LEMUR 1 Orbital Debris Assessment Report

0213-EX-PL-2014 Text Documents

Spire Global, Inc

2014-03-13ELS_146849

2014 LEMUR-1 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 COMPLIANT breakups: 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 ForeSight CubeSat market study is to evaluate the commercial viability of a low-Earth orbiting constellation of nanosatellites providing both a platform for high school STEM education and for generating high-revisit Earth observation data. As a part of this study, NanoSatisfi will be launching the LEMUR-1 satellite to perform technology demonstration of several spacecraft modules required for the constellation Project Milestones:  The development of LEMUR-1 began in Q3 2013, LEMUR-1 is currently undergoing subsystem integration in San Francisco.  LEMUR-1 will be delivered to the launch service provider in early April 2014, to be integrated in the launch vehicle in mid April 2014.  LEMUR-1 will be deployed from a P-POD as a secondary payload on the UniSat-6 mission, currently scheduled for no earlier than May 1 2014.  LEMUR-1 is part of an ongoing market study, which will conclude at the end of 2015. Foreign Government None Involvement Proposed Launch No earlier than May 1, 2014 Date: Proposed Launch Dnepr, UniSat-6 mission Vehicle: Proposed Launch Yasny Launch Base, Orenburg, Russia Site: Launch Vehicle International Space Company (ISC) Kosmotras Operator: Mission Duration: June 2014 – Dec 2015 Launch / Launch Deployment Profile: LEMUR-1 will be inserted directly into a circular sun-synchronous orbit at an altitude of 600km. Operations The operational phase of the satellite begins following the successful deployment of the satellite from the launch vehicle, at which point its solar panels and antennae deploy. The operational phase continues until the end of the market study in December 2015. .

Postmission Disposal Following the end of the operational phase, the orbit of the satellite will passively decay, 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, as detailed in Appendix B: LEMUR1 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 Interference with naturally decay 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 4kg Dry Mass at Launch 4kg 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 Range Safety / None Pyrotechnic Devices Electrical Generation Triple-junction GaAs solar panels Electrical Storage Rechargable lithium-ion 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 2600mAh Lithium-Ion cells, and represent the only credible failure mode during which stored energy is released. The main failure modes associated with Lithium Ion batteries result from overcharging, overdischarging, internal shorts, and external shorts. The battery pack onboard ArduSat-2 and the ArduSat-2X is in compliance with NASA’s Crewed Space Vehicle Battery Safety Requirements (JSC-20793), and 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 includ 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 can not 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. As detailed in Section 7, the satellites will completely disintegrate during reentry, with no components surviving reentry to the ground. 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 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 Aluminum 2 150 Box 56 x 80 x 20 Subsystem PCBs FR4 PCB 10 60 Flat 90 x 90 Plate Primary Structure Aluminum 1 560 Box 100 x 100 x 300 Optical Camera Aluminum, FR4 1 350 Cylinder 60 x 70 PCB, Glass Reaction wheel Aluminum, copper, 1 600 Box 100 x 100 assembly + enclosure FR4 PCB x 56 Battery pack Li-Ion, aluminum 1 470 Box 100 x 100 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 28 2014; 15:31:06PM DAS Application Started 01 28 2014; 15:31:07PM Opened Project C:\Program Files (x86)\NASA\DAS 2.0\ArduSat2\ 01 28 2014; 15:31:11PM Processing Requirement 4.3-1: Return Status : Not Run ===================== No Project Data Available ===================== =============== End of Requirement 4.3-1 =============== 01 28 2014; 15:31:13PM Processing Requirement 4.3-2: Return Status : Passed ===================== No Project Data Available ===================== =============== End of Requirement 4.3-2 =============== 01 28 2014; 15:31:14PM Requirement 4.4-3: Compliant =============== End of Requirement 4.4-3 =============== 01 28 2014; 15:31:18PM Processing Requirement 4.5-1: Return Status : Passed ============== Run Data ============== **INPUT** Space Structure Name = LEMUR1 Space Structure Type = Payload Perigee Altitude = 600.000000 (km) Apogee Altitude = 600.000000 (km) Inclination = 98.900000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass Ratio = 0.026310 (m^2/kg) Start Year = 2014.000000 (yr) Initial Mass = 4.000000 (kg) Final Mass = 4.000000 (kg) Duration = 10.000000 (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 = 0.000002 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range Status = Pass ============== =============== End of Requirement 4.5-1 =============== 01 28 2014; 15:31:23PM Requirement 4.5-2: Compliant 01 28 2014; 15:31:23PM Processing Requirement 4.6 Return Status : Passed ============== Project Data ============== **INPUT** Space Structure Name = LEMUR1 Space Structure Type = Payload Perigee Altitude = 600.000000 (km) Apogee Altitude = 600.000000 (km) Inclination = 98.900000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.026310 (m^2/kg) Start Year = 2014.000000 (yr) Initial Mass = 4.000000 (kg) Final Mass = 4.000000 (kg) Duration = 10.000000 (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 = 600.000000 (km) Suggested Apogee Altitude = 600.000000 (km) Returned Error Message = Reentry during mission (no PMD req.). Released Year = 2022 (yr) Requirement = 61 Compliance Status = Pass ============== =============== End of Requirement 4.6 =============== 01 28 2014; 15:31:29PM *********Processing Requirement 4.7-1 Return Status : Passed ***********INPUT**** Item Number = 1 name = LEMUR1 quantity = 1 parent = 0 materialID = 8 type = Box Aero Mass = 4.000000 Thermal Mass = 4.000000 Diameter/Width = 0.100000 Length = 0.300000 Height = 0.100000 name = STRUCTURE quantity = 1 parent = 1 materialID = 9 type = Box Aero Mass = 0.500000 Thermal Mass = 0.500000 Diameter/Width = 0.100000 Length = 0.300000 Height = 0.100000 name = PCBs quantity = 10 parent = 1 materialID = 23 type = Flat Plate Aero Mass = 0.060000 Thermal Mass = 0.060000 Diameter/Width = 0.100000 Length = 0.100000 name = ADCS quantity = 1

parent = 1 materialID = 8 type = Box Aero Mass = 0.600000 Thermal Mass = 0.600000 Diameter/Width = 0.100000 Length = 0.100000 Height = 0.050000 name = LENS quantity = 1 parent = 1 materialID = 8 type = Cylinder Aero Mass = 0.350000 Thermal Mass = 0.350000 Diameter/Width = 0.060000 Length = 0.070000 name = GPS_ANTENNA quantity = 2 parent = 1 materialID = 8 type = Box Aero Mass = 0.150000 Thermal Mass = 0.150000 Diameter/Width = 0.056000 Length = 0.080000 Height = 0.020000 name = BATTERY quantity = 1 parent = 1 materialID = 9 type = Box Aero Mass = 0.470000 Thermal Mass = 0.470000 Diameter/Width = 0.100000 Length = 0.100000 Height = 0.030000 name = SOLAR_PANELS_LONG quantity = 6 parent = 1 materialID = 24 type = Flat Plate Aero Mass = 0.150000 Thermal Mass = 0.150000 Diameter/Width = 0.100000 Length = 0.300000 name = SOLAR_PANELS_SHORT

quantity = 2 parent = 1 materialID = 24 type = Flat Plate Aero Mass = 0.060000 Thermal Mass = 0.060000 Diameter/Width = 0.100000 Length = 0.100000 **************OUTPUT**** Item Number = 1 name = LEMUR1 Demise Altitude = 77.998504 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = STRUCTURE Demise Altitude = 76.367371 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = PCBs Demise Altitude = 77.151676 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = ADCS Demise Altitude = 71.136496 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = LENS Demise Altitude = 71.200402 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = GPS_ANTENNA Demise Altitude = 74.411589 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = BATTERY Demise Altitude = 71.941042 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000

************************************* name = SOLAR_PANELS_LONG Demise Altitude = 77.621574 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = SOLAR_PANELS_SHORT Demise Altitude = 77.613543 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* =============== End of Requirement 4.7-1 ===============

Appendix B: LEMUR1 Orbit Lifetime Case Area Area/Mass (Mass=4Kg) 1a 0.0300 (30x10) 0.00750  CubeSat Z face nadir  Minimum surface area worst case drag 1b 0.0424 (30x14.1) 0.01061  CubeSat Z face nadir  Nominal drag configuration 2 0.0452 (0.01524+0.03) 0.01131  CubeSat Z face nadir  Worst case drag config  Antennas deployed (older configuration) 3 0.1052 (0.07524+0.03) 0.02631  CubeSat Z face nadir  Worst case drag config  Antennas deployed (older configuration)  Solar panels deployed (2 length wise panels) Case 1a:

Case 1b: Case 2:

Case 3:


Document Created: 2014-03-04 19:54:51
Document Modified: 2014-03-04 19:54:51
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