Swarm ODAR Signed 7 June 2017

0305-EX-CN-2017 Text Documents

Swarm Technologies, Inc.

2017-06-07ELS_193219

Exhibit B – Orbital Debris Assessment Report (“ODAR”) SWARM Orbital Debris Assessment Report SWARM TECHNOLOGIES MISSION PROFILE PREPARED BY: SWARM TECHNOLOGIES INC REVISION 1, April 23, 2017 ODAR Signature Approval Program/ Project Sara Spangelo Manager Signature Date June 7, 2017 ODAR Section 1: Program Management and Mission Overview Program/ Project Sara Spangelo Manager Mission Description This mission is a technology demo for two-way communications satellites, data relay, and a new attitude control system. Foreign Government None Involvement Project Milestones The project milestones for the Swarm satellites align with the launch of the vehicles into orbit, including a delivery of the spacecraft one month prior to launch to Spaceflight services. Proposed Launch Sept 15, 2017 Date: Proposed Launch PSLV Vehicles Number of Satellites: 4 Altitude: 580 km Inclination:97.7 degrees (​SSO​) LTDN 9:30AM Proposed Launch SHAR, India Sites

Launch Vehicle Astrix/ ISRO Operator: Mission Duration: The operational lifetime of the hardware for each satellite is designed to be up to​ 10​ years following deployment from the launch vehicle. The orbital lifetime for the satellites is nominally expected to be between ​4.4 to 9.9 year​s, depending on the vehicle’s orbit, and solar influence of the Earth’s atmosphere, as described in Section 6. Launch / Launch Deployment Profile: The Swarm satellites will be injected directly into the target orbits outlined in the table above. Checkout For up to 1 month following deployment into orbit, the Swarm 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 Swarm satellites from the launch vehicle, and successful checkout. The operational phase continues until the end of the market study. Post-mission 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 7.7 y​ears following deployment from the launch vehicle, as detailed in Appendix B: Swarm BEEs Orbit Lifetime. Selection of Orbit: The selection of the chosen orbit was made due to available launch opportunities. Potential Physical As the satellite does not have any propulsion systems, its orbit will naturally Interference with decay following deployment from the launch vehicle. Other Orbiting Object: ​ n 5, the probability of physical interference between the As detailed in Sect​io 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 0.732 kg (all four satellites), 0.182 kg (each individual satellite) Dry Mass at Launch 0.732 kg (all four satellites), 0.182 kg (each individual satellite) Form Factor 1/4U satellites, Qty 4 stacked into form-factor of a 1U CubeSat COG < 0.170 cm in vertical direction from geometric center Envelope (stowed) 100mm x 100mm x 113.5mm (all four satellites) Envelope (deployed) 100mm x 100mm x 113.5mm (all four satellites) Deployed dipole antenna tip to tip is 892 mm Propulsion Systems None Fluid Systems None AOCS Passive stabilization about two axis, GPS navigation Range Safety/ None Pyrotechnic Devices Electrical Generation Solar cells Electrical Storage Rechargeable lithium-ion battery. Qty 1: 18650B Panasonic cell. 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 2.1.2 log demonstrating the compliance to the above requirements is available in Appendix A – “DAS 2.1.2 Log”. ODAR Section 4: Assessment of Spacecraft Intentional Breakups and Potential for Explosions Potential causes for spacecraft breakup: There is only one plausible causes for breakup of the satellites: ● Energy released from onboard Lithium-ion battery from the unlikely event of overcharging or shorts Summary of failure modes and effects analysis of all credible failure modes which may lead to an accidental explosion: The battery aboard the satellite is a 12.5 Whr Lithium-Ion battery, which represents the only credible failure mode during which stored energy is released. The main failure modes associated with Lithium Ion batteries result from overcharging, over-discharging, internal shorts, and external shorts. The battery onboard Swarm BEE 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. 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 end of mission, all radio transmissions and beacons will be disabled. Spacecraft transmissions are only initiated by ground command and self terminate. All RF transmissions from the satellite can be disabled via command from the ground. 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 2.1.2 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 2.1.2 log demonstrating the compliance to the above requirements is available in Appendix A – “DAS 2.1.2 Log”. ODAR Section 6: Assessment of Spacecraft Post-mission 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 Swarm BEEs 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. The satellites will be deployed from the P-POD with a spring and will separate from one another with ​separation springs in the 1/4U feet. Drag area from deployed antennas (2x ​446mm whip antennas) was neglected; as such, the effective area-to-mass calculated below is a conservative case. Table 1 - Area-to-Mass Ratio of Swarm Satellites in Various Mission Scenarios Scenario Description Effective Area-to-Mass (m​2​/kg) Operational, Nominal ● Satellite maintains +Z axis nadir 0.0154

● Satellite maintains position around Z axis as planned for mission operations ADCS Nonfunctional ● Satellite tumbles randomly 0.0350 Table 2 shows the simulated orbital dwell time for a Swarm BEE satellite for the range of possible orbits, in each of the identified mission scenarios. In all mission scenarios and orbits, the dwell time of the satellite was simulated us​ing DAS 2.1.2 software to be less than 10 years. Table 2 – Orbit Dwell Time for Swarm BEE Satellite in Each Planned Orbit and Mission Scenario Orbital Lifetime (years) Case Nominal Lowest Altitude Highest Altitude Launch Q3 2017 PSLV Q3 2017 PSLV Q3 2017 PSLV (4 Satellites) (4 Satellites) (4 Satellites) Orbit (Launch Sept. 580 km x 580 km 500 km x 500 km 600 km x 600 km 17, 2017, 9:30 LTDN) SSO (97.7 deg) SSO (97.4 deg) SSO (97.8 deg) Scenario Effective Area-to-Mass (m​2​/kg) Operational, Nominal 0.0154 7.68 5.23 9.87 ADCS Nonfunctional 0.0350 5.80 4.38 6.27 Identification of Systems Required for Post-mission Disposal:​ None Plan for Spacecraft Maneuvers required for Post-mission 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 4.6-3, Disposal for space structures between LEO and GEO: N/A 4.6-4, Reliability of post-mission 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 (grams) Shape Size (cm) Solar Panels Copper, Glass 2 1 Box 79 x 50 x 0.3 Main Board FR4 2 48 Box 98 x 98 x 1.6 PCB Primary Al 6061 1 32 Box 100 x 100 x 27 Structure Battery Li-Ion 1 48.5 Cylinder 18 (r) x 67 (l) Summary of objects expected to survive an uncontrolled ree​ntry (using DAS 2.1.2 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 2.1.2 log demonstrating the compliance to Requirement 4.7-1 is available in Appendix A – “DAS 2.1.2 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 post-mission disposal: N ​ /A

Probability of tether colliding with large space objects:​ N/A Probability of tether being severed during mission or after post-mission 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 ODAR Section 9: Orbital Tracking Methodology In consideration of the small satellite form factor, the satellites employ a radar return enhancement technology to ensure passive ground tracking capability by third party tracking services. Each of our satellites is a ¼-U size, or 100 mm x 100 mm x 28 mm, and is composed of an aluminum frame, and 6 PCBs on each face. Each 100 mm x 100 mm face PCB has a built-in ground plane and solar cells, which provide the same radar return as a 1U satellite, or a 3U satellite end-on. Each 100 mm x 28 mm face is composed of a passive Ku-band radar reflector, specifically designed to be used to passively increase the radar cross section of small satellites for enhanced tracking. Each 100 mm x 28 mm face has an equivalent radar return signature of a 100 mm x 280 mm area (or 10x larger than it’s actual area), in effect providing a radar signature equivalent of a 3U satellite, side-on. The passive radar retroreflector was designed for the Haystack Auxiliary RADAR (HAX) operated by MIT Lincoln Labs, which has the following capabilities: Peak Power: 50 Kilowatts Center frequency: 16.7 GHz (Ku Band) Bandwidth: 2 GHz Antenna Diameter: 12.2 meters Antenna Gain (at 16.7 GHz): 63.6 dB Antenna Beamwidth: 0.10 degrees Polarization: Right Hand Circular Pulse Length: 1.64 milliseconds Pulse Repetition Frequency: 60 Hz The radar retroreflectors were developed by Terry Albert at SPAWAR. Albert, Terry R CIV SPAWARSYSCEN-PACIFIC, 56290 <terry.albert@navy.mil> The HAX Radar, which is part of the NORAD system, operated by the Joint Space Operations Center (JSpOC), ​ he radar ​reflectors will improve the RADAR return from the smallsat, and thereby will track our satellites​. T improve the ability to detect and track it. HAX can track the satellite any time the smallsat flies over it, and JSpOC calculates the TLEs from the RADAR returns. ​Any other radar unit in the Ku-band (14.7 GHz to 18.7 GHz) would similarly be able to track our satellites, and would see a signature that is the equivalent to a 3U satellite. Further, each of our satellites has an onboard GPS receiver, and the GPS location of each of our satellites is transmitted every time that the satellite is interrogated from the ground. We will have the ability to silence all RF transmission of the satellite by command from the ground. Our GPS data, and computed TLEs, will be provided to JSpOC, and any other entity that wishes to receive the live telemetry.

The GPS device will provide telemetry for the hardware lifetime of the satellite, which exceeds the anticipated orbital lifetime of the satellite. Appendix A: DAS 2.1.2 Log Below is the log of the DAS 2.1.2 simulation performed to demonstrate compliance to the above requirements. 04 20 2017; 15:03:17PM Activity Log Started 04 20 2017; 15:03:17PM New Project Files Created 04 20 2017; 15:04:46PM Mission Editor Changes Applied 04 20 2017; 15:04:50PM Project Data Saved To File 04 21 2017; 22:16:49PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2017.000000 (yr) Perigee Altitude = 600.000000 (km) Apogee Altitude = 600.000000 (km) Inclination = 97.792400 (deg) RAAN = 316.647000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.035000 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 6.269678 (yr) Time Spent in LEO during Lifetime = 6.269678 (yr) Last year of Propagation = 2023 (yr) Returned Error Message: Object reentered 04 21 2017; 22:17:01PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2017.000000 (yr) Perigee Altitude = 600.000000 (km) Apogee Altitude = 600.000000 (km) Inclination = 97.792400 (deg) RAAN = 316.647000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.015400 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 9.872690 (yr) Time Spent in LEO during Lifetime = 9.872690 (yr) Last year of Propagation = 2026 (yr) Returned Error Message: Object reentered 04 21 2017; 22:23:05PM Science and Engineering - Orbit Lifetime/Dwell Time

**INPUT** Start Year = 2017.000000 (yr) Perigee Altitude = 600.000000 (km) Apogee Altitude = 600.000000 (km) Inclination = 97.792400 (deg) RAAN = 316.647000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.015400 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 9.872690 (yr) Time Spent in LEO during Lifetime = 9.872690 (yr) Last year of Propagation = 2026 (yr) Returned Error Message: Object reentered 04 21 2017; 22:23:21PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2017.000000 (yr) Perigee Altitude = 600.000000 (km) Apogee Altitude = 600.000000 (km) Inclination = 97.792400 (deg) RAAN = 316.647000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.035000 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 6.269678 (yr) Time Spent in LEO during Lifetime = 6.269678 (yr) Last year of Propagation = 2023 (yr) Returned Error Message: Object reentered 04 21 2017; 22:23:48PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2017.000000 (yr) Perigee Altitude = 580.000000 (km) Apogee Altitude = 580.000000 (km) Inclination = 97.700000 (deg) RAAN = 316.647000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.035000 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 5.798768 (yr)

Time Spent in LEO during Lifetime = 5.798768 (yr) Last year of Propagation = 2022 (yr) Returned Error Message: Object reentered 04 21 2017; 22:24:08PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2017.000000 (yr) Perigee Altitude = 580.000000 (km) Apogee Altitude = 580.000000 (km) Inclination = 97.700000 (deg) RAAN = 316.647000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.015400 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 7.676934 (yr) Time Spent in LEO during Lifetime = 7.676934 (yr) Last year of Propagation = 2024 (yr) Returned Error Message: Object reentered 04 21 2017; 22:24:41PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2017.000000 (yr) Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 97.400000 (deg) RAAN = 316.647000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.015400 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 5.229295 (yr) Time Spent in LEO during Lifetime = 5.229295 (yr) Last year of Propagation = 2022 (yr) Returned Error Message: Object reentered 04 21 2017; 22:24:54PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2017.000000 (yr) Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 97.400000 (deg) RAAN = 316.647000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.035000 (m^2/kg)

**OUTPUT** Orbital Lifetime from Startyr = 4.380561 (yr) Time Spent in LEO during Lifetime = 4.380561 (yr) Last year of Propagation = 2021 (yr) Returned Error Message: Object reentered 04 24 2017; 14:19:28PM Processing Requirement 4.3-1: Return Status : Passed ============== Project Data ============== Objects Passing Through LEO = True Number of Objects = 1 **INPUT** Quantity = 4 Final Area-To-Mass Ratio = 0.035000 (m^2/kg) Perigee Altitude = 580.000000 (km) Apogee Altitude = 580.000000 (km) Inclination = 97.600000 (deg) RAAN = -1.000000 (deg) Argument of Perigee = -1.000000 (deg) Mean Anomaly = -1.000000 (deg) Released Year = 2017.000000 (yr) **OUTPUT** Perigee Altitude = -6378.136000 (km) Apogee Altitude = -6378.136000 (km) Inclination = 0.000000 (deg) Lifetime = 5.807192 (yr) Object Reentered within 25 years of Release = True Object-Time = 23.162218 (obj-yrs) Total Object-Time = 23.162218 (obj-yrs) Status = Pass Returned Error Message - Normal Processing ============== =============== End of Requirement 4.3-1 =============== 04 24 2017; 11:28:14AM Processing Requirement 4.3-2: Return Status : Passed =====================

No Project Data Available ===================== =============== End of Requirement 4.3-2 =============== 04 24 2017; 11:28:22AM Requirement 4.4-3: Compliant =============== End of Requirement 4.4-3 =============== 04 24 2017; 11:28:23AM Requirement 4.4-3: Compliant =============== End of Requirement 4.4-3 =============== 04 24 2017; 11:40:35AM Processing Requirement 4.5-1: Return Status : Passed ============== Run Data ============== **INPUT** Space Structure Name = SwarmBEE Space Structure Type = Payload Perigee Altitude = 580.000000 (km) Apogee Altitude = 580.000000 (km) Inclination = 97.600000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass Ratio = 0.035000 (m^2/kg) Start Year = 2017.000000 (yr) Initial Mass = 0.183100 (kg) Final Mass = 0.183100 (kg) Duration = 5.000000 (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 ===============

04 21 2017; 15:50:26PM Requirement 4.5-2: Compliant 04 21 2017; 15:53:04PM Processing Requirement 4.6 Return Status : Passed ============== Project Data ============== **INPUT** Space Structure Name = SwarmBEE Space Structure Type = Payload Perigee Altitude = 580.000000 (km) Apogee Altitude = 580.000000 (km) Inclination = 97.600000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.004150 (m^2/kg) Start Year = 2017.000000 (yr) Initial Mass = 0.156400 (kg) Final Mass = 0.156400 (kg) Duration = 5.000000 (yr) Station Kept = False Abandoned = True PMD Perigee Altitude = 576.060384 (km) PMD Apogee Altitude = 576.060384 (km) PMD Inclination = 97.748927 (deg) PMD RAAN = 344.718056 (deg) PMD Argument of Perigee = 8.342328 (deg) PMD Mean Anomaly = 0.000000 (deg) **OUTPUT** Suggested Perigee Altitude = 576.060384 (km) Suggested Apogee Altitude = 576.060384 (km) Returned Error Message = Passes LEO reentry orbit criteria. Released Year = 2045 (yr) Requirement = 61 Compliance Status = Pass ============== =============== End of Requirement 4.6 =============== 04 25 2017; 12:32:07PM *********Processing Requirement 4.7-1 Return Status : Passed ***********INPUT****

Item Number = 1 name = SwarmBEE quantity = 1 parent = 0 materialID = 5 type = Box Aero Mass = 0.183100 Thermal Mass = 0.183100 Diameter/Width = 0.100000 Length = 0.100000 Height = 0.028300 name = Solar Panels quantity = 2 parent = 1 materialID = 24 type = Box Aero Mass = 0.001000 Thermal Mass = 0.001000 Diameter/Width = 0.050000 Length = 0.079000 Height = 0.000300 name = Subsystem PCB quantity = 2 parent = 1 materialID = 5 type = Box Aero Mass = 0.041300 Thermal Mass = 0.041300 Diameter/Width = 0.098000 Length = 0.098000 Height = 0.001600 name = Primary Structure quantity = 1 parent = 1 materialID = 8 type = Box Aero Mass = 0.032000 Thermal Mass = 0.032000 Diameter/Width = 0.100000 Length = 0.100000 Height = 0.002700 name = Battery Pack quantity = 1 parent = 1 materialID = 5

type = Cylinder Aero Mass = 0.048500 Thermal Mass = 0.048500 Diameter/Width = 0.039000 Length = 0.067000 **************OUTPUT**** Item Number = 1 name = SwarmBEE Demise Altitude = 77.988602 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Solar Panels Demise Altitude = 77.964577 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Subsystem PCB Demise Altitude = 75.182190 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Primary Structure Demise Altitude = 76.035942 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Battery Pack Demise Altitude = 73.450478 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* ***********INPUT**** Item Number = 2 name = SwarmBEE2 quantity = 4 parent = 0 materialID = 5 type = Box Aero Mass = 0.183100 Thermal Mass = 0.183100

Diameter/Width = 0.100000 Length = 0.100000 Height = 0.028300 name = S quantity = 4 parent = 1 materialID = 5 type = Box Aero Mass = 0.183100 Thermal Mass = 0.183100 Diameter/Width = 0.100000 Length = 0.100000 Height = 0.028300 **************OUTPUT**** Item Number = 2 name = SwarmBEE2 Demise Altitude = 77.988602 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = S Demise Altitude = 69.932800 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* =============== End of Requirement 4.7-1 ===============


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Document Modified: 2019-04-24 10:55:21
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