV vehicle are nominally expected to reenter the atmosphere within 18 years following deployment from the launch vehicle, as detailed in Table 2 of Section 6. Selection of Orbit: The selection of the chosen orbits was made due to available launch opportunities. Potential Physical As the satellites do not have any propulsion systems, their orbits will naturally decay Interference with following deployment from the launch vehicle. Other Orbiting Object: As detailed in Section 5, the probability of physical interference between the satellites and other space objects is sufficiently unlikely that the satellite complies with Requirement 4.5.

ODAR Section 2: Spacecraft Description Physical Description: Property Value Total Mass at Launch 4.5kg Dry Mass at Launch 4.5kg Form Factor 3U CubeSat COG <3cm radius from geometric center Envelope (stowed) 100mm x 100mm x 340.5mm (excluding dynamic envelope) Envelope (deployed) 1m x 1m x 300mm Propulsion Systems None Fluid Systems None AOCS Stabilization/pointing with 3x orthogonal reaction wheels, desaturation + coarse pointing with magnetorquers, GPS navigation Range Safety / None Pyrotechnic Devices Electrical Generation Triple-junction GaAs solar panels Electrical Storage Rechargeable lithium-polymer battery pack Radioactive Materials None

ODAR Section 3: Assessment of Debris Released During Normal Operations Objects larger than 1mm expected to be released during orbit: None Rationale for release of each object: N/A Time of release of each object: N/A Release velocity of each object: N/A Expected orbital parameters of each object: N/A Calculated orbital lifetime of each object: N/A Assessment of spacecraft compliance with Requirements 4.3-1 and 4.3-2: 4.3-1, Mission-Related Debris Passing Through LEO: COMPLIANT 4.3-2, Mission-Related Debris Passing Near GEO: COMPLIANT A DAS 2.0.2 log demonstrating the compliance to the above requirements is available in Appendix A – “DAS 2.0.2 Log”.

ODAR Section 4: Assessment of Spacecraft Intentional Breakups and Potential for Explosions Potential causes for spacecraft breakup: There are only two plausible causes for breakup of the satellites: ● energy released from onboard batteries, and ● mechanical failure of the reaction wheels Summary of failure modes and effects analysis of all credible failure modes which may lead to an accidental explosion: The batteries aboard the satellites are two 42Wh Lithium-Polymer batteries, and represent the only credible failure mode during which stored energy is released. The main failure modes associated with Lithium Polymer batteries result from overcharging, overdischarging, internal shorts, and external shorts. The battery pack onboard LEMUR-2 satellites complies with all controls / process requirements identified in JSC- 20793 Section 5.4.3 to mitigate chance of any accidental venting / explosion caused by the above failure modes. The only failure mode of the reaction wheel assemblies that could lead to creation of debris would be breakup of the wheels themselves due to mechanical failure while operating at a high angular rate. Risk mitigation strategies for breakups due to the reaction wheels include limiting the maximum rotational speed of the wheels, and containing them within a sealed compartment. Detailed Plan for any designed spacecraft breakup, including explosions and intentional collisions: There is no planned breakup the satellites on-orbit. List of components passivated at EOM: At the end of mission, the only components that will require passivation are the reaction wheels. At the end of the mission, the reaction wheels will be de-spun to passivate. Rationale for all items required to be passivated that cannot be due to design: N/A Assessment of spacecraft compliance with Requirements 4.4-1 through 4.4-4: 4.4-1, Limiting the risk to other space systems from accidental explosions during COMPLIANT deployment and mission operations while in orbit about Earth or the Moon 4.4-2, Design for passivation after completion of mission operations while in orbit COMPLIANT about Earth or the Moon 4.4-3, Limiting the long-term risk to other space systems from planned breakups: COMPLIANT There are no planned breakups of any of the satellites. 4.4-4, Limiting the short-term risk to other space systems from planned breakups COMPLIANT There are no planned breakups of any of the satellites.

ODAR Section 5: Assessment of Spacecraft Potential for On- Orbit Collisions Probability for Collision with Objects >10cm: The probability of a collision of any of the satellites with an orbiting object larger than 10cm in diameter was sufficiently small that the simulation performed using DAS 2.0.2 software returned a probability value of 0. Assessment of spacecraft compliance with Requirement 4.5-1 and 4.5-2: 4.5-1, Probability of Collision with Large Objects: COMPLIANT 4.5-2, Probability of Damage from Small Objects: COMPLIANT A DAS 2.0.2 log demonstrating the compliance to the above requirements is available in Appendix A – “DAS 2.0.2 Log”.

ODAR Section 6: Assessment of Spacecraft Postmission Disposal Plans and Procedures Description of Disposal Option Selected: Following its deployment, the satellite’s orbit will naturally decay until it reenters the atmosphere. Table 1Table 1 describes the mission scenarios for which lifetime analysis of LEMUR-2 was considered, and the effective area- to-mass ratio of the satellite in each scenario. The ratio was calculated using the external dimensions of the satellite and deployed arrays. Drag area from deployed antennas was neglected. Table 1 - Area-to-Mass Ratio of LEMUR-2 Satellites in Various Mission Scenarios Scenario Description Effective Area-to- Mass (m2/kg) Satellite  Antennas do not deploy Nonfunctional  Solar arrays do not deploy 0.0074  Satellite tumbles randomly Solar panel  Antennas deploy failure  Solar panels fail to deploy 0.0130  Satellite maintains +Z axis nadir  Position around Z axis as planned for mission operations Operational,  Antennas deploy nominal  Solar panels deploy 0.0208  Satellite maintains +Z axis nadir  Position around Z axis as planned for mission operations ADCS  Antennas deploy Nonfunctional  Solar arrays deploy 0.0169  Satellite tumbles randomly

Table 2Table 2 shows the simulated orbital dwell time for a LEMUR-2 satellite in each of the planned orbits of the constellation, in each of the identified mission scenarios. In all mission scenarios and orbits, the dwell time of the satellite was simulated using DAS 2.0.2 software to be less than 20 years. Table 2 – Orbit Dwell Time for LEMUR-2 Satellite in Each Planned Orbit and Mission Scenario Orbital Lifetime (Years) Soyuz HII-A Falcon-9 PSLV Effective (2 satellites) (7 satellites) (8 satellites) (4 satellites) Description Area-to-Mass (m2/kg) 600km x 575km x 575km, 750km x 450km, 650km x 650km, 600km SSO 31 deg SSO 6 deg Satellite 19.8 17.0 11.6 40.4 0.0074 Nonfunctional Solar panels 11.1 8.8 8.0 23.2 0.0130 failure ADCS 9.0 8.0 7.4 18.8 0.0169 Nonfunctional Operational, 8.3 7.5 6.9 17.3 0.0208 Nominal Identification of Systems Required for Postmission Disposal: None Plan for Spacecraft Maneuvers required for Postmission Disposal: N/A Calculation of final Area-to-Mass Ratio if Atmospheric Reentry Not Selected: N/A

Assessment of Spacecraft Compliance with Requirements 4.6-1 through 4.6-4: 1 4.6-1, Disposal for space structures passing through LEO COMPLIANT All of the satellites will reenter the atmosphere within 25 years of mission completion and 30 years of launch. 4.6-2, Disposal for space structures passing through GEO: N/A 4.6-3, Disposal for space structures between LEO and GEO: N/A 4.6-4, Reliability of postmission disposal operations: COMPLIANT 1 The only mission scenario in which the predicted orbital lifetime exceeds the limit of within 25 years of mission completion and within 30 years of launch is if both the deployable antennas and solar panels fail to deploy on the PSLV launch. As the satellites are nominally expected to perform, all will reenter within 17.3 years following launch.

ODAR Section 7: Assessment of Spacecraft Reentry Hazards Detailed description of spacecraft components by size, mass, material, shape, and original location on the space vehicle: A system-level mass breakdown and primary materials list included in the generic satellite bus is available in the table below: Subsystem Materials Quantity Mass Shape Size (mm) (g) Solar Panels (long) Glass, GaAs, FR4 6 150 Flat 100 x 300 PCB Plate GPS Antenna (large) Aluminum 1 450 Box 300 x 80 x 8 GPS Antenna (small) Aluminum 1 50 Box 50 x 50 x 17 Subsystem PCBs FR4 PCB 12 80 Flat 90 x 90 Plate Primary Structure Aluminum 1 560 Box 100 x 100 x 300 Optical Camera Aluminum, FR4 1 350 Cylinder 30 x 100 PCB, Glass Reaction wheel assembly Aluminum, copper, 1 600 Box 100 x 100 + enclosure FR4 PCB x 56 Battery pack Li-Polymer 2 470 Box 80 x 60 x 40 Summary of objects expected to survive an uncontrolled reentry (using DAS 2.0.2 software): None Calculation of probability of human casualty for expected reentry year and inclination: 0% Assessment of spacecraft compliance with Requirement 4.7-1: 4.7-1, Casualty Risk from Reentry Debris: COMPLIANT A DAS 2.0.2 log demonstrating the compliance to Requirement 4.7-1 is available in Appendix A – “DAS 2.0.2 Log”.

ODAR Section 7A: Assessment of Spacecraft Hazardous Materials Summary of Hazardous Materials Contained on Spacecraft: None

ODAR Section 8: Assessment for Tether Missions Type of tether: N/A Description of tether system: N/A Determination of minimum size of object that will cause the tether to be severed: N/A Tether mission plan, including duration and postmission disposal: N/A Probability of tether colliding with large space objects: N/A Probability of tether being severed during mission or after postmission disposal: N/A Maximum orbital lifetime of a severed tether fragment: N/A Assessment of compliance with Requirement 4.8-1: 4.8-1, Collision Hazards of Space Tethers: N/A

Appendix A: DAS 2.0.2 Log Below is the log of the DAS 2.0.2 simulation performed to demonstrate compliance to the above requirements. 01 29 2015; 18:35:20PM DAS Application Started 01 29 2015; 18:35:21PM Opened Project C:\Users\jspark\Desktop\Lemur- 2\ODAR\ 01 29 2015; 18:35:47PM Mission Editor Changes Applied 01 29 2015; 18:35:52PM Project Data Saved To File 01 29 2015; 18:36:33PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2015.500000 (yr) Perigee Altitude = 650.000000 (km) Apogee Altitude = 650.000000 (km) Inclination = 6.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.013000 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 23.392197 (yr) Time Spent in LEO during Lifetime = 23.392197 (yr) Last year of Propagation = 2038 (yr) Returned Error Message: Object reentered 01 29 2015; 18:36:59PM Science and Engineering - Apogee/Perigee History for a Given Orbit **INPUT** Perigee Altitude = 650.000000 (km) Apogee Altitude = 650.000000 (km) Inclination = 6.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.013000 (m^2/kg) Start Year = 2015.500000 (yr) Integration Time = 30.000000 (yr) **OUTPUT** Plot 01 29 2015; 18:38:21PM Mission Editor Changes Applied 01 29 2015; 18:38:25PM Project Data Saved To File 01 29 2015; 19:52:48PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT**

Start Year = 2015.500000 (yr) Perigee Altitude = 650.000000 (km) Apogee Altitude = 650.000000 (km) Inclination = 6.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.007400 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 40.388775 (yr) Time Spent in LEO during Lifetime = 40.388775 (yr) Last year of Propagation = 2055 (yr) Returned Error Message: Object reentered 01 29 2015; 19:53:06PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2015.500000 (yr) Perigee Altitude = 650.000000 (km) Apogee Altitude = 650.000000 (km) Inclination = 6.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.016900 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 18.803559 (yr) Time Spent in LEO during Lifetime = 18.803559 (yr) Last year of Propagation = 2034 (yr) Returned Error Message: Object reentered 01 29 2015; 19:53:19PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2015.500000 (yr) Perigee Altitude = 650.000000 (km) Apogee Altitude = 650.000000 (km) Inclination = 6.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.020800 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 17.264887 (yr) Time Spent in LEO during Lifetime = 17.264887 (yr) Last year of Propagation = 2032 (yr)

Returned Error Message: Object reentered 01 29 2015; 19:54:30PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2015.500000 (yr) Perigee Altitude = 450.000000 (km) Apogee Altitude = 750.000000 (km) Inclination = 98.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.007400 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 11.570157 (yr) Time Spent in LEO during Lifetime = 11.570157 (yr) Last year of Propagation = 2027 (yr) Returned Error Message: Object reentered 01 29 2015; 19:54:40PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2015.500000 (yr) Perigee Altitude = 450.000000 (km) Apogee Altitude = 750.000000 (km) Inclination = 98.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.013000 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 8.043806 (yr) Time Spent in LEO during Lifetime = 8.043806 (yr) Last year of Propagation = 2023 (yr) Returned Error Message: Object reentered 01 29 2015; 19:54:50PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2015.500000 (yr) Perigee Altitude = 450.000000 (km) Apogee Altitude = 750.000000 (km) Inclination = 98.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.016900 (m^2/kg)

**OUTPUT** Orbital Lifetime from Startyr = 7.370294 (yr) Time Spent in LEO during Lifetime = 7.370294 (yr) Last year of Propagation = 2022 (yr) Returned Error Message: Object reentered 01 29 2015; 19:54:59PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2015.500000 (yr) Perigee Altitude = 450.000000 (km) Apogee Altitude = 750.000000 (km) Inclination = 98.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.020800 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 6.921287 (yr) Time Spent in LEO during Lifetime = 6.921287 (yr) Last year of Propagation = 2022 (yr) Returned Error Message: Object reentered 01 29 2015; 19:55:17PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2015.500000 (yr) Perigee Altitude = 575.000000 (km) Apogee Altitude = 575.000000 (km) Inclination = 31.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.013000 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 8.750171 (yr) Time Spent in LEO during Lifetime = 8.750171 (yr) Last year of Propagation = 2024 (yr) Returned Error Message: Object reentered 01 29 2015; 19:55:28PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2015.500000 (yr) Perigee Altitude = 600.000000 (km) Apogee Altitude = 600.000000 (km)

Inclination = 98.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.013000 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 11.082820 (yr) Time Spent in LEO during Lifetime = 11.082820 (yr) Last year of Propagation = 2026 (yr) Returned Error Message: Object reentered 01 29 2015; 19:57:02PM Processing Requirement 4.3-1: Return Status : Not Run ===================== No Project Data Available ===================== =============== End of Requirement 4.3-1 =============== 01 29 2015; 19:57:05PM Processing Requirement 4.3-2: Return Status : Passed ===================== No Project Data Available ===================== =============== End of Requirement 4.3-2 =============== 01 29 2015; 19:57:07PM Requirement 4.4-3: Compliant =============== End of Requirement 4.4-3 =============== 01 29 2015; 19:57:17PM Processing Requirement 4.5-1: Return Status : Passed ============== Run Data ============== **INPUT** Space Structure Name = Lemur2_PSLV Space Structure Type = Payload Perigee Altitude = 650.000000 (km) Apogee Altitude = 650.000000 (km) Inclination = 6.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass Ratio = 0.013000 (m^2/kg) Start Year = 2015.500000 (yr) Initial Mass = 4.500000 (kg) Final Mass = 4.500000 (kg) Duration = 23.400000 (yr)

Station-Kept = False Abandoned = True PMD Perigee Altitude = -1.000000 (km) 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 = 0.000002 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range Status = Pass ============== **INPUT** Space Structure Name = Lemur2_Soyuz Space Structure Type = Payload Perigee Altitude = 600.000000 (km) Apogee Altitude = 600.000000 (km) Inclination = 97.800000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass Ratio = 0.013000 (m^2/kg) Start Year = 2015.500000 (yr) Initial Mass = 4.500000 (kg) Final Mass = 4.500000 (kg) Duration = 19.800000 (yr) Station-Kept = False Abandoned = True PMD Perigee Altitude = -1.000000 (km) 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 = 0.000002 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range Status = Pass ============== **INPUT**

Space Structure Name = Lemur2_Falcon9 Space Structure Type = Payload Perigee Altitude = 425.000000 (km) Apogee Altitude = 750.000000 (km) Inclination = 97.100000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass Ratio = 0.013000 (m^2/kg) Start Year = 2015.500000 (yr) Initial Mass = 4.500000 (kg) Final Mass = 4.500000 (kg) Duration = 9.000000 (yr) Station-Kept = False Abandoned = True PMD Perigee Altitude = -1.000000 (km) 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 = 0.000001 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range Status = Pass ============== **INPUT** Space Structure Name = Lemur2_HIIB Space Structure Type = Payload Perigee Altitude = 575.000000 (km) Apogee Altitude = 575.000000 (km) Inclination = 31.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass Ratio = 0.013000 (m^2/kg) Start Year = 2015.500000 (yr) Initial Mass = 4.500000 (kg) Final Mass = 4.500000 (kg) Duration = 17.000000 (yr) Station-Kept = False Abandoned = True PMD Perigee Altitude = -1.000000 (km) 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 = 0.000001 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range Status = Pass ============== =============== End of Requirement 4.5-1 =============== 01 29 2015; 19:57:20PM Requirement 4.5-2: Compliant 01 29 2015; 19:57:22PM Processing Requirement 4.6 Return Status : Passed ============== Project Data ============== **INPUT** Space Structure Name = Lemur2_PSLV Space Structure Type = Payload Perigee Altitude = 650.000000 (km) Apogee Altitude = 650.000000 (km) Inclination = 6.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.013000 (m^2/kg) Start Year = 2015.500000 (yr) Initial Mass = 4.500000 (kg) Final Mass = 4.500000 (kg) Duration = 23.400000 (yr) Station Kept = False Abandoned = True PMD Perigee Altitude = -1.000000 (km) 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** Suggested Perigee Altitude = 650.000000 (km) Suggested Apogee Altitude = 650.000000 (km) Returned Error Message = Reentry during mission (no PMD req.).

Released Year = 2038 (yr) Requirement = 61 Compliance Status = Pass ============== **INPUT** Space Structure Name = Lemur2_Soyuz Space Structure Type = Payload Perigee Altitude = 600.000000 (km) Apogee Altitude = 600.000000 (km) Inclination = 97.800000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.013000 (m^2/kg) Start Year = 2015.500000 (yr) Initial Mass = 4.500000 (kg) Final Mass = 4.500000 (kg) Duration = 19.800000 (yr) Station Kept = False Abandoned = True PMD Perigee Altitude = -1.000000 (km) 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** Suggested Perigee Altitude = 600.000000 (km) Suggested Apogee Altitude = 600.000000 (km) Returned Error Message = Reentry during mission (no PMD req.). Released Year = 2026 (yr) Requirement = 61 Compliance Status = Pass ============== **INPUT** Space Structure Name = Lemur2_Falcon9 Space Structure Type = Payload Perigee Altitude = 425.000000 (km) Apogee Altitude = 750.000000 (km) Inclination = 97.100000 (deg)

RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.013000 (m^2/kg) Start Year = 2015.500000 (yr) Initial Mass = 4.500000 (kg) Final Mass = 4.500000 (kg) Duration = 9.000000 (yr) Station Kept = False Abandoned = True PMD Perigee Altitude = -1.000000 (km) 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** Suggested Perigee Altitude = 425.000000 (km) Suggested Apogee Altitude = 750.000000 (km) Returned Error Message = Reentry during mission (no PMD req.). Released Year = 2022 (yr) Requirement = 61 Compliance Status = Pass ============== **INPUT** Space Structure Name = Lemur2_HIIB Space Structure Type = Payload Perigee Altitude = 575.000000 (km) Apogee Altitude = 575.000000 (km) Inclination = 31.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.013000 (m^2/kg) Start Year = 2015.500000 (yr) Initial Mass = 4.500000 (kg) Final Mass = 4.500000 (kg) Duration = 17.000000 (yr) Station Kept = False Abandoned = True PMD Perigee Altitude = -1.000000 (km) 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** Suggested Perigee Altitude = 575.000000 (km) Suggested Apogee Altitude = 575.000000 (km) Returned Error Message = Reentry during mission (no PMD req.). Released Year = 2024 (yr) Requirement = 61 Compliance Status = Pass ============== =============== End of Requirement 4.6 =============== 01 29 2015; 19:57:25PM *********Processing Requirement 4.7-1 Return Status : Passed ***********INPUT**** Item Number = 1 name = Lemur2_PSLV quantity = 1 parent = 0 materialID = 5 type = Box Aero Mass = 4.500000 Thermal Mass = 4.500000 Diameter/Width = 0.100000 Length = 0.340000 Height = 0.100000 name = Structure_tray quantity = 2 parent = 1 materialID = 9 type = Box Aero Mass = 0.200000 Thermal Mass = 0.200000 Diameter/Width = 0.100000 Length = 0.340000 Height = 0.005000 name = Structure_ribs quantity = 10 parent = 1 materialID = 9 type = Box Aero Mass = 0.010000 Thermal Mass = 0.010000 Diameter/Width = 0.012000 Length = 0.083000

Height = 0.006000 name = Structure_mountingplates quantity = 5 parent = 1 materialID = 9 type = Flat Plate Aero Mass = 0.100000 Thermal Mass = 0.100000 Diameter/Width = 0.080000 Length = 0.100000 name = PCB quantity = 15 parent = 1 materialID = 23 type = Flat Plate Aero Mass = 0.080000 Thermal Mass = 0.080000 Diameter/Width = 0.080000 Length = 0.080000 name = Lenses quantity = 2 parent = 1 materialID = 9 type = Cylinder Aero Mass = 0.200000 Thermal Mass = 0.200000 Diameter/Width = 0.030000 Length = 0.120000 name = Reaction Wheels quantity = 3 parent = 1 materialID = 67 type = Cylinder Aero Mass = 0.120000 Thermal Mass = 0.120000 Diameter/Width = 0.030000 Length = 0.020000 name = solar_panels quantity = 6 parent = 1 materialID = 23 type = Flat Plate Aero Mass = 0.100000 Thermal Mass = 0.100000 Diameter/Width = 0.083000 Length = 0.324000

name = solar_cells quantity = 61 parent = 1 materialID = 24 type = Flat Plate Aero Mass = 0.015000 Thermal Mass = 0.015000 Diameter/Width = 0.040000 Length = 0.080000 **************OUTPUT**** Item Number = 1 name = Lemur2_PSLV Demise Altitude = 77.996621 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Structure_tray Demise Altitude = 76.444527 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Structure_ribs Demise Altitude = 77.121871 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Structure_mountingplates Demise Altitude = 75.443886 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = PCB Demise Altitude = 76.127535 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Lenses Demise Altitude = 72.843566 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Reaction Wheels Demise Altitude = 0.000000 Debris Casualty Area = 1.169982

Impact Kinetic Energy = 202.520203 ************************************* name = solar_panels Demise Altitude = 77.271605 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = solar_cells Demise Altitude = 77.747871 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* ***********INPUT**** Item Number = 2 name = Lemur2_Soyuz quantity = 1 parent = 0 materialID = 9 type = Box Aero Mass = 4.500000 Thermal Mass = 4.500000 Diameter/Width = 0.100000 Length = 0.340000 Height = 0.100000 name = Lemur2_Soyuz quantity = 1 parent = 1 materialID = 9 type = Box Aero Mass = 4.500000 Thermal Mass = 4.500000 Diameter/Width = 0.100000 Length = 0.340000 Height = 0.100000 **************OUTPUT**** Item Number = 2 name = Lemur2_Soyuz Demise Altitude = 77.998722 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Lemur2_Soyuz Demise Altitude = 66.439011

Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* ***********INPUT**** Item Number = 3 name = Lemur2_Falcon9 quantity = 1 parent = 0 materialID = 5 type = Box Aero Mass = 4.500000 Thermal Mass = 4.500000 Diameter/Width = 0.100000 Length = 0.340000 Height = 0.100000 name = Lemur2_Falcon9 quantity = 1 parent = 1 materialID = 5 type = Box Aero Mass = 4.500000 Thermal Mass = 4.500000 Diameter/Width = 0.100000 Length = 0.340000 Height = 0.100000 **************OUTPUT**** Item Number = 3 name = Lemur2_Falcon9 Demise Altitude = 77.997660 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Lemur2_Falcon9 Demise Altitude = 64.797706 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* ***********INPUT**** Item Number = 4 name = Lemur2_HIIB quantity = 1 parent = 0

materialID = 9 type = Box Aero Mass = 4.500000 Thermal Mass = 4.500000 Diameter/Width = 0.100000 Length = 0.340000 Height = 0.100000 name = Lemur2_HIIB quantity = 1 parent = 1 materialID = 9 type = Box Aero Mass = 4.500000 Thermal Mass = 4.500000 Diameter/Width = 0.100000 Length = 0.340000 Height = 0.100000 **************OUTPUT**** Item Number = 4 name = Lemur2_HIIB Demise Altitude = 77.995176 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Lemur2_HIIB Demise Altitude = 64.728616 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* =============== End of Requirement 4.7-1 ===============


Document Created: 2015-01-29 18:38:17
Document Modified: 2015-01-29 18:38:17
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