Orbital Debris Assessment Report

0317-EX-ST-2019 Text Documents

Stara Corporation

2019-05-01ELS_228907

Orbital Debris Assessment Report NOOR-1 per NASA-STD 8719.14A Page 1 of 24

04/22/19 Page 2 of 24

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 NOOR-1 mission. Page 3 of 24

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 April 2019 The following table summarizes the compliance status of the NOOR-1A and NOOR-1B spacecraft. They 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 Table 1 Compliance Assessment per Requirement Page 4 of 24

Section 1: Mission Overview The overall goal of the NOOR-1 mission, is to test, develop, and demonstrate the efficacy and design of a nano-satellite network, including associated software applications and their ability to exchange encrypted data via crosslinks, relay store-and-forward requests, and reliably communicate with Stara’s ground station. Section 2: Spacecraft Description The two spacecraft are identical, using an Alba Orbital 3p PocketQube platform. Each has the dimensions 8 x 6.9 x 19 cm stowed, and 44 x 7 x 18.5 cm with the solar panels deployed. The total mass of each is about 0.75 Kg. Figure 1: A Noor-1 Unit, Dimension Drawing: Solar Panels Deployed Dimensions in mm Page 5 of 24

Figure 2: A Noor-1 Unit, Dimension Drawing: Solar Panels Stowed Dimensions in mm Figure 3: A Noor-1 Unit, Perspective Drawing: Solar Panels and Patch Antenna Deployed Hazards There are no pressure vessels, hazardous, or exotic materials. Page 6 of 24

Batteries There are 2 batteries per spacecraft. The batteries are Lithium Polymer batteries manufactured from RS- components under RS stock number 125-1266. Their characteristics are: 2000 mAh, 3.7 V, Catalog Number- SR674361P Battery circuit protection module: This battery has a fuel gauge module which is used for monitoring the state of charge of the battery via the fuel gauge IC (DS2756E+T&R). This IC monitors voltage, temperature, currents and current accumulation and alerts the on-board computer when accumulated current or temperature exceeds programmable limits. No other protection module is present. This battery complies with the specifications published by RS Components. Electrostatic discharge sensitive devices have been handled and packed under conditions that meet the administrative and technical requirements of the ANSI/ESD S20.20:2014 and BS EN 61340-5-1:2007 Electrostatic Control Standards. Additionally, according to the “ST/SG/AC.10/11/Rev.6/ 2015, UN Model Regulations Part 3 - 38.3 Lithium Batteries” standard, provided by the manufacturer, these batteries have passed Vibe, Shock and Thermal Ambient testing. The batteries have been subjected to a qualification and acceptance test as suggested by the NASA standard JSC- 20793D (https://standards.nasa.gov/standard/jsc/jsc-20793). The batteries were: - Subjected to functional baseline tests (capacity & load check, mass, visual inspection) - Vibed and shocked - Subjected to another functional baseline test - Subjected to multiple charge and discharge cycles before thermal vacuum exposure - Exposed to a thermal vacuum under extreme temperature conditions - Subjected to functional baseline tests and a visual inspection to ensure no expansion of the batteries occurred. The EPS is a direct energy transfer system, using a solar array producing approximately 19W of orbit average power to charge the battery system. The solar arrays utilize standard AzurSpace photovoltaic cells. Page 7 of 24

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 the effect of an explosion on the far-term LEO environment is negligible, per HQ OSMA Policy Memo/Email to 8719.14: CubeSat Battery Non-Passivation, Suzanne Aleman to Justin Treptow, 10, March 2014 The batteries meet Reg. 56450 (4.4-2), per this reference, by virtue of the HQ OSMA policy regarding battery disconnect stating "CubeSats [3U or smaller] 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 that the satellite pair is compliant. Page 8 of 24

Section 5: Assessment of Spacecraft Potential for On Orbit Collisions 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 was calculated for both fully deployed and fully stowed configurations. This satisfies the 0.001 maximum probability requirement 4.5-l. The spacecraft have no capability nor have plans for end-of- mission disposal, therefore requirement 4.5-2 is not applicable. Assessment of spacecraft compliance with Requirements 4.5-1 shows it to be compliant. Requirement 4.5-2 is not applicable to this mission. Page 9 of 24

Section 6: Assessment of Spacecraft Postmission Disposal Plans and Procedures The spacecraft all will naturally decay from orbit within 25 years after end of the mission, satisfying requirement 4.6- l. Planning for spacecraft maneuvers to accomplish post-mission disposal is not applicable. Disposal is achieved via passive atmospheric reentry. Summary of DAS 2.1.1 Orbital Lifetime Calculations: DAS inputs are: 385 km circular orbit, with an inclination of 98° at deployment no earlier than June 15, 2019. From the DAS output data and the following figure from DAS, in the nominal operation case, the lifetime of the spacecraft is estimated to be approximately six months until demise. Figure 4 Altitude vs. Time For Noor-1 Spacecraft. Deployed Similarly, in the case of non-deployment, the orbit lifetime is shown to be 1.1 years, in Figure 5. Page 10 of 24

Figure 5 Altitude vs. Time For Noor-1 Spacecraft. Stowed Configuration The assessment of the spacecraft illustrates it is compliant with Requirements 4.6-1 through 4.6-5. Page 11 of 24

Section 7: Assessment of Spacecraft Reentry Hazards 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 demise upon reentry and all spacecraft comply with the less than 1:10,000 probability of Human Casualty Requirement 4.7-1. The satellites thus are in compliance with Requirement 4.7-1 of NASA-STD-8719.14A. Page 12 of 24

Section 8: Assessment for Tether Missions 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. Page 13 of 24

Appendix 04 11 2019; 13:39:40PM Activity Log Started 04 11 2019; 13:42:30PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2019.000000 (yr) Perigee Altitude = 385.000000 (km) Apogee Altitude = 385.000000 (km) Inclination = 98.000000 (deg) RAAN = 270.000000 (deg) Argument of Perigee = 80.000000 (deg) Area-To-Mass Ratio = 0.039816 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 0.553046 (yr) Time Spent in LEO during Lifetime = 0.553046 (yr) Last year of Propagation = 2019 (yr) Returned Error Message: Object reentered 04 11 2019; 13:46:04PM Science and Engineering - Apogee/Perigee History for a Given Orbit **INPUT** Perigee Altitude = 385.000000 (km) Apogee Altitude = 385.000000 (km) Inclination = 98.000000 (deg) RAAN = 270.000000 (deg) Argument of Perigee = 80.000000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.039816 (m^2/kg) Start Year = 2019.600000 (yr) Integration Time = 1.000000 (yr) **OUTPUT** Plot 04 11 2019; 13:48:02PM Science and Engineering - Apogee/Perigee History for a Given Orbit **INPUT** Start Year = 2019.000000 (yr) Perigee Altitude = 385.000000 (km) Apogee Altitude = 385.000000 (km) Inclination = 98.000000 (deg) RAAN = 270.000000 (deg) Argument of Perigee = 80.000000 (deg) Area-To-Mass Ratio = 0.020995 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 1.100616 (yr) Time Spent in LEO during Lifetime = 1.100616 (yr) Page 14 of 24

Last year of Propagation = 2020 (yr) Returned Error Message: Object reentered 04 11 2019; 13:48:49PM Science and Engineering - Apogee/Perigee History for a Given Orbit **INPUT** Perigee Altitude = 385.000000 (km) Apogee Altitude = 385.000000 (km) Inclination = 98.000000 (deg) RAAN = 270.000000 (deg) Argument of Perigee = 80.000000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.020995 (m^2/kg) Start Year = 2019.600000 (yr) Integration Time = 1.000000 (yr) **OUTPUT** Plot 04 11 2019; 13:50:22PM Activity Log Started 04 11 2019; 13:51:10PM *********Processing Requirement 4.7-1 Return Status : Passed ***********INPUT**** Item Number = 1 name = NOOR-1 quantity = 1 parent = 0 materialID = 5 type = Box Aero Mass = 0.754370 Thermal Mass = 0.754370 Diameter/Width = 0.080000 Length = 0.190000 Height = 0.069000 name = Solar panel board module quantity = 8 parent = 1 materialID = 19 type = Flat Plate Aero Mass = 0.015730 Thermal Mass = 0.015730 Diameter/Width = 0.045000 Length = 0.185000 name = Solar cell quantity = 16 parent = 1 materialID = 24 type = Flat Plate Aero Mass = 0.002600 Thermal Mass = 0.002600 Page 15 of 24

Diameter/Width = 0.040000 Length = 0.080000 name = Back plane quantity = 1 parent = 1 materialID = 19 type = Flat Plate Aero Mass = 0.057860 Thermal Mass = 0.057860 Diameter/Width = 0.058000 Length = 0.191000 name = Main structure frame quantity = 1 parent = 1 materialID = 8 type = Box Aero Mass = 0.050970 Thermal Mass = 0.050970 Diameter/Width = 0.050000 Length = 0.178000 Height = 0.050000 name = End plate 1 quantity = 1 parent = 1 materialID = 8 type = Flat Plate Aero Mass = 0.002440 Thermal Mass = 0.002440 Diameter/Width = 0.047000 Length = 0.047000 name = End plate 2 quantity = 1 parent = 1 materialID = 8 type = Flat Plate Aero Mass = 0.004960 Thermal Mass = 0.004960 Diameter/Width = 0.047000 Length = 0.047000 name = Lithium ion batteries quantity = 2 parent = 1 materialID = 5 type = Box Aero Mass = 0.040000 Thermal Mass = 0.040000 Diameter/Width = 0.050000 Length = 0.054300 Height = 0.006100 name = Radio mounting bracket Page 16 of 24

quantity = 1 parent = 1 materialID = 8 type = Flat Plate Aero Mass = 0.007110 Thermal Mass = 0.007110 Diameter/Width = 0.047000 Length = 0.054000 name = Radio assembly rods quantity = 4 parent = 1 materialID = 54 type = Cylinder Aero Mass = 0.002000 Thermal Mass = 0.002000 Diameter/Width = 0.002500 Length = 0.080000 name = Patch mounting panel quantity = 1 parent = 1 materialID = 76 type = Box Aero Mass = 0.013150 Thermal Mass = 0.013150 Diameter/Width = 0.050000 Length = 0.056000 Height = 0.007000 name = Top shield quantity = 3 parent = 1 materialID = 8 type = Box Aero Mass = 0.011000 Thermal Mass = 0.011000 Diameter/Width = 0.042000 Length = 0.042000 Height = 0.005000 name = Bottom shield quantity = 3 parent = 1 materialID = 8 type = Box Aero Mass = 0.007000 Thermal Mass = 0.007000 Diameter/Width = 0.042000 Length = 0.042000 Height = 0.005000 name = Ipex Cable quantity = 3 parent = 1 materialID = 64 Page 17 of 24

type = Cylinder Aero Mass = 0.001620 Thermal Mass = 0.001620 Diameter/Width = 0.002500 Length = 0.180000 name = ISL S-band radio board quantity = 1 parent = 1 materialID = 23 type = Box Aero Mass = 0.010430 Thermal Mass = 0.010430 Diameter/Width = 0.042000 Length = 0.042000 Height = 0.016000 name = DL S-band radio board quantity = 1 parent = 1 materialID = 23 type = Box Aero Mass = 0.010430 Thermal Mass = 0.010430 Diameter/Width = 0.042000 Length = 0.042000 Height = 0.016000 name = UHF radio board quantity = 1 parent = 1 materialID = 23 type = Box Aero Mass = 0.010430 Thermal Mass = 0.010430 Diameter/Width = 0.042000 Length = 0.042000 Height = 0.016000 name = DL S-band patch antenna quantity = 1 parent = 1 materialID = 19 type = Flat Plate Aero Mass = 0.008400 Thermal Mass = 0.008400 Diameter/Width = 0.050000 Length = 0.050000 name = ISL S-band omni antenna quantity = 1 parent = 1 materialID = 19 type = Flat Plate Aero Mass = 0.004500 Thermal Mass = 0.004500 Page 18 of 24

Diameter/Width = 0.012000 Length = 0.100000 name = UHF omni antenna quantity = 1 parent = 1 materialID = 19 type = Flat Plate Aero Mass = 0.009300 Thermal Mass = 0.009300 Diameter/Width = 0.023000 Length = 0.162000 name = ADCS Main Support Frame quantity = 1 parent = 1 materialID = 5 type = Box Aero Mass = 0.018340 Thermal Mass = 0.018340 Diameter/Width = 0.046000 Length = 0.047000 Height = 0.040500 name = ADCS Inertia Wheels quantity = 3 parent = 1 materialID = 14 type = Cylinder Aero Mass = 0.011610 Thermal Mass = 0.011610 Diameter/Width = 0.007500 Length = 0.035000 name = ADCS BLDC Motor quantity = 3 parent = 1 materialID = 19 type = Cylinder Aero Mass = 0.006900 Thermal Mass = 0.006900 Diameter/Width = 0.019000 Length = 0.008800 name = ADCS Core+wire (40mm 'torquer) quantity = 2 parent = 1 materialID = 19 type = Cylinder Aero Mass = 0.052000 Thermal Mass = 0.052000 Diameter/Width = 0.014000 Length = 0.040000 name = ADCS Core+wire (50mm 'torquer) quantity = 1 Page 19 of 24

parent = 1 materialID = 19 type = Cylinder Aero Mass = 0.066000 Thermal Mass = 0.066000 Diameter/Width = 0.014000 Length = 0.050000 name = ADCS Core Ends quantity = 6 parent = 1 materialID = 14 type = Cylinder Aero Mass = 0.001000 Thermal Mass = 0.001000 Diameter/Width = 0.004000 Length = 0.011600 name = ADCS Support Frame (40mm 'torquer) quantity = 2 parent = 1 materialID = 23 type = Flat Plate Aero Mass = 0.001100 Thermal Mass = 0.001100 Diameter/Width = 0.017000 Length = 0.040000 name = ADCS Support Frame (50mm 'torquer) quantity = 1 parent = 1 materialID = 23 type = Flat Plate Aero Mass = 0.001100 Thermal Mass = 0.001100 Diameter/Width = 0.017000 Length = 0.050000 name = Sun Sensor Cap quantity = 2 parent = 1 materialID = 8 type = Cylinder Aero Mass = 0.001000 Thermal Mass = 0.001000 Diameter/Width = 0.006000 Length = 0.016000 name = Sun Sensor Board quantity = 2 parent = 1 materialID = 23 type = Flat Plate Aero Mass = 0.003800 Thermal Mass = 0.003800 Diameter/Width = 0.033000 Page 20 of 24

Length = 0.033000 **************OUTPUT**** Item Number = 1 name = NOOR-1 Demise Altitude = 77.992844 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Solar panel board module Demise Altitude = 77.515686 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Solar cell Demise Altitude = 77.936600 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Back plane Demise Altitude = 76.632027 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Main structure frame Demise Altitude = 77.232742 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = End plate 1 Demise Altitude = 77.719124 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = End plate 2 Demise Altitude = 77.448997 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Lithium ion batteries Demise Altitude = 74.671814 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Radio mounting bracket Demise Altitude = 77.298744 Debris Casualty Area = 0.000000 Page 21 of 24

Impact Kinetic Energy = 0.000000 ************************************* name = Radio assembly rods Demise Altitude = 76.776337 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Patch mounting panel Demise Altitude = 77.803795 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Top shield Demise Altitude = 76.729721 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Bottom shield Demise Altitude = 77.175598 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Ipex Cable Demise Altitude = 77.907967 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = ISL S-band radio board Demise Altitude = 77.345848 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = DL S-band radio board Demise Altitude = 77.345848 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = UHF radio board Demise Altitude = 77.345848 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = DL S-band patch antenna Demise Altitude = 77.321091 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 Page 22 of 24

************************************* name = ISL S-band omni antenna Demise Altitude = 77.426155 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = UHF omni antenna Demise Altitude = 77.504059 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = ADCS Main Support Frame Demise Altitude = 76.953499 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = ADCS Inertia Wheels Demise Altitude = 75.817863 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = ADCS BLDC Motor Demise Altitude = 76.158958 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = ADCS Core+wire (40mm 'torquer) Demise Altitude = 72.019272 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = ADCS Core+wire (50mm 'torquer) Demise Altitude = 71.773895 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = ADCS Core Ends Demise Altitude = 77.151649 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = ADCS Support Frame (40mm 'torquer) Demise Altitude = 77.789116 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = ADCS Support Frame (50mm 'torquer) Page 23 of 24

Demise Altitude = 77.826462 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Sun Sensor Cap Demise Altitude = 77.239166 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Sun Sensor Board Demise Altitude = 77.469467 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* =============== End of Requirement 4.7-1 =============== Page 24 of 24


Document Created: 2019-04-23 13:02:11
Document Modified: 2019-04-23 13:02:11
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