Attachment Exhibit C

This document pretains to SAT-AMD-20161114-00107 for Amended Filing on a Satellite Space Stations filing.

IBFS_SATAMD2016111400107_1158060

2016 Spire Global, Inc. Orbital Debris Assessment Report: 100 LEMUR-2 Phase IB and IC Satellites

Revision History Revision Description of Revisions Release Date 1 Initial Release 11/11/2016 An orbital debris risk assessment of 100 LEMUR-2 Phase IB and Phase IC satellites to reflect upcoming launches listed in this ODAR

Section 1: Program Management and Mission Overview Program / Project Peter Platzer Manager Mission The purpose of the LEMUR-2 satellite fleet is to provide high-revisit maritime and aircraft Description domain monitoring data and weather data. This orbital debris risk assessment covers 100 LEMUR-2 Phase IB and Phase IC satellites proposed to be launched by Spire Global, Inc. (“Spire”) over 2017-2018. Foreign None Government Involvement Project Milestones LEMUR-2 Phase IB and Phase IC satellites will be launched up to 16 at a time depending on available capacity, quality of orbit, service and fleet replenishment needs, Proposed and risk profiles of the launch vehicle and campaign. Launch Date Given that Spire is applying for a number of orbits, this orbital debris risk assessment Proposed covers all such orbits. Spire is also seeking authority to deploy from the International Launch Vehicles Space Station (“ISS”) and so that orbit is also considered. Proposed The following deployments are considered in this Orbital Debris Assessment Report Launch Sites (“ODAR”):1 Launch Vehicle Launch # Launch Provider/Vehicle Launch Date (NET) Altitude (km) Inclination (+/- 1 deg) Operator Launch 1 SpaceX/Falcon9 Q1 2017 450x720 SSO (98) Launch 2 ISRO/PSLV Q1 2017 580 SSO (98) Launch 3 Roscosmos/Soyuz Q1 2017 600 SSO (98) Launch 4 ISRO/PSLV Q2 2017 500 SSO (98) Launch 5 Orbital/Minotaur4 Q3 2017 400 x 600 24 Launch 6 Roscosmos/Soyuz Q2 2017 600 SSO (98) Launch 7 Roscosmos/Soyuz Q3 2017 600 SSO (98) Launch 8 Orbital/Antares Q1 2017 Up to 500 ISS (51.6) Launch 9 Orbital/Antares Q2 2017 Up to 500 ISS (51.6) Launch 10 ISRO/PSLV Q3 2017 500 SSO (98) Launch 11 SpaceX/Falcon9 Q4 2017 575 SSO (98) Launch 12 Rocket Lab/Electron Q2 2017 500 SSO (98) Launch 13 Rocket Lab/Electron Q3 2017 450 45 Launch 14 Virgin/LauncherOne Q3 2017 500 90 Launch 15 Virgin/LauncherOne Q4 2017 500 87.9 Launch 16 Roscosmos/Soyuz Q4 2017 585 SSO (98) ISS Resupply Varies Varies ~400 ~51.6 1 Note that the Formosat-5 launch was previously analyzed in an ODAR, and no changes have occurred to that previous analysis. Spire does not seek authority to launch more than 8 satellites on Formosat-5, as agreed with ORBCOMM License Corp, but includes the orbit here for completeness.

Mission Duration The operational lifetime of each LEMUR-2 Phase IB and Phase IC satellite is estimated to be up to 2 years following deployment from the launch vehicle. Selection of Orbit Orbits are selected based on current availability. Potential Physical Because the LEMUR-2 Phase IB and Phase IC satellites do not have any propulsion Interference with systems, their orbit will naturally decay following deployment from either the launch Other Orbiting vehicle or the ISS. Objects As detailed in Section 5, the probability of physical interference between the LEMUR-2 Phase IB and Phase IC satellites and other space objects complies with Requirement 4.5 of NASA-STD-8719.14A.

ODAR Section 2: Spacecraft Description Physical Description: Property Value Total Mass at Launch 4.5 kg Dry Mass at Launch 4.5 kg Form Factor 3U CubeSat COG <3 cm radius from geometric center Envelope (stowed) 100 mm x 100 mm x 340.5 mm (excluding dynamic envelope) Envelope (deployed) 1 m x 1 m x 300 mm Propulsion Systems None Fluid Systems None AOCS Stabilization/pointing with 3x orthogonal reaction wheels, desaturation + coarse pointing with magnetorquers, and 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 Spire’s LEMUR-2 Phase IB and Phase IC satellites do not release objects during deployment or operation. Therefore, Requirements 4.3-1 and 4.3-2 of NASA-STD-8719.14A are not applicable.

ODAR Section 4: Assessment of Spacecraft Intentional Breakups and Potential for Explosions Potential causes for spacecraft breakup: LEMUR-2 Phase IB and Phase IC satellites have no propulsion and accordingly do not carry highly volatile rocket propellant. The only energy sources (kinetic, chemical, or otherwise) onboard the spacecraft are a Lithium- Polymer battery system and reaction wheels. Thus, the only two plausible causes for breakup of the LEMUR-2 Phase IB and Phase IC satellites are the following: 1. energy released from onboard batteries, and 2. 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 LEMUR-2 Phase IB and Phase IC satellites are two 42Wh Lithium-Polymer batteries, which 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 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 Plan: The battery pack onboard the LEMUR-2 Phase IB and Phase IC satellites has been designed and built to comply with all controls / process requirements identified in NASA Report JSC-20793 Section 5.4.3 to mitigate the chance of any accidental venting / explosion caused by the above failure modes. The reaction wheels onboard the LEMUR-2 Phase IB and Phase IC satellites are limited with respect to maximum rotational speed of the wheels and are contained within a sealed compartment, thus mitigating any risk of breakup of the wheels themselves into debris. Detailed plan for any designed spacecraft breakup, including explosions and intentional collisions: There is no planned breakup of the satellites on-orbit. 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 N/A about Earth or the Moon: 4.4-3, Limiting the long-term risk to other space systems from planned breakups: N/A 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: N/A 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 larger than 10 cm: The probability of a collision of any of the LEMUR-2 Phase IB and Phase IC satellites with an orbiting object larger than 10 cm in diameter was calculated using the National Aeronautics and Space Administration’s (“NASA’s”) Debris Assessment Software (“DAS”) 2.0.2 software. Table 1 below shows the risk for all orbits into which LEMUR-2 Phase IB and Phase IC satellites may be deployed in each of three different area/mass ratio scenarios, including a worst case scenario. The table shows the risk both at the expected (nominal) orbital dwell times and at the worst-case dead on arrival dwell time. Because Launch 8 and Launch 9 are potential Above Station Deployments where the ultimate altitude will be determined by NASA (including potentially requiring a below station deployment), the table below shows a worst case analysis of 500 km. ISS deployments are from in front and below the ISS at the time of deployment, typically in a range of 385 km to 400 km, as directed by the ISS Program. The table below shows a worst case of 400 km. Certain deployments have similar inclinations but slightly different altitudes. Where the altitude is slightly different, Spire groups the launches together under the worst case (highest) altitude.

Table 1 –Collision Risk with Objects Larger Than 10 cm 600 km, 580 km, 450x720 km, 400x600 km, 500 km, 500 km, 500 km, 500 km, 450 km, 400 km, 98 degrees 98 degrees 98 degrees 24 degrees 98 degrees 51.6 degrees 90 degrees 87.9 degrees 45 degrees 51.6 degrees Effective Area-to- Launch Name Mass (m2/kg) Satellite Nonfunctional 0.0074 2 x 10-6 1 x 10-6 1 x 10-6 0 0 0 0 0 0 0 ADCS 1 x 10-6 1 x 10-6 0 0 0 0 0 0 0.0169 2 x 10-6 0 Nonfunctional Operational, 2 x 10-6 2 x 10-6 1 x 10-6 0 0 0 0 0 0 0 0.0208 Nominal

Probability for collision with objects 10 cm or less: NASA’s DAS returned a response of Compliant with Requirement 4.5-2 of NASA-STD-8719.14A in all deployment scenarios. 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

ODAR Section 6: Assessment of Spacecraft Postmission Disposal Plans and Procedures Description of disposal option selected: Following its deployment, a LEMUR-2 Phase IB and Phase IC satellite’s orbit will naturally decay until it reenters the atmosphere. Table 2 describes the mission scenarios for which lifetime analysis of a LEMUR-2 Phase IB and Phase IC satellite 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 LEMUR-2 Phase IB and Phase IC satellite and deployed arrays. For purposes of Section 6, drag area from deployed antennas was omitted; as such, the effective area-to-mass calculated below is a conservative case. Table 2 - Area-to-Mass Ratio of LEMUR-2 Phase IB and Phase IC Satellites in Various Mission Scenarios Scenario Description Effective Area-to-Mass (m2/kg) Satellite ▪ Solar arrays fail to deploy 0.0074 for 5 years Nonfunctional ▪ Satellite tumbles randomly 0.0169 thereafter2 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 Table 3 below shows the simulated orbital dwell time for a LEMUR-2 Phase IB and Phase IC satellite in each of the deployment scenarios. Because Launch 8 and Launch 9 are potential Above Station Deployments where the ultimate altitude will be determined by NASA (including potentially requiring a below station deployment), the table below shows a worst case analysis of 500 km. ISS deployments are from in front and below the ISS at the time of deployment, typically in a range of 385 km to 400 km, as directed by the ISS Program. The table below shows a worst case of 400 km. Certain deployments have similar inclinations but slightly different altitudes. Where the altitude is slightly different, Spire groups the launches together under the worst case (highest) altitude. 2 This conservatively assumes the solar panels do not deploy in the first five years and deployment only occurs after nylon burn wire degrades in natural sunlight (i.e., double fault situation).

Table 3 – Orbit Dwell Time for LEMUR-2 Phase IB and Phase IC Satellite in Each Planned Deployment 600 km, 580 km, 450x720 km, 400 km x 600 km, 500 km, 500 km, 500 km, 500 km, 450 km, 400 km, Effective 98 degrees 98 degrees 98 degrees 24 degrees 98 degrees 51.6 degrees 90 degrees 87.9 degrees 45 degrees 51.6 degrees Area-to- Description Mass (m2/kg) Satellite 12.83 11.93 9.39 4.9 6 6.1 6 6 4.7 2.7 Nonfunctional 0.0074 7.8 6.9 6.20 3.9 4.7 4.8 4.7 4.7 3.7 .8 ADCS 0.0169 Nonfunctional 7 6.4 5.81 3.7 4.5 4.6 4.5 4.5 3.2 .7 Operational, 0.0208 Nominal 3 To ensure that Spire exceeds the NASA standard in all scenarios, Spire has included a double fault-tolerant solar panel deployment mechanism, which will provide sufficient surface area and drag to comply with the NASA standard even if the LEMUR-2 Phase IB and Phase IC satellites are dead on arrival. The LEMUR-2 Phase IB and Phase IC satellite’s solar panels are part of a built-in, post-deployment sequence programmed into onboard software prior to launch, which requires no direction from the ground. If for some reason the onboard sequence fails, solar array deployment can be commanded from the ground. If a LEMUR-2 Phase IB and Phase IC satellite is non-communicative, an entirely passive, redundant fail-safe is included on all LEMUR-2 Phase IB and Phase IC satellites in the form of a burn wire. The tensile strength of the burn wire has been tested and verified to degrade to a breaking point after 3600 hours or 150 days of UV radiation exposure. 3 Spire’s worst-case scenario for dwell time above conservatively models 5 years of non-deployed solar panels and no loss of altitude during those 5 years, followed by the dwell times for an Attitude Determination and Control nonfunctional satellite, even though a non-deployed solar panel LEMUR-2 would still have some surface area that would cause some loss of altitude during that period. As such, this is a conservative worst-case scenario.

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 low-Earth orbit (“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 geostationary orbit (“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

ODAR Section 7: Assessment of Spacecraft Reentry Hazards NASA DAS was used to test the major spacecraft components for re-entry hazards. The major components tested included:  Solar panels and cells  GPS antennas  PCB circuit boards  Primary structure  Cameras  Reaction wheel assembly 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 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


Document Created: 2016-11-14 02:23:22
Document Modified: 2016-11-14 02:23:22
© 2024 FCC.report
This site is not affiliated with or endorsed by the FCC