Orbital Debris Assessment Report

0312-EX-CN-2019 Text Documents

Near Space Launch, Inc.

2019-07-18ELS_234247

Orbital Debris Assessment Report GEARRS-3 per NASA-STD 8719.14A 1

Signature Page CTO, Near Space Launch, Inc. 1 f Z 7/17/19 Mike Miller Date Licensing Coordinator, Sterk Solutions Corporation %y/hfl 7/17/19 Michael H. Miller Date Licensing Analyst, Sterk Solutions Corporation

REFERENCES: A. NASA Procedural Requirements for Limiting Orbital Debris Generation, NPR 8715.6A, 5 February 2008 B. Process for Limiting Orbital Debris, NAS A-STD-8719.14A, 25 May 2012 C. International Space Station Reference Trajectory, delivered May 2017 D. McKissock , Barbara, Patricia Loyselle, and Elisa Vogel. Guidelines on Lithium- ion Battery Use in Space Applications. Tech. no. RP-08-75. NASA Glenn Research Center Cleveland, Ohio E. UL Standard for Safety.for Lithium Batteries, UL 1642. 1JL Standard. 4th ed. Northbrook, IL, Underwriters Laboratories, 2007 F. Kwas, Robert. Thermal Analysis of ELaNa-4 CubeSat Batteries, ELVL-2012- 0043254; Nov 2012 G. Range Safety User Requirements Manual Volume 3- Launch Vehicles, Payloads, and Ground Support Systems Requirements, AFSCM 91-710 V3. H. HQ OSMA Policy Memo/Email to 8719.14: CubeSat Battery Non-Passivation, Suzanne Aleman to Justin Treptow, 10, March 2014 I. HQ OSMA Emai1:6U CubcSat Ba_ttery Non Passivation Suzanne Aleman to Justin Treptow, 8 August 2017 This report is intended to satisfy the orbital debris requirements listed in NASA Procedural Requirements for Limiting Orbital Debris Generation, NPR 8715.6A, 5 February 2008, for the GEARRS-3 mission. 3

Sections 1 through 8 of Process for Limiting Orbital Debris, NAS A-STD-8719.14A, 25 May 2012, are addressed in this document; sections 9 through 14 are in the domain of the launch provider and are addressed by others. RECORD OF REVISIONS REV DESCRIPTION DATE 0 Original submission July 2019 The following table summarizes the compliance status of the spacecraft. They all are fully compliant with all applicable requirements. Requirements Compliance Assessment Comments 4.3-1a Not Applicable No planned debris release 4.3-1b Not Applicable No planned debris release 4.3-2 Not Applicable No planned debris release 4.4-1 Compliant Batteries incapable of debris producing failure 4.4-2 Compliant Batteries incapable of debris producing failure 4.4-3 Not Applicable No planned breakups 4.4-4 Not Applicable No planned breakups 4.5-1 Compliant 4.5-2 TBD Damage from small objects 4.6-1 through 4.6-4 Compliant Lifetime TBD 4.7-1 Compliant Non-credible risk of human casualty 4.8-1 Not Applicable No Tethers Table 1 Compliance Assessment per Requirement 4

Section 1: Mission Overview The overall goal of the GEARRS-3 mission, is to correlate Solar Activity to the Electron Density in the Near-Earth (LEO) Plasma Field. The spacecraft will carry an Energetic Particle Detector and a Langmuir Probe. Section 2: Spacecraft Description The spacecraft is a 3U cubesat unit with the dimensions of 10 cm X 10 cm X 30 cm The total mass is about 3.17 Kg. See Figure 1. Figure 1 GEARRS-3 3U Cubesat Hazards There are no pressure vessels, hazardous, or exotic materials. Batteries The spacecraft carries a total of 17 COTS Tenergy cells, UL 925050. The Tenergy Model 925050 pouch type cell, uses Polymer Lithium ion chemistry. It stores 2200 mAh at 3.7 volts. The UL listing number of the battery is SR925959 (30256-0). It is used with a battery circuit protection module providing over-charge/over-current protection and over-discharge protection circuitry. Tests have been conducted to demonstrate compliance with JSC EP-WI-032 “Statement of Work: Engineering Evaluation, Qualification and Flight Acceptance Tests for Lithium-ion Cells and Battery Packs for Small Satellite Systems.” 5

Section 3: Assessment of Spacecraft Debris Released during Normal Operations The assessment of spacecraft debris requires the identification of any object (>1 mm) expected to be released from the spacecraft any time after launch, including object dimensions, mass, and material. Section 3 requires rationale/necessity for release of each object, time of release of each object, relative to launch time, release velocity of each object with respect to spacecraft, expected orbital parameters (apogee, perigee, and inclination) of each object after release, calculated orbital lifetime of each object, including time spent in Low Earth Orbit (LEO), and an assessment of spacecraft compliance with Requirements 4.3-1 and 4.3-2. No releases are planned, therefore this section is not applicable. Section 4: Assessment of Spacecraft Intentional Breakups and Potential for Explosions There are NO plans for designed spacecraft breakups, explosions, or intentional collisions. The probability of battery explosion is very low, and, due to the very small mass of the satellite, and the short orbital lifetime, the effect of an explosion on the far term LEO environment is negligible. In addition due to the very small mass of the battery, and the foil pouch construction not supporting pressure buildup prior to breach, the effect of battery overpressure would not cause any release of debris from the satellite. The batteries meet Reg. 56450 (4.4-2), per this reference, by virtue of the HQ OSMA policy regarding battery disconnect stating "Cube Sats as a satellite class need not disconnect their batteries if flown in LEO with orbital lifetimes less than 25 years." Assessment of spacecraft compliance with Requirements 4.4-1 through 4.4-4 shows the satellite is compliant. 6

Section 5: Assessment of Spacecraft Potential for On Orbit Collisions 4.5-1 Probability of Collision with Large Debris Calculation of spacecraft probability of collision with space objects larger than 10 cm in diameter during the orbital lifetime of the spacecraft takes into account both the mean cross sectional area (MCSA) and orbital lifetime. See Appendix for DAS Analysis Input Data and Output Results. This shows that the probability of an on orbit collision with debris or meteoroids greater than 10 cm in diameter is “less than 0.00000”. This satisfies the 0.001 maximum probability requirement 4.5-l. Assessment of spacecraft compliance with Requirements 4.5-1 shows it to be compliant. 4.5-2 Probability of Damage from Small Objects Assessment of spacecraft compliance with Requirements 4.5-2 shows it to be compliant. 7

Section 6: Assessment of Spacecraft Postmission Disposal Plans and Procedures 4.6.1 Remove from LEO to Reduce Collision Threat The spacecraft will naturally decay from orbit within 25 years after end of the mission, satisfying requirement 4.6- l. No systems are required. Requirements 4.6-2, 4.6-3 and 4.6-4 therefore are not applicable. Summary of DAS 2.1.1 Orbital Lifetime Calculations: DAS inputs are: 550 km circular orbit, with an inclination of 90° at deployment no earlier than August 2019. The total mass of the spacecraft is 3.171 kg, and per DAS, the equivalent cross sectional area (minimum of all cases, for maximum lifetime) is 0.009 m2. From DAS, the lifetime for this maximum case will be 6.73 years. 8

Figure 3 Altitude vs. Time GEARRS-3 Spacecraft The assessment of the spacecraft illustrates it is compliant with Requirements 4.6-1 through 4.6-4 9

Section 7: Assessment of Spacecraft Reentry Hazards 4.7-1 Limit Number and Size of Debris Fragments Surviving Reentry A detailed assessment of the components of the spacecraft was performed using DAS 2.1.1, to verify Requirement 4.7-1. See Appendix for a complete log of DAS inputs and outputs. The analysis provides a bounding analysis for characterizing the survivability of a component during re-entry. It is conservative in that when it shows terminal energy of a component surviving reentry, it is does not consider any loss material from ablation or charring. Both of these may for some materials decrease the mass and dimensions of the re-entering components, reducing the risk below that calculated. All components TBD demise upon reentry and all spacecraft comply with the less than 1:10,000 probability of Human Casualty Requirement 4.7-1. The satellite thus is in compliance with Requirement 4.7-1 of NASA-STD-8719.14A. 10

Section 8: Assessment for Tether Missions 4.8-1 Collision Hazards of Space Tethers No tethers are used. Requirement 4.8-1 is satisfied. Section 9 through 14: ODAR sections 9 through 14 pertain to the launch vehicle, and are not covered here. 11

Appendix ***********INPUT**** Item Number = 1 name = GEARRS-3 quantity = 1 parent = 0 materialID = 8 type = Box Aero Mass = 3.171000 Thermal Mass = 3.171000 Diameter/Width = 0.100000 Length = 0.290000 Height = 0.100000 name = NSL 3U CubeSat Chassis quantity = 1 parent = 1 materialID = 8 type = Box Aero Mass = 1.210000 Thermal Mass = 1.210000 Diameter/Width = 0.100000 Length = 0.290000 Height = 0.100000 name = NSL 3x1 Deploy Solar Array quantity = 4 parent = 1 materialID = 23 type = Flat Plate Aero Mass = 0.104000 Thermal Mass = 0.104000 Diameter/Width = 0.083000 Length = 0.290000 name = NSL Duplex Antenna quantity = 2 parent = 1 materialID = 40 type = Box Aero Mass = 0.069000 Thermal Mass = 0.069000 Diameter/Width = 0.050000 Length = 0.050000 Height = 0.012500 name = NSL Simplex Antenna quantity = 2 parent = 1 materialID = 40 type = Box Aero Mass = 0.015000 Thermal Mass = 0.015000 Diameter/Width = 0.035000 Length = 0.035000 Height = 0.005000 name = NSL RBF Switch Assembly quantity = 1 parent = 1 materialID = 8 type = Box Aero Mass = 0.005000 12

Thermal Mass = 0.005000 Diameter/Width = 0.010000 Length = 0.040000 Height = 0.005000 name = Rail Switches quantity = 4 parent = 1 materialID = 27 type = Box Aero Mass = 0.002000 Thermal Mass = 0.002000 Diameter/Width = 0.010000 Length = 0.020000 Height = 0.007000 name = NSL BlackBOX Patch Antenna quantity = 2 parent = 1 materialID = 40 type = Box Aero Mass = 0.007000 Thermal Mass = 0.007000 Diameter/Width = 0.025000 Length = 0.025000 Height = 0.004500 name = NSL BlackBOX Patch PCB quantity = 1 parent = 1 materialID = 23 type = Box Aero Mass = 0.031000 Thermal Mass = 0.031000 Diameter/Width = 0.080000 Length = 0.100000 Height = 0.002500 name = NSL Lipo Battery UL 925050 Single quantity = 1 parent = 1 materialID = 5 type = Box Aero Mass = 0.044000 Thermal Mass = 0.044000 Diameter/Width = 0.050000 Length = 0.055000 Height = 0.007000 name = NSL BlackBOX Patch Frame quantity = 1 parent = 1 materialID = 5 type = Box Aero Mass = 0.008000 Thermal Mass = 0.008000 Diameter/Width = 0.082000 Length = 0.100000 Height = 0.005000 name = NSL EPS / COMM quantity = 1 parent = 1 materialID = 23 type = Box Aero Mass = 0.130000 13

Thermal Mass = 0.130000 Diameter/Width = 0.087000 Length = 0.090000 Height = 0.014000 name = NSL Dual Lipo Battery Pack UL 925050 Tenergy quantity = 8 parent = 1 materialID = 5 type = Box Aero Mass = 0.083000 Thermal Mass = 0.083000 Diameter/Width = 0.050000 Length = 0.055000 Height = 0.017000 name = Cabling quantity = 1 parent = 1 materialID = 52 type = Cylinder Aero Mass = 0.100000 Thermal Mass = 0.100000 Diameter/Width = 0.003500 Length = 1.000000 name = Fasteners quantity = 20 parent = 1 materialID = 54 type = Box Aero Mass = 0.003250 Thermal Mass = 0.003250 Diameter/Width = 0.007000 Length = 0.012500 Height = 0.007000 name = NSL D2F Duplex Module quantity = 1 parent = 1 materialID = 23 type = Flat Plate Aero Mass = 0.060000 Thermal Mass = 0.060000 Diameter/Width = 0.060000 Length = 0.118000 name = NSL S2F Backup Simplex quantity = 2 parent = 1 materialID = 23 type = Box Aero Mass = 0.056000 Thermal Mass = 0.056000 Diameter/Width = 0.045000 Length = 0.082000 Height = 0.014000 name = NSL ADACS Coil quantity = 3 parent = 1 materialID = 19 type = Cylinder Aero Mass = 0.030000 Thermal Mass = 0.030000 Diameter/Width = 0.008000 14

Length = 0.068000 name = NSL ADACS Module quantity = 1 parent = 1 materialID = 23 type = Flat Plate Aero Mass = 0.010000 Thermal Mass = 0.010000 Diameter/Width = 0.042000 Length = 0.070000 name = NSL Peak Power Tracker quantity = 2 parent = 1 materialID = 23 type = Box Aero Mass = 0.009000 Thermal Mass = 0.009000 Diameter/Width = 0.020000 Length = 0.050000 Height = 0.005000 name = NSL Entergetic Partical Detector quantity = 3 parent = 1 materialID = 23 type = Box Aero Mass = 0.005000 Thermal Mass = 0.005000 Diameter/Width = 0.016000 Length = 0.028000 Height = 0.007000 name = NSL Particle Detector quantity = 1 parent = 1 materialID = 23 type = Box Aero Mass = 0.003000 Thermal Mass = 0.003000 Diameter/Width = 0.015000 Length = 0.032000 Height = 0.005000 **************OUTPUT**** Item Number = 1 name = GEARRS-3 Demise Altitude = 77.995102 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = NSL 3U CubeSat Chassis Demise Altitude = 73.424583 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = NSL 3x1 Deploy Solar Array Demise Altitude = 77.267998 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = NSL Duplex Antenna Demise Altitude = 74.166084 Debris Casualty Area = 0.000000 15

Impact Kinetic Energy = 0.000000 ************************************* name = NSL Simplex Antenna Demise Altitude = 76.266502 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = NSL RBF Switch Assembly Demise Altitude = 77.032921 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Rail Switches Demise Altitude = 77.851143 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = NSL BlackBOX Patch Antenna Demise Altitude = 76.628052 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = NSL BlackBOX Patch PCB Demise Altitude = 77.476860 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = NSL Lipo Battery UL 925050 Single Demise Altitude = 75.569756 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = NSL BlackBOX Patch Frame Demise Altitude = 77.802185 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = NSL EPS / COMM Demise Altitude = 76.056259 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = NSL Dual Lipo Battery Pack UL 925050 Tenergy Demise Altitude = 74.347290 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Cabling Demise Altitude = 77.493858 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Fasteners Demise Altitude = 74.922081 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = NSL D2F Duplex Module Demise Altitude = 76.927498 Debris Casualty Area = 0.000000 16

Impact Kinetic Energy = 0.000000 ************************************* name = NSL S2F Backup Simplex Demise Altitude = 76.756859 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = NSL ADACS Coil Demise Altitude = 75.614265 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = NSL ADACS Module Demise Altitude = 77.625793 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = NSL Peak Power Tracker Demise Altitude = 77.355095 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = NSL Entergetic Partical Detector Demise Altitude = 77.383278 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = NSL Particle Detector Demise Altitude = 77.616867 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* **INPUT** Space Structure Name = GEARRS-3 Space Structure Type = Payload Perigee Altitude = 550.000000 (km) Apogee Altitude = 550.000000 (km) Inclination = 90.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass Ratio = 0.009000 (m^2/kg) Start Year = 2019.000000 (yr) Initial Mass = 3.171000 (kg) Final Mass = 3.171000 (kg) Duration = 2.000000 (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** 17

Collision Probability = 0.000000 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range Status = Pass ============== =============== End of Requirement 4.5-1 =============== 07 16 2019; 15:52:50PM Requirement 4.5-2: Compliant 07 16 2019; 15:52:54PM Processing Requirement 4.6 Return Status : Passed 22 18


Document Created: 2019-07-18 15:36:13
Document Modified: 2019-07-18 15:36:13
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