Orbital Debris Assessment

0376-EX-CN-2019 Text Documents

St. Louis University

2019-05-03ELS_229069

ELVL—2019—0045507 Rev A April 24, 2019 Orbital Debris Assessment for the Argus—02 CubeSat per NASA—STD 8719.14A

Signature Page Johyson, Anal{rst} a.1. solutions, AIS2 Scott Higginbotham, Misgffh Manager, NASA KSC VA—C

National Aeronautics and Space Administration John F. Kennedy Space Center, Florida Kennedy Space Center, FL 32899 ELVL—2019—0045507 Rev A Reply to Attnof VA—H1 Apl'll 24, 2019 TO: Scott Higginbotham, LSP Mission Manager, NASA/KSC/VA—C FROM: Yusef Johnson, a.i. solutions/KSC/AIS2 SUBJECT: Orbital Debris Assessment Report (ODAR) for the Argus—02 CubeSat REFERENCES: A. NASA Procedural Requirements for Limiting Orbital Debris Generation, NPR 8$715.6B, 16 February 2017 B. Process for Limiting Orbital Debris, NASA—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 Standardfor Safetyfor Lithium Batteries, UL 1642. UL Standard. 4th ed. Northbrook, IL, Underwriters Laboratories, 2007 Kwas, Robert. Thermal Analysis of ELaNa—4 CubeSat Batteries, ELVL—2012— es 0043254; Nov 2012 Range Safety User Requirements Manual Volume 3— Launch Vehicles, O Payloads, and Ground Support Systems Requirements, AFSCM 91—710 V3. HQ OSMA Policy Memo/Email to 8719.14: CubeSat Battery Non—Passivation, iA Suzanne Aleman to Justin Treptow, 10, March 2014 HQ OSMA Email:6U CubeSat Battery Non Passivation Suzanne Aleman to m ? Justin Treptow, 8 August 2017 The intent of this report is to satisfy the orbital debris requirements listed in ref. (a) for the Argus—02 CubeSat, which will be deployed from the International Space Station. It serves as the final submittal in support of the spacecraft Safety and Mission Success Review (SMSR). Sections 1 through 8 of ref. (b) are addressed in this document; sections 9 through 14 fall under the requirements levied on the primary mission and are not presented here. The CubeSat will passively reenter and therefore this ODAR will also serve as the EOMP (End of Mission Plan)

RECORD OF REVISIONS REV DESCRIPTION DATE 0 Original submission January 2019 A Incorporated official name change from ‘Argus‘ to April 2019 ‘Argus—02°, updated CubeSat mass properties and materials list

The following table summarizes the compliance status of the Argus—02 CubeSat to be deployed from the International Space Station. Argus—02 is fully compliant with all applicable requirements. Table 1: Orbital Debris Requirement Com liance Matrix Requirement Compliance Assessment Comments 4.3—l1a 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 On board energy source (batteries) incapable of debris—producing failure 4.4—2 Compliant On board energy source (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 Not applicable 4.6—1(a) Compliant Worst case lifetime 1.6 yrs 4.6—1(b) Not applicable 4.6—1(c) Not applicable 4.6—2 Not applicable 4.6—3 Not applicable 4.6—4 Not applicable Passive disposal 4.6—5 Compliant 4.7—1 Compliant Non—credible risk of human casualty 4.8—1 Compliant No planned tether release for Argus—02

Section 1: Program Management and Mission Overview Argus—02 is sponsored by the Human Exploration and Operations Mission Directorate at NASA Headquarters. The Program Executive is John Guidi. Responsible program/project manager and senior scientific and management personnel are as follows: Argus—02: Dr. Michael Swartwout, Principal Investigator, St. Louis University

Program Milestone Schedule Task Date CubeSat Selection November 154, 2018 Delivery to NanoRacks August 154 , 2019 Launch October 192019 Figure 1: Program Milestone Schedule Argus—02 will be launched as a payload on the Antares launch vehicle executing the NG— 12 mission. Argus—02 will be deployed from the International Space Station. Each CubeSat is identified in Table 2: Attributes. Argus—02 weighs approximately 1.3 kg.

Section 2: Spacecraft Description Table2: outline the generic attributes of the spacecraft. Table 2: Argus—02 Attributes CubeSat CubeSat CubeSat Names & CubeSat size (mm) Masses Quantity (ke) Argus—02 1 100 x 100 x 113.5 1.3 The following pages describe the Argus—02 CubeSat.

Argus—02 — St. Louis University — 1U Figure 2: Argus—02 exploded view Overview Argus—02 is a reflight of the original Argus mission lost on ELaNa 7. It continues the original Argus mission of characterizing the performance of modern electronics in the space environment, and has been augmented with an artificial intelligence demonstration (on board event detection using neural nets). The reasoning software use imagery from two onboard visible—light cameras to observe and predict local events; together with ground operators, the flight software will also observe the effects of radiation on memory storage. CONOPS Argus—02 will be deployed from a NanoRacks deployer and will activate after 30 minutes. Upon booting it will deploy its antenna, and hold in safe mode until batteries are charged to the point to begin beacon operations. Once ground communication is established, Argus—02 will begin transmitting health data and basic telemetry as requested. Experimentation will begin once nominal spacecraft health is established. Materials The spacecraft structure is made of aluminum 6061 which has a class III type 2 hard anodization. The side panels and the payload bay are constructed out of Nylon 12 and ABS 3D printing material. The EPS, transceiver, and antenna have an anodized aluminum shell. The antenna is constructed from shape memory alloy (SMA), and the PCBs are all FR—4. Nearly all electronic components are commercial—off—the—shelf (COTS), and the primary structure is also COTS.

Hazards There are no pressure vessels, hazardous, or exotic materials. Batteries The spacecraft batteries, which will store charge from solar panels, are lithium polymer cells which are in accordance with UL1642 and RoHS—compliant. There is also a lithium coin cell to power the real—time clock. 10

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. The 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 for Argus—02, therefore this section is not applicable. 11

Section 4: Assessment of Spacecraft Intentional Breakups and Potential for Explosions. There are NO plans for designed spacecraft breakups, explosions, or intentional collisions on the Argus—02 mission. The probability ofbattery explosion is very low, and, due to the very small mass of the satellites and their short orbital lifetimes the effect of an explosion on the far—term LEO environment is negligible (ref (h)). The CubeSat batteries still meet Req. 56450 (4.4—2) by virtue of the HQ OSMA policy regarding CubeSat battery disconnect stating; "CubeSats as a satellite class need not disconnect their batteries if flown in LEO with orbital lifetimes less than 25 years." (ref. (h)) Limitations in space and mass prevent the inclusion of the necessary resources to disconnect the battery or the solar arrays at EOM. However, the low charges and small battery cells on the CubeSat‘s power system prevents a catastrophic failure, so that passivation at EOM is not necessary to prevent an explosion or deflagration large enough to release orbital debris. Assessment of spacecraft compliance with Requirements 4.4—1 through 4.4—4 shows that with a maximum CubeSat lifetime of 1.6 years maximum, Argus—02 is compliant. 12

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 and orbital lifetime. Figure 4: Argus—02 Expanded View (with solar panels deployed) x (w + A)] Mean CSA = ZS“ff‘:ce Area _ [2+(w +1 :4 Equation 1: Mean Cross Sectional Area for Convex Objects A +Aq + A Mean CSA = E—"fiTl-—l) Equation 2: Mean Cross Sectional Area for Complex Objects The CubeSat evaluated for this ODAR are stowed in a convex configuration, indicating there are no elements of the CubeSat obscuring another element of the same CubeSat from view. Thus, the mean CSA for the stowed CubeSat was calculated using Equation 1. The Argus—02 (1.3 kg) orbit at deployment will be 423 x 407 km at a 51.6° inclination. With an area to mass ratio of ~.0122 m*/kg, DAS yields ~1.6 years for orbit lifetime, which in turn is used to obtain the collision probability. Argus—02 is calculated to have a probability of collision of 0.0. Table 3 below provides complete results. There will be no post—mission disposal operation. As such the identification of all systems and components required to accomplish post—mission disposal operation, including passivation and maneuvering, is not applicable. 13

CubeSat Argus—02 Mass (kg) 1.3 Mean C/S Area (m42) 0.01568 § Area—to Mass {m"2/kg) 0.0122 § Orbital Lifetime (yrs) 1.6 Probability of collision (10"X) 0.0000 Solar Flux Table Dated 12/18/2018 Table 3: CubeSat Orbital Lifetime & Collision Probability 14

The probability of Argus—02 colliding with debris and meteoroids greater than 10 cm in diameter and capable of preventing post—mission disposal is less than 0.00000, for any configuration. This satisfies the 0.001 maximum probability requirement 4.5—1. Assessment of spacecraft compliance with Requirements 4.5—1 shows Argus—02 to be compliant. Argus—02 has no capability or plans for end—of—mission disposal, therefore Requirement 4.5—2 is not applicable. Argus—02 will passively reenter and therefore this ODAR also serves as the EOMP (End of Mission Plan) Section 6: Assessment of Spacecraft Postmission Disposal Plans and Procedures Argus—02 will naturally decay from orbit within 25 years after end of the mission, satisfying requirement 4.6—1a detailing the spacecraft disposal option. Planning for spacecraft maneuvers to accomplish post—mission disposal is not applicable. Disposal is achieved via passive atmospheric reentry. In order to determine the area—to—mass ratio for the Argus—02 CubeSat, the area—to—mass is calculated as follows: Mean ©/‘g Area (m") 4 M m W = Area — to — Mass (E) Equation 3: Area to Mass 0.01568 m m* _—o———————= 0122 —— 1.3 kg kg The assessment of the spacecraft illustrates they are compliant with Requirements 4.6—1 through 4.6—5. DAS 2.1.1 Orbital Lifetime Calculations: DAS inputs are: 423.5 km maximum apogee 407.8 km maximum perigee altitudes with an inclination of 51.6° at deployment no earlier than October 2019. An area to mass ratio of ~0.0122 m*/kg for the Argus—02 CubeSat was used. DAS 2.1.1 yields a 1.6 years orbit lifetime for Argus—02. This meets requirement 4.6—1. For the complete list of CubeSat orbital lifetimes reference Table 3: CubeSat Orbital Lifetime & Collision Probability. Assessment results show compliance. 15

Section 7: Assessment of Spacecraft Reentry Hazards A detailed assessment of the components of Argus—02 was performed. The assessment used DAS 2.1.1, a conservative tool used by the NASA Orbital Debris Office to verify Requirement 4.7—1. The analysis is intended to provide a bounding analysis for characterizing the survivability of a CubeSat‘s component during re—entry. For example, when DAS shows a component surviving reentry it is not taking into account the material ablating away or charring due to oxidative heating. Both physical effects are experienced upon reentry and will decrease the mass and size of the real—life components as the reenter the atmosphere, reducing the risk they pose still further. The following steps are used to identify and evaluate a components potential reentry risk relative to the 4.7—1 requirement of having less than 15 J of kinetic energy and a 1:10,000 probability of a human casualty in the event the survive reentry. 1. Low melting temperature (less than 1000 °C) components are identified as materials that would never survive reentry and pose no risk to human casualty. This is confirmed through DAS analysis that showed materials with melting temperatures equal to or below that of copper (1080 °C) will always demise upon reentry for any size component up to the dimensions of a 1U CubeSat. 2. The remaining high temperature materials are shown to pose negligible risk to human casualty through a bounding DAS analysis of the highest temperature components, stainless steel (1500°C). If a component is of similar dimensions and has a melting temperature between 1000 °C and 1500°C, it can be expected to possess the same negligible risk as stainless steel components. Table 4: Argus—02 High Melting Temperature Material Analysis Hysteresis Rods HyMu8O 00663 77 4 0 Pa%’::g::::gx:'s Stainless Steel .00413 77.4 Watc:::fh;f;:aded ©Stainless Steel 0012 76.8 0 Cam Nut M2 Stainless Steel 00028 0 0 Cam Bolt M2 Stainless Steel 00072 77.5 0 Shelf Nut M2.5 Stainless Steel 00224 77.6 0 Payload Washers M2.5 Stainless Steel .0008 77.8 0 M3 x 5 Screws Stainless Steel 0046 74.9 0 M2 x 6 Screws Stainless Steel 00336 77.0 0 M3 X 8 Screws Stainless Steel 00672 77.2 0 M3 x 6 Screws Stainless Steel 00168 77.6 0 M3 Hex Nut Stainless Steel 00875 77.6 0 M3 Washer Stainless Steel 0012 77.7 0 16

The majority of stainless steel components demise upon reentry and Argus—02 complies with the 1:10,000 probability of Human Casualty Requirement 4.7—1. A breakdown of the determined probabilities follows: Table 5: Requirement 4.7—1 Compliance for Argus—02 Risk of Human Status Casualty Argus—02 Compliant *Requirement 4.7—1 Probability of Human Casualty > 1:10,000 If a component survives to the ground but has less than 15 Joules of kinetic energy, it is not included in the Debris Casualty Area that inputs into the Probability of Human Casualty calculation. This is why Argus—02 has a 1:0 probability as none ofits components survive to the ground with more than 15J of energy. Argus—02 is shown to be in compliance with Requirement 4.7—1 of NASA—STD— 8719.14A. 17

Section 8: Assessment for Tether Missions Argus—02 will not be deploying any tethers. Argus—02 satisfies Section 8‘s requirement 4.8—1. 18

Section 9—14 ODAR sections 9 through 14 pertain to the launch vehicle, and are not covered here. Launch vehicle sections of the ODAR are the responsibility of the CRS provider. If you have any questions, please contact the undersigned at 321—867—2098. /original signed by/ Yusef A. Johnson Flight Design Analyst a.i. solutions/KSC/AIS2 ce: VA—H/Mr. Carney VA—H1/Mr. Beaver VA—H1/Mr. Haddox VA—C/Mr. Higginbotham VA—C/Mrs. Nufer VA—G2/Mr. Treptow SA—D2/Mr. Frattin SA—D2/Mr. Hale SA—D2/Mr. Henry Analex—3/Mr. Davis Analex—22/Ms. Ramos 19

Appendix Index: Appendix A. Argus—02 Component List by CubeSat 20

Appendix A. Argus—02 Component List Argus 1U CubeSat Demise 2 Endums:l:;“éfi:um: Top Aluminum 6061—T6 Box 264 100 100 7 No — Demise 3 EndurosatElement Sguclare: Boltom Aluminum 6061—T6 Box 239 100 100 6.5 No — Demise 4 Endurosat Structure: Legs Aluminum 6061—T6 Box 37.179 2.5 2.5 100 No — Demise 5 Solar Panel Z+ With UHF FR—4, Shape Memory Box 95 98 93 16.3 No _ Demise Antenna Alloy 6 Solar Panel Z— FR—4 Box 48 | 98 98 8.6 No — Demise 7 Solar Panels X/Y FR—4 Box 132 82.6 98 8.6 No — Demise 8 Side Panel Aluminum 6061 —T6 Box 32.95 $2.7 98.2 1.6 No — Demise 9 Payload Bay Polyamide 2200 Box 37.06 86.2 91.6 40.2 No — Demise 10 Cable Bracket Polyamide 2200 Irregular 8.12 40.0 25.0 40.0 No — Demise Aluminum 6061, FR— 11 Edurosat EPS 4, Lithium Polymer Box 198 90 96 21 No — Demise Battery 12 Endurosat UHF Transciever Alummurr;6061 . FR— Box 94 89 95 23.2 No — Demise 13 Raspberry Pi Zero FR4 Box 11.56 30.5 65.1 10.3 No — Demise 14 Zeus Board FR—4 Box 18.65 29.9 65.0 11.1 No — Demise 15 Raspberry Pi Camera V2 FR—4 Box 3.53 1.0 23.8 24.9 No — Demise 16 Connection Circuit Board FR—4 Box 50.89 90.0 97.0 25 No — Demise 17 Watchdog Timer Board FR4 Box 9.97 33.3 63.4 10 No — Demise Lithium (coin cell 18 RTC Battery battery with metal Cylinder 0.75 124 — 2.0 No — Demise exterior) 19 Magnet NdFeB Cylinder 1.51 3.175 — 25.4 No — Demise 20 Hysteresis Rods HY—MU 80 Cylinder 6.63 3.4 — 42 No 2642° Demise 21

ABS housing, FR—4 21 Roller Switches board Box 15 5.12 20 14.52 No — Demise 22 Antenna Cables 1 Copper Cylinder 100 5 100 — No — Demise 23 Watchdog Cables 4 Copper Cylinder 24 2 150 — No — Demise 24 Kapton Tape — Polyimide Fitm Amorphous 12 — — — No — Demise 25 Epoxy — 0151 Hysol Amorphous 20 — — — No ~ Demise 26 Solder — 88 (‘633’;12 )Le"‘d Amorphous 0.00 — — — No — Demise 27 Cai’{‘:;gée‘igg 22‘;&?“‘ — Cylinders 100 3,8 100 — No — Demise 28 .SicoceSeriong — * Wedcy®" Amorphous 142 — — — No — Demise 29 Threadftr;‘ifu':’f for it 4 Brass Cylinder 16.92 2.84 95.35 — No — Demise 30 P"mgggg’ 4 Stainless Steel Cylinder 416 221 36.68 z Yes 2750° Demise 31 CCSuppg on 4 Stainless Stel Cylinder 1.12 221 10.00 — Yes 2750° Demise 32 Paylaod — Cam Nut M2 4 Stainless Steel Cylinder 0.28 3.86 1.14 — Yes 2750° Demise 33 Payload — Cam Bolt M2 4 Stainless Steel Cylinder 0.72 4.17 13.46 — Yes 2750° Demise 34 Payload — Shelf Nut M2.5 32 Stainless Steel Cylinder 2.24 4.90 1.50 — Yes 2750° Demise 35 Payload Washers M2.5 8 Stainless Steel Cylinder 0.8 5.84 0.46 — Yes 2750° Demise 36 M3 x 5 Screw in Structure 20 Stainless Steel Cylinder 4.6 5.61 5.00 — Yes 2750° Demise 37 M2 x 6 Screw in Structure 8 Stainless Steel Cylinder 3.36 3.91 7.59 — Yes 2750° Demise 38 M3 X 8 Screw in Strucutre 16 Stainless Steel Cylinder 6.172 5.49 * 8.03 — Yes 2750° Demise 39 M3 X 6 Screw in Strucutre 4 Stainless Steel Cylinder 1.68 5.61 6.00 — Yes 2750° Demise 40 M3 Hex Nut 25 Stainless Steel Cylinder 8.75 5.50 — 24 Yes 2750° Demise 41 M3 Washer 12 Stainless Steel Cylinder 1.2 6.00 — 0.5 Yes 2750° Demise 22


Document Created: 2019-04-24 14:01:28
Document Modified: 2019-04-24 14:01:28
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