Exhibit B

0780-EX-PL-2015 Text Documents

Spire Global, Inc.

2016-01-07ELS_171133

Exhibit B – Orbital Debris  Assessment  Report  (“ODAR”)

2015 Orbital Debris Assessment Report LEMUR CUBESAT CONSTELLATION PREPARED BY: SPIRE GLOBAL, 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 nanosatellite fleet is to provide high-revisit maritime domain monitoring data and GPS-Radio Occultation data. The mission consists of a set of 175 3U Cubesats satellites launched over the course of 2 years as secondary payloads on a series of many separate launch vehicles into various orbital planes, the result being a distributed constellation to improve average revisit time globally. Foreign None Government Involvement Project Milestones: LEMUR satellites will be launched typically 2 to 8 at a time; this will be dependent on the orbital characteristics, the launch vehicle reliability as well as schedule certainty. As a Proposed Launch result of launching a small number of satellites at a time, Spire will have an extensive Date: launch manifest in order to reach the full constellation of 175 satellites. Because of the nature of the secondary payload market, there is limited control over the future planning Proposed Launch of the launches; launches will be booked as they become available, typically within a Vehicles: year of launch. Proposed Launch While the specific launches and schedule remain TBD, the bounding orbital Sites: characteristics of the constellation are known. All LEMUR satellites will be launched to an altitude of 650km or lower, with inclinations ranging from equatorial to polar sun- Launch Vehicle Operator: synchronous. Most secondary opportunities currently available to cubesats are to 500km SSO or 600km SSO orbits. Spire will also be interested in mid inclinations and equatorial orbits. The table below includes a set of the orbital planes that are desired from the constellation performance standpoint; these planes are also representative of the available launch opportunities for secondary cubesat payloads in the timeframe desired. Number of Satellites Altitude Inclination ~60 500 km ~98 deg ~55 600 km ~98 deg ~40 500 km ~52 deg ~20 500km ~ 0-10 deg 400km (ISS) – 51.6 deg – Upper and Lower Limit 650 km ~6 deg 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 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 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. 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. The satellite is nominally expected to reenter the atmosphere 10 years following deployment from the launch vehicle. Selection of Orbit: The selection of orbits was made due to payload capability, available launch opportunities and orbital lifetime considerations. Potential Physical As the satellite does not have any propulsion systems, its orbit 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, over-discharging, internal shorts, and external shorts. The battery pack onboard LEMUR 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 1 describes the mission scenarios for which lifetime analysis of LEMUR 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 (2x 0.5m whip antennas, 3x 0.3m whip antennas) was neglected; as such, the effective area-to-mass calculated below is a conservative case. Table 1 - Area-to-Mass Ratio of LEMUR-2 Satellites in Various Mission Scenarios Scenario Description Effective Area- to-Mass (m2/kg) 1 Satellite ▪ Solar arrays deploy only after 5 years 0.0000 (yrs 1-5) Nonfunctional ▪ Satellite tumbles randomly 0.0169 (yrs 5+) Solar panel ▪ Solar panels fail to deploy failure ▪ Satellite maintains +Z axis nadir 0.0130 ▪ Position around Z axis as planned for mission operations Operational, ▪ Solar panels deploy nominal ▪ Satellite maintains +Z axis nadir 0.0208 ▪ Position around Z axis as planned for mission operations ADCS ▪ Solar arrays deploy 0.0169 Nonfunctional ▪ Satellite tumbles randomly 1 For the analysis, it was conservatively assumed that the satellite does not lose any altitude during the first 5 years (ie, an area of 0).

Table 2 shows the simulated orbital dwell time for a LEMUR 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 Satellite in Each Planned Orbit and Mission Scenario Orbital Lifetime (Years) 600 km Sun- 500 km Sun- 500 km Mid Effective Upper Bound Lower Bound Synchronous Synchronous Inclination Area-to- Description Mass (m2/kg) 600km x 500km x 500km, 500km x 650km x 400km x 400km, 600km, 98 deg 98 deg 500km, ~52 deg 650km, 6 deg ~52 deg Satellite 19.8 7.1 7.2 23.8 2 1.0 0.0074 Nonfunctional Solar panels 11.1 6.1 6.1 23.2 0.5 0.0130 failure ADCS 9.0 5.0 5.7 18.8 0.3 0.0169 Nonfunctional Operational, 8.3 5.6 5.2 17.3 0.4 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: 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 2 No decay in first 5 years, after that deployment of antenna and solar panel due to decay of nylon filament with an effective area/mass of 0.0169 m2/kg

4.6-3, Disposal for space structures between LEO and GEO: N/A 4.6-4, Reliability of postmission disposal operations: COMPLIANT

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. 04 22 2015; 22:49:55PM DAS Application Started 04 22 2015; 22:49:57PM Opened Project C:\Program Files (x86)\NASA\DAS 2.0\project\ 04 22 2015; 22:50:57PM Opened Project C:\Users\nanosatisfi\Downloads\ODAR-2015-04-22\ODAR\ 04 22 2015; 22:51:47PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2015.500000 (yr) Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 51.600000 (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 = 7.178645 (yr) Time Spent in LEO during Lifetime = 7.178645 (yr) Last year of Propagation = 2022 (yr) Returned Error Message: Object reentered 04 22 2015; 22:52:41PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2015.500000 (yr) Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 51.600000 (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 = 6.121834 (yr) Time Spent in LEO during Lifetime = 6.121834 (yr) Last year of Propagation = 2021 (yr) Returned Error Message: Object reentered 04 22 2015; 22:52:51PM Science and Engineering - Orbit Lifetime/Dwell Time

**INPUT** Start Year = 2015.500000 (yr) Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 51.600000 (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 = 5.700205 (yr) Time Spent in LEO during Lifetime = 5.700205 (yr) Last year of Propagation = 2021 (yr) Returned Error Message: Object reentered 04 22 2015; 22:53:02PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2015.500000 (yr) Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 51.600000 (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 = 5.212868 (yr) Time Spent in LEO during Lifetime = 5.212868 (yr) Last year of Propagation = 2020 (yr) Returned Error Message: Object reentered 04 22 2015; 22:53:24PM 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 = 0.020800 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 8.268309 (yr)

Time Spent in LEO during Lifetime = 8.268309 (yr) Last year of Propagation = 2023 (yr) Returned Error Message: Object reentered 04 22 2015; 22:53:38PM 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 = 0.016900 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 8.974675 (yr) Time Spent in LEO during Lifetime = 8.974675 (yr) Last year of Propagation = 2024 (yr) Returned Error Message: Object reentered 04 22 2015; 22:53:46PM 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 04 22 2015; 22:53:57PM 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 = 0.007400 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 19.805613 (yr) Time Spent in LEO during Lifetime = 19.805613 (yr) Last year of Propagation = 2035 (yr) Returned Error Message: Object reentered 04 22 2015; 22:55:47PM Mission Editor Changes Applied 04 22 2015; 22:56:24PM Mission Editor Changes Applied 04 22 2015; 22:56:28PM Project Data Saved To File 04 22 2015; 22:56:48PM Processing Requirement 4.3-1: Return Status : Not Run ===================== No Project Data Available ===================== =============== End of Requirement 4.3-1 =============== 04 22 2015; 22:56:51PM Processing Requirement 4.3-2: Return Status : Passed ===================== No Project Data Available ===================== =============== End of Requirement 4.3-2 =============== 04 22 2015; 22:56:53PM Requirement 4.4-3: Compliant =============== End of Requirement 4.4-3 =============== 04 22 2015; 22:57:01PM Processing Requirement 4.5-1: Return Status : Passed ============== Run Data ============== **INPUT** Space Structure Name = Lemur2_650Equatorial 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 = 0.020800 (m^2/kg) Start Year = 2015.500000 (yr) Initial Mass = 4.500000 (kg)

Final Mass = 4.500000 (kg) Duration = 17.300000 (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_600SSO 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 = 0.020800 (m^2/kg) Start Year = 2015.500000 (yr) Initial Mass = 4.500000 (kg) Final Mass = 4.500000 (kg) Duration = 8.300000 (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_500km52deg Space Structure Type = Payload Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 51.600000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass Ratio = 0.020800 (m^2/kg) Start Year = 2015.500000 (yr) Initial Mass = 4.500000 (kg) Final Mass = 4.500000 (kg) Duration = 5.200000 (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 = 0.000000 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range Status = Pass ============== =============== End of Requirement 4.5-1 =============== 04 22 2015; 22:57:09PM Requirement 4.5-2: Compliant 04 22 2015; 22:57:12PM Processing Requirement 4.6 Return Status : Passed ============== Project Data ============== **INPUT** Space Structure Name = Lemur2_650Equatorial 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 = 0.020800 (m^2/kg) Start Year = 2015.500000 (yr) Initial Mass = 4.500000 (kg) Final Mass = 4.500000 (kg) Duration = 17.300000 (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 = 2032 (yr) Requirement = 61 Compliance Status = Pass ============== **INPUT** Space Structure Name = Lemur2_600SSO 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 = 0.020800 (m^2/kg) Start Year = 2015.500000 (yr) Initial Mass = 4.500000 (kg) Final Mass = 4.500000 (kg) Duration = 8.300000 (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 = 2023 (yr) Requirement = 61 Compliance Status = Pass ============== **INPUT** Space Structure Name = Lemur2_500km52deg Space Structure Type = Payload Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 51.600000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.020800 (m^2/kg) Start Year = 2015.500000 (yr) Initial Mass = 4.500000 (kg) Final Mass = 4.500000 (kg) Duration = 5.200000 (yr) Station Kept = False Abandoned = True PMD Perigee Altitude = 248.048791 (km) PMD Apogee Altitude = 256.789865 (km) PMD Inclination = 51.571325 (deg) PMD RAAN = 7.848664 (deg) PMD Argument of Perigee = 74.605471 (deg) PMD Mean Anomaly = 0.000000 (deg) **OUTPUT** Suggested Perigee Altitude = 248.048791 (km) Suggested Apogee Altitude = 256.789865 (km) Returned Error Message = Passes LEO reentry orbit criteria. Released Year = 2020 (yr) Requirement = 61

Compliance Status = Pass ============== =============== End of Requirement 4.6 =============== 04 22 2015; 22:58:19PM *********Processing Requirement 4.7-1 Return Status : Passed ***********INPUT**** Item Number = 1 name = Lemur2_650Equatorial 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_650Equatorial 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_600SSO 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_600SSO 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_600SSO Demise Altitude = 77.998722 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Lemur2_600SSO Demise Altitude = 66.439011 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 *************************************

************************************* ***********INPUT**** Item Number = 5 name = Lemur2_500km52deg 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_500km52deg 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 = 5 name = Lemur2_500km52deg Demise Altitude = 77.993738 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Lemur2_500km52deg Demise Altitude = 65.304866 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* =============== End of Requirement 4.7-1 =============== 11 23 2015; 18:34:55PM DAS Application Started 11 23 2015; 18:34:56PM Opened Project C:\Users\jspark\Desktop\Lemur-2\ODAR\ 11 23 2015; 18:35:04PM Processing Requirement 4.3-1: Return Status : Not Run ===================== No Project Data Available

===================== =============== End of Requirement 4.3-1 =============== 11 23 2015; 18:36:25PM Mission Editor Changes Applied 11 23 2015; 18:36:47PM Processing Requirement 4.3-1: Return Status : Not Run ===================== No Project Data Available ===================== =============== End of Requirement 4.3-1 =============== 11 23 2015; 18:36:51PM Processing Requirement 4.3-2: Return Status : Passed ===================== No Project Data Available ===================== =============== End of Requirement 4.3-2 =============== 11 23 2015; 18:36:53PM Requirement 4.4-3: Compliant =============== End of Requirement 4.4-3 =============== 11 23 2015; 18:36:57PM Processing Requirement 4.5-1: Return Status : Passed ============== Run Data ============== **INPUT** Space Structure Name = Lemur2_500kmSSO Space Structure Type = Payload Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 98.000000 (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 = 7.100000 (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 = 0.000000 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range Status = Pass ============== **INPUT** Space Structure Name = Lemur2_400km51deg Space Structure Type = Payload Perigee Altitude = 400.000000 (km) Apogee Altitude = 400.000000 (km) Inclination = 51.600000 (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 = 1.000000 (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 = 0.000000 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range Status = Pass ============== =============== End of Requirement 4.5-1 =============== 11 23 2015; 18:37:04PM Requirement 4.5-2: Compliant 11 23 2015; 18:37:06PM Processing Requirement 4.6 Return Status : Passed ============== Project Data ============== **INPUT** Space Structure Name = Lemur2_500kmSSO Space Structure Type = Payload Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 98.000000 (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 = 7.100000 (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 = 500.000000 (km) Suggested Apogee Altitude = 500.000000 (km) Returned Error Message = Reentry during mission (no PMD req.). Released Year = 2021 (yr) Requirement = 61 Compliance Status = Pass ============== **INPUT** Space Structure Name = Lemur2_400km51deg Space Structure Type = Payload

Perigee Altitude = 400.000000 (km) Apogee Altitude = 400.000000 (km) Inclination = 51.600000 (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 = 1.000000 (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 = 400.000000 (km) Suggested Apogee Altitude = 400.000000 (km) Returned Error Message = Reentry during mission (no PMD req.). Released Year = 2016 (yr) Requirement = 61 Compliance Status = Pass ============== =============== End of Requirement 4.6 ===============


Document Created: 2015-12-15 10:24:42
Document Modified: 2015-12-15 10:24:42
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