Orbital Debris Assessment Report

0879-EX-ST-2019 Text Documents

University of Washington

2019-05-11ELS_229759

ELVL—0045523 April 9, 2019 Orbital Debris Assessment for the HuskySat—I Mission per NASA—STD 8719.14A

Signature Page /)th_S_m)l, Analyst, a.i. solutions, AIS2 Scott Higginbotham, Missiop@fi anager, NASA KSC VA—C

National Aeronautics and Space Administration John F. Kennedy Space Center, Florida Kennedy Space Center, FL 32899 ELVL—2019—0045523 Reply to Attn of. VA—H1 April 9, 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 HuskySat—I CubeSat REFERENCES: A. NASA Procedural Requirements for Limiting Orbital Debris Generation, NPR $715.6A, 5 February 2008 Processfor Limiting Orbital Debris, NASA—STD—8719.14A, 25 May 2012 0aw International Space Station Reference Trajectory, delivered May 2017 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 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— 40 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, mo Suzanne Aleman to Justin Treptow, 10, March 2014 HQ OSMA Email:6U CubeSat Battery Non Passivation Suzanne Aleman to i Justin Treptow, 8 August 2017 The intent of this report is to satisfy the orbital debris requirements listed in ref. (a) for theHuskySat—I CubeSat, which will be deployed from a Cygnus spacecraft, post—ISS departure. 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.

RECORD OF REVISIONS DESCRIPTION DATE Original submission April 2019

The following table summarizes the compliance status of the HuskySat—I CubeSat to be deployed from the Cygnus spacecraft, post—ISS departure. HuskySat—I is fully compliant with all applicable requirements. Table 1: Orbital Debris Requirement Com liance Matrix Requirement Compliance Assessment Comments 4.3—la 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 3.5 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 HuskySat—I

Section 1: Program Management and Mission Overview HuskySat—I 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: HuskySat—I: Dr. Robert Winglee, Principal Investigator, University of Washington

Program Milestone Schedule Task Date CubeSat Selection October 30¢", 2018 Delivery to Nanoracks August 15%, 2019 Launch October 19¢", 2019 Deployment NET January 2020 Figure 1: Program Milestone Schedule HuskySat—I will be launched as a payload on the Antares launch vehicle executing the NG—12 mission. HuskySat—I will be deployed from the Cygnus spacecraft post—ISS departure. HuskySat—I weighs approximately 3.7 kg.

Section 2: Spacecraft Description Table 2: outline the generic attributes of the spacecraft. Table 2: HuskySat—I Attributes CubeSat CnpeSat CubeSat Names R CubeSat size (mmr) Masses Quantity (kg) HuskySat—I 1 340.5 x 102 x 102 3.67 The following pages describe the HuskySat—I CubeSat.

HuskySat—l— University of Washington — 3U Camera payioad Power distribution COM2: 1$1$ antenna: 246Hz I% uup/vHF RUTIx fllqht Power generation /”'""w / ADCS actuators AMSAT linear ADCS Propuision unit: transponder sensor contains tungsten processing electrodesa Figure 2: HuskySat—I exploded view Overview The HuskySat—I is a 3U CubeSat being developed by the University of Washington (UW). The two primary scientific payloads are a pulsed plasma thruster propulsion system and a software defined high frequency downlink system. In addition to these scientific payloads, the HuskySat—I is carrying an AMSAT radio. This mission is being licensed under part 5 with the FCC, and it is intended that once the University of Washington has completed its mission objectives, AMSAT will license the HuskySat under part 97. CONOPS After deployment from the Cygnus, the power distribution board will turn on as well as the COM1 communication system. After waiting 30min, the ISIS antenna will be deployed, and the beacon will begin. Beaconing consists of 10s transmissions every 2min at transmit level of 20dBm. Once contact is made with the ground station spacecraft health checkout will begin. After the state is known, if no anomalies are detected, normal operations will begin. Normal operations will consist of the pulsed plasma thruster, COM2 operation, and camera operation. After completing these objectives, the

HuskySat—I will be re—commissioned by AMSAT and will continue operating as an amateur radio repeater satellite until the satellite burns up in the atmosphere. Materials The CubeSat structure is made of aluminum. It contains standard commercial off the shelf (COTS) materials, and electrical components. HuskySat—I‘s propulsion system consists of a tungsten electrode and a solid sulfur propellant. Hazards There are no pressure vessels or hazardous materials. Batteries HuskySat—I uses rechargeable lithium batteries (Model APR18650M1A) for power storage. These batteries contain protection against various off—nominal conditions such as over/under voltage protection, overcurrent protection, and under temperature protection. The batteries have UN38.3 certification. 10

Section 3: Assessment of Spacecraft Debris Released during Normal Operations P 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. Since there are no releases are planned for HuskySat—I, 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 HuskySat—I mission. The probability of battery 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 CubeSats 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 3.5 years maximum, HuskySat—I 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 em in diameter during the orbital lifetime of the spacecraft takes into account both the mean cross sectional area and orbital lifetime. Camera payload Power distribution AMSAT linear ADCS Propulsion unit: transponder sensor contains tungsten procassing elactrodes Figure 4: HuskySat—I Expanded View * (w * A)] Mean CSA = ZSurft;ce Area _ [2 * (w *1) ';4 Equation 1: Mean Cross Sectional Area for Convex Objects A +A + A 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. This configuration renders the longest orbital life times for all CubeSat. Once a CubeSat has been ejected from the CubeSat dispenser and deployables have been extended, Equation 2 is utilized to determine the mean CSA. Amax is identified as the view that yields the maximum cross—sectional area. A1 and Az are the two cross—sectional areas orthogonal to Amax. Refer to Appendix A for component dimensions used in these calculations The HuskySat—I (3.67 kg) orbit at deployment will be 500 km circular at a 51.6° inclination. With an area to mass ratio of 0.0083 m*/kg, DAS yields ~3.5 years for orbit lifetime for its stowed state, which in turn is used to obtain the collision probability. 13

HuskySat—I 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. 14

CubeSat HuskySat—l Mass (kg) 3.67 a Mean C/S Area (m42) 0.0295 § Area—to Mass (m"2/kg) 00803 2 Orbital Lifetime (yrs) 3.5 h6 Probability of collision (10"X) 0.0000 Solar Flux Table Dated 12/18/2018 *Antennae area is negligible with respect to orbital lifetime calculations Table 3: CubeSat Orbital Lifetime & Collision Probability 15

The probability of HuskySat—I 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. HuskySat—I has 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 HuskySat—I to be compliant. Requirement 4.5—2 is not applicable to this mission. Section 6: Assessment of Spacecraft Postmission Disposal Plans and Procedures HuskySat—I 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. Calculating the area—to—mass ratio for the worst—case (smallest Area—to—Mass) post— mission disposa finds HuskySat—I in its stowed configuration as the worst case. The area— to—mass is calculated for is as follows: Mean ©C/‘gArea (m*) a J m 1w# Mass (kg) t rea — to to — ass (uim kg) Equation 3: Area to Mass The assessment of the spacecraft illustrates HuskySat—I are compliant with Requirements 4.6—1 through 4.6—5. DAS 2.1.1 Orbital Lifetime Calculations: DAS inputs are: 500 km circular orbit with an inclination of 51.6° at deployment no earlier than January 2020. An area to mass ratio of ~0.008 m*/kg for the HuskySat—I CubeSat was used. DAS 2.1.1 yields a 3.5 years orbit lifetime for HuskySat—I in its stowed state. 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. 16

Section 7: Assessment of Spacecraft Reentry Hazards A detailed assessment of the components of HuskySat—I 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: HuskySat—I High Melting Temperature Material Analysis PPT anode Tungsten .014 0 6 PPT electrode Tungsten 0001 0 0 Fasteners Stainless Steel 18—8 .130 77.6 — The majority of stainless steel components demise upon reentry and HuskySat—I complies with the 1:10,000 probability of Human Casualty Requirement 4.7—1. A breakdown of the determined probabilities follows: 17

Table 5: Requirement 4.7—1 Compliance for HuskySat—I Risk of Human Casualty HuskySat—l 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 HuskySat—I has a 1:0 probability as none of its components have more than 15J ofenergy. HuskySat—I is shown to be in compliance with Requirement 4.7—1 of NASA—STD— 8719.14A. 18

Section 8: Assessment for Tether Missions HuskySat—I will not be deploying any tethers. HuskySat—I satisfies Section 8‘s requirement 4.8—1. 19

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.1i. solutions/KSC/AIS2 cc: 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 20

Appendix Index: Appendix A. HuksySat—1 Component List: 21

Appendix A. HuskySat—I Component List — HuskySat—I — Box 3673 340.5 100 100 — — = 1 PPT anode Tungsten cylinder 14 4.8 40 = Yes 6191° 0 km 2 PPT electrode Tungsten cylinder 0.1 1.5 3.5 = Yes 6191° 0 km 3 CubeSat Structure Aluminum 7075 Box 470 102 226 102 «No — Demise 4 Propulsion Module Aluminum 7075 Box 665 104 104 82 No — Demise Multiple 5 Battery Board lithium batteries Board 230 90 90 26 No — Demise Assembly 6 COM2 Module Aluminum 7075 Box 426 90 90 49 No — Demise 7 COM!1 antenna Aluminum Box 89 100 100 6. No — Demise 8 Solar Panels FR4 Panel 243 82 277 3 No — Demise Board Stack a 9 ; AMSAT linear transponder FR4 Assembly 177 90 92.5 21 No — Demise Multiple 10 Battery Board lithium batteries Board 230 90 90 26 No — Demise Assembly 11 Power Generation Board FR4 Board 48 90 90 10 No — Demise 12 Power Distribution Board FR4 Board 53 90 90 10 No — Demise ‘Multiple 13 Camera Board FR4 Board 103 90 90 15 No — Demise Assembly 14 COM2 Module Aluminum 7075 Box 480 90 90 49 No — Demise 15 ADCS Flight Computer — — 48 90 90 10 No — Demise 16 ADCS Sensor Board — — 81 90 90 10 No — Demise 17 ADCS Actuators Copper = 150 90 90 35 No ~ Demise 18 Fasteners Stainless 18—8 Cylinder 130 #4 or #2 <3" = Yes 2500° Demise 19 Cabling Copper — 50 <l2ga — — No — Demise 22

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Document Created: 2019-04-09 11:45:35
Document Modified: 2019-04-09 11:45:35
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