ODAR

0297-EX-CN-2016 Text Documents

California Polytechnic State University

2017-02-03ELS_187462

ELVL-2017-0044671 January 14, 2017 Orbital Debris Assessment for The CubeSats on the (LV) /ELaNa-19 Mission per NASA-STD 8719.14A

Signature Pag 3

National Aeronautics and Space Administration John F. Kennedy Space Center, Florida Kennedy Space Center, FL 32899 ELVL-2017-0044671 Reply to Attn of: VA-H1 January 14, 2017 TO: Garrett Skrobot, LSP Mission Manager, NASA/KSC/VA-C FROM: Justin Treptow, NASA/KSC/VA-H1 SUBJECT: Orbital Debris Assessment Report (ODAR) for the ELaNa-19 Mission (FCC) REFERENCES: A. NASA Procedural Requirements for Limiting Orbital Debris Generation, NPR 8715.6A, 5 February 2008 B. Process for Limiting Orbital Debris, NASA-STD-8719.14A, 25 May 2012 C. Armstrong, Jason; TriSept Corp. “ODAR info” email, Oct 20, 2016. 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. UL 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 The intent of this report is to satisfy the orbital debris requirements listed in ref. (a) for the ELaNa-19 primary mission payload. 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. 3

The following table summarizes the compliance status of the ELaNa-19 auxiliary payload mission flown on ELaNa XIX. The fourteen CubeSats comprising the ELaNa-19 mission are fully compliant with all applicable requirements. Table 1: Orbital Debris Requirement Compliance Matrix Requirement 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 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 6.6 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 ELaNa-19 includes the CubeSail mission, containing a 250m solar sail / tether 4

Section 1: Program Management and Mission Overview The ELaNa-19 mission is sponsored by the Human Exploration and Operations Mission Directorate at NASA Headquarters. The Program Executive is Jason Crusan. Responsible program/project manager and senior scientific and management personnel are as follows: ANDESITE: Walsh Brian, Principle Investigator CeREs: Summerlin Errol, Principle Investigator CHOMPTT: Conklin John, Principle Investigator CubeSail: Carroll David, Principle Investigator DaVinci: Finman Lorna, Principle Investigator ISX: Bellardo John, Principle Investigator NMTSat: Jorgensen Anders, Principle Investigator RSat: Kang Jin, Principle Investigator Shields-1: Thomsen Laurence, Principle Investigator STF-1: Grubb Matthew, Principle Investigator TOMSat EAGLESCOUT: Hattersley Bonnie, Principle Investigator TOMSat R3: Hattersley Bonnie, Principle Investigator GEOStare: de Vries Wim, Principle Investigator SHFT-1: Lux Jim, Principle Investigator 5

Program Milestone Schedule Task Date CubeSat Selection CSLI award February 2016 CubeSat Mission Readiness review: February 28th 2017 CubeSat delivery to TriSept May 8th 2017 CubeSat integration with LV May 18th 2017 Launch date June 23rd 2017 Figure 1: Program Milestone Schedule The ELaNa-19 mission will be launched as the Primary payload on the VCLS RocketLabs ELaNa XIX mission on an Electron launch vehicle from CCAFS, FL. The ELaNa-19 compliment, will deploy 14 pico-satellites (or CubeSats). The CubeSat slotted position is identified in Table 2: ELaNa-19 CubeSats. The ELaNa-19 manifest includes: ANDESITE, CeREs, CHOMPTT , CubeSail, DaVinci, ISX, NMTSat, RSat, Shields-1, STF-1, TOMSat EAGLESCOUT, TOMSat R3, GEOStare, and SHFT-1. The current launch date is in June 23, 2017. The 14 CubeSats are to be ejected from the Electron shortly after the launch, placing the CubeSats in an orbit approximately 500 X 500 km at inclination of 85 deg (ref. (h)). Each CubeSat ranges in sizes from a 10 cm x 10cm x 30 cm to 10 cm x 20 cm x 30 cm, with masses from about 1.81 kg to ~9.19 kg total. The CubeSats have been designed and universities and government agencies and each have their own mission goals. 6

Section 2: Spacecraft Description There are 14 CubeSats flying on the ELaNa-19 Mission. Table 2: ELaNa-19 CubeSats outlines their generic attributes. Table 2: ELaNa-19 CubeSats CubeSat CubeSat CubeSat Masses CubeSat size Quantity Names (kg) 1 6U (24 cm x 36.3 cm x 11 cm) ANDESITE 9.19 1 3U (10 cm x 10 cm x 34 cm) CeREs 4.56 1 3U (10 cm x 10 cm x 34 cm) CHOMPTT 1.56 1 3U (10 cm x 10 cm x 31 cm) CubeSail 3.74 1 3U (11.7 cm x 11.3 cm x 34.05 cm) DaVinci 2.60 1 3U (11.2 cm x 11.1 cm x 34.05 cm) ISX 3.70 1 3U (10 cm x 10 cm x 34 cm) NMTSat 1.58 1 3U (11.3 cm x 11.3 cm x 34.05 cm) Rsat 4.15 1 3U (10.6 cm x 10.6 cm x 34.05 cm) Shields-1 6.94 1 3U (11.5 cm x 11.5 cm x 34.05 cm) STF-1 1.81 TOMSat 1 3U (10.3 cm x 10.3 cm x 34.05 cm) 4.09 EAGLESCOUT 1 3U (10.3 cm x 10.3 cm x 34.05 cm) TOMSat R3 4.09 1 3U (11.2 cm x 11.1 cm x 34.05 cm) GEOStare 7.15 1 3U (11.3 cm x 11.2 cm x 36.6 cm) SHFT-1 5.10 The following subsections contain descriptions of these 14 CubeSats. 7

ISX (Ionospheric Scintillation eXplorer) – Cal Poly, SLO – 3U Figure 11: ISX Expanded View Overview The Ionospheric Scintillation eXplorer (ISX) is a satellite developed by undergraduate and graduate students as part of the PolySat research group in collaboration with SRI. The satellite is sponsored by NSF. ISX will measure the scintillation of disrupts in ionospheric plasma tubules using DTV signals. ISX will study the multi-frequency radio wave propagation properties of intermediate-to-large scale ionospheric structures of Equatorial Spread F that cause rapid phase and amplitude fluctuation of transionospheric signals. CONOPS Upon deployment from the PPOD, ISX will power on. Approximately 15 minutes later, the antenna will deploy. 115 minutes after antenna deployment, the beacon will be activated and the satellite will be available to acquire with the ground station. Acquisition and verification of the correct orientation and rates of the satellite will take place one week into the mission. The payload will then start taking data for one year. Materials The structure is made of 6061-T6 Aluminum. The antenna is made of NiTi. The antenna route is made of Delrin. It contains standard commercial off the shelf (COTS) materials, electrical components, PCBs, and solar cells. Hazards There are no pressure vessels, hazardous or exotic materials. 18

Batteries The electrical power storage system consists of nine 3.7V 2600mAh Lithium-Ion 18650 batteries, model LR1865SK, with over-charge/current protection circuitry. There are three strings in parallel, with each string consisting of three batteries in series. UL Listing information is as follows BBCV2.MH48285. 19

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 on the ELaNa-19 CubeSat mission therefore this section is not applicable. 32

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 ELaNa-19 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)) ELaNa-19 manifest one, 6U CubeSats which are not included in the 3U or smaller mentioned in ref. (h). However, this CubeSat has protective circuitry in their designs and COTS components. ANDESITE’s EPS and battery system has over-current poly switch protection, over- current bus protection, and battery under-voltage protection built into the EPS system. The ANDESITE CubeSat use UL listed battery cells. 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 6.6 years maximum the ELaNa-19 CubeSat is compliant. 33

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. The largest mean cross sectional area (CSA) among the fourteen CubeSats is that of the CubeSail CubeSat with solar sail / tether deployed (250m X 0.08m solar sail): Figure 21: CubeSail Deployed Config +./0'1& ,/&' = 3 5 6 +2 5 8 %&'( *+, = 2 2 Equation 1: Mean Cross Sectional Area for Convex Objects %&'( *+, = , 9': + ,; + ,; 3 Equation 2: Mean Cross Sectional Area for Complex Objects All CubeSats evaluated for this ODAR are stowed in a convex configuration, indicating there are no elements of the CubeSats obscuring another element of the same CubeSats from view. Thus, mean CSA for all stowed CubeSats was calculated using Equation 1. This configuration renders the longest orbital life times for all CubeSats. Once a CubeSat has been ejected from the P-POD 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 A2 are the two cross-sectional areas orthogonal to Amax. Refer to Appendix A for component dimensions used in these calculations The CubeSail (3.74 kg) orbit at deployment is 500km apogee altitude by 500 km perigee altitude, with an inclination of 85 degrees. With an area to mass ratio of 2.684 m2/kg, DAS yields 0.1 years for orbit lifetime for its deployed state, which in turn is used to obtain the collision probability. Even with the variation in CubeSat design and orbital 34

lifetime ELaNa-19 CubeSats see an average of 0.00000 probability of collision. All CubeSats on ELaNa-19 were calculated to have a probability of collision of 0.00000. Table 4 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. 35

Table 4: CubeSat Orbital Lifetime & Collision Probability Stowed Deployed Mean C/S Area-to Orbital Probability of Area-to Orbital Probability of Mean C/S CubeSat Mass (kg) Area (m^2) Mass (m^2/kg) Lifetime (yrs) collision (10^X) Area (m^2) Mass (m^2/kg) Lifetime (yrs) collision (10^X) ANDESITE 9.19 0.0763 0.0083 5.8 0.00000 0.1083 0.012 5.2 0.00000 CeREs 4.56 0.0390 0.0086 5.7 0.00000 0.0735 0.016 4.8 0.00000 CHOMPTT 1.56 0.0390 0.0250 4.4 0.00000 0.0415 0.027 4.3 0.00000 CubeSail 3.74 0.0362 0.0097 5.5 0.00000 10.0364 2.684 0.1 0.00000 DaVinci 2.60 0.0459 0.0177 4.7 0.00000 0.1006 0.039 4 0.00000 ISX 3.70 0.0442 0.0120 5.2 0.00000 0.0445 0.012 5.2 0.00000 NMTSat 1.58 0.0417 0.0264 4.3 0.00000 0.0493 0.031 4.2 0.00000 Rsat 4.15 0.0449 0.0108 5.3 0.00000 0.0629 0.015 4.9 0.00000 Shields-1 6.94 0.0417 0.0060 6.6 0.00000 0.0494 0.007 6.2 0.00000 STF-1 1.81 0.0467 0.0259 4.3 0.00000 0.0490 0.027 4.3 0.00000 TOMSat 4.09 0.0406 0.0099 5.5 0.00000 0.0635 0.016 4.8 0.00000 EAGLESCOUT TOMSat R3 4.09 0.0406 0.0099 5.5 0.00000 0.0635 0.016 4.8 0.00000 GEOStare 7.15 0.0443 0.0062 6.4 0.00000 0.0880 0.012 5.2 0.00000 SHFT-1 5.10 0.0476 0.0093 5.6 0.00000 0.1855 0.036 4.1 0.00000 Solar Flux Table Dated 11/07/2016

The probability of any ELaNa-19 spacecraft collision 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. Since the CubeSats have no capability or plan for end-of-mission disposal, requirement 4.5-2 is not applicable. Assessment of spacecraft compliance with Requirements 4.5-1 shows ELaNa-19 to be compliant. Requirement 4.5-2 is not applicable to this mission. Section 6: Assessment of Spacecraft Postmission Disposal Plans and Procedures All ELaNa-19 spacecraft 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 postmission 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 disposal among the CubeSats finds Shields-1 in its stowed configuration as the worst case. The area-to-mass is calculated for is as follows: !"#$ & ' ()"# (+,) = ()"# , 34 !#.. ( + ) !#.. (/0) /0 Equation 3: Area to Mass ; 0.0417:; = 0.0060 : 6.94>? >? Shields-1 has the smallest Area-to-Mass ratio and as a result will have the longest orbital lifetime. The assessment of the spacecraft illustrates they are compliant with Requirements 4.6-1 through 4.6-5. DAS 2.0.2 Orbital Lifetime Calculations: DAS inputs are: 500 km maximum apogee 500 km maximum perigee altitudes with an inclination of 85 degrees at deployment no earlier than June 23rd 2017. An area to mass ratio of 0.0060 m2/kg for the Shields-1 CubeSat was imputed. DAS 2.0.2 yields a 6.6 years orbit lifetime for Shields-1 in its stowed state. This meets requirement 4.6-1. For the complete list of CubeSat orbital lifetimes reference Table 4: CubeSat Orbital Lifetime & Collision Probability. Assessment results show compliance.

Section 7: Assessment of Spacecraft Reentry Hazards A detailed assessment of the components to be flown on ELaNa-19 was performed. The assessment used DAS 2.0, 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 casualty. This never survive is confirmed throughreentry and pose DAS analysis noshowed that risk to human 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 similar components, 1500°C,dimensions it can and hasstainless be expected steel toa posses melting (1500°C). temperature the same If a component between negligible risk1000 °Cisand of as stainless steel components. See Table 5 through Table 7. Table 5: ELaNa-19 High Melting Temperature Material Analysis (1/3) CubeSat High Temp Component Material Demise Alt (km) KE (J) ANDESITE Node Deployment Springs Steel AISI 304 76.4 0 ANDESITE Antennae Steel AISI 410 0 0 ANDESITE 6-32 Screws Stainless Steel (generic) 77.5 0 ANDESITE 2-56 Screws Stainless Steel (generic) 77.4 0 ANDESITE Hinges Stainless Steel (generic) 0 1 CeREs Tungsten Tube Tungsten 0 150 CeREs Detector Silicon 0 0 CeREs Closeout Plate 1 Tungsten 0 8 CHOMPTT StenSat UHF Antennae Stainless Steel (generic) 0 0 CHOMPTT Lithium UHF Antennae Stainless Steel (generic) 0 0 CHOMPTT Backplane Holder - 11 mm Steel AISI 304 0 0 CHOMPTT Backplane Holder - 13 mm Steel AISI 304 0 0 CHOMPTT Reaction Wheel Assembly Stainless Steel (generic) 68.6 0 38

Table 6: ELaNa-19 High Melting Temperature Material Analysis (2/3) CubeSat High Temp Component Material Demise Alt (km) KE (J) CHOMPTT Batteries Stainless Steel (generic) 69 0 CHOMPTT Battery Holder Plates 2a&2b Steel AISI 304 0 25 CHOMPTT Lithium Radio Stainless Steel (generic) 0 6 CHOMPTT Retoreflector Array Stainless Steel (generic) 0 4 CubeSail New Component Stainless Steel (generic) 0 1 CubeSail Fasteners* Stainless Steel (generic) 77.9 0 CubeSail SRU Nut Plate Stainless Steel (generic) 74.4 0 CubeSail Motor Steel AISI 304 70 0 CubeSail Drive Pin Steel AISI 304 77.1 0 CubeSail Reaction Wheel Daughter Board Stainless Steel (generic) 0 14 ISX Historesis Material Stainless Steel (generic) 77 0 ISX Screw - Representative Stainless Steel (generic) 76.9 0 ISX Structural Rods Stainless Steel (generic) 77.4 0 ISX ISIS screws Stainless Steel (generic) 77.1 0 ISX ISIS washers Stainless Steel (generic) 0 0 ISX GAMMA Antenna washers Stainless Steel (generic) 0 0 ISX GAMMA Antenna screws Stainless Steel (generic) 76.2 0 ISX GAMMA Antenna nuts Stainless Steel (generic) 0 0 ISX solar panel screw Stainless Steel (generic) 76.6 0 ISX solar panel nut Stainless Steel (generic) 0 0 ISX Solar panel clip Stainless Steel (generic) 0 0 ISX 15mm spacers Stainless Steel (generic) 75 0 ISX 25mm spacers Stainless Steel (generic) 73.5 0 Rsat Motors Stainless Steel (generic) 73.3 0 Rsat ADCS Stainless Steel (generic) 0 3 Rsat Fasteners Stainless Steel (generic) 77.6 0 Shields-1 Shield0 Titanium (6 Al-4 V) 0 16 Shields-1 Shield1 Tantalum 0 69 Shields-1 Shield2 Titanium (6 Al-4 V) 0 14 Shields-1 Shield3 Tantalum 0 27 Shields-1 Shield4 Titanium (6 Al-4 V) 0 0 Shields-1 Shield5 Tantalum 0 0 Shields-1 Shield6 Titanium (6 Al-4 V) 0 0 Shields-1 Shield7 Titanium (6 Al-4 V) 0 0 Shields-1 Shield8 Titanium (6 Al-4 V) 0 0 Shields-1 Charge Dissipation Film electrodes Steel AISI 304 73.8 0 Shields-1 Charge Dissipation Film spring Stainless Steel (generic) 76.1 0 Shields-1 RTDs (Est Dims) Stainless Steel (generic) 77.5 0 Shields-1 Fasterners2 Stainless Steel (generic) 77.7 0 Shields-1 Fasteners3 Stainless Steel (generic) 77.7 0 39

Table 7: ELaNa-19 Summary of Surviving High Temperature Material Components (3/3) CubeSat High Temp Component Material Demise Alt (km) KE (J) Shields-1 Fasteners4 Stainless Steel (generic) 0 0 Shields-1 Solar Panel Screws Steel AISI 410 77.6 0 Shields-1 Solar Panel Washers Steel AISI 410 0 0 Shields-1 Remove Before Flight Pin Stainless Steel (generic) 73.7 0 Shields-1 Sep Switch Stainless Steel (generic) 73.7 0 Shields-1 ADCS Components (Hysteresis Rods) Stainless Steel (generic) 77.5 0 STF-1 Ferrite Bead Stainless Steel (generic) 77.3 0 STF-1 Geiger Tube Stainless Steel (generic) 67 0 STF-1 Fasteners5 Stainless Steel (generic) 77.9 0 TOMSat Reaction Wheels Stainless Steel (generic) 63.9 0 TOMSat Single Torque Rod Stainless Steel (generic) 74.8 0 TOMSat 18267 Titanium (generic) 0 2 TOMSat 18265 Titanium (generic) 0 1 TOMSat 18264 Titanium (generic) 0 1 TOMSat 18268 Titanium (generic) 0 0 TOMSat 18266 Titanium (generic) 0 2 TOMSat 18263 Titanium (generic) 0 0 TOMSat 18270 Titanium (generic) 0 0 TOMSat Laser Aluminum 6061-T6 72.8 0 GEOstare Batteries-GEOStae Stainless Steel (generic) 0 1 GEOstare Telescope baffle Titanium (generic) 0 22 GEOstare Telescope Stainless Steel (generic) 65.4 0 GEOstare Fasteners7 Steel A-286 78 0 SHFT-1 Internal Fasteners Stainless Steel (generic) 77 0 SHFT-1 External Fasteners Stainless Steel (generic) 77 0 The majority of high temperature components demise upon reentry. And all CubeSats comply with the 1:10,000 probability of Human Casualty Requirement 4.7-1. A breakdown of the determined probabilities follows on Table 8. 40

Table 8: Requirement 4.7-1 Compliance by CubeSat CubeSat Risk Risk < 1:10,000 ANDESITE 1:0 Compliant CeREs 1:210,600 Compliant CHOMPTT 1:93,400 Compliant CubeSail 1:0 Compliant DaVinci 1:0 Compliant ISX 1:0 Compliant NMTsat 1:0 Compliant Rsat 1:0 Compliant Shields-1 1:32,400 Compliant STF-1 1:0 Compliant TOMSat 1:0 Compliant GEOstare 1:200,000 Compliant SHFT-1 1:0 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. Which is why CubeSats that have surviving components like ANDESITE, CubeSail, DaVinci, ISX, NMTsat Rsat, STF-1 TOMSat EAGLESCOUT, TOMSat R3, and SHFT-1 have a 1:0 probability as none of their components have more than 15J of energy. The breakdown of CubeSat’s with greater than 15J of energy components is as follows: CeREs has 1, CHOMPTT has1, Shields-1 has 3, and GEOStare has 1. All CubeSats launching under the ELaNa-19 mission are shown to be in compliance with Requirement 4.7-1 of NASA-STD-8719.14A. See the Appendix for a complete accounting of the survivability of all CubeSat components. 41

Section 8: Assessment for Tether Missions In the ELaNa-19 mission, CubeSail’s deployable sail made of a mylar film qualifies as a momentum tether although a ribbon would be a more accurate description of its dimensions (0.0004 cm x 7.9cm x 25,317 cm). The tether mission plan can be referenced in the CubeSail specific mission plan located in Section 2. Following the Methods to Assess Compliance for Tethered Systems (section 4.8.4), the DAS analysis determined the CubeSail design to be COMPLIANT with both Requirement 4.5-1 and 4.5-2 dealing with meeting the requirements limiting the generation or orbital debris from on-orbit collisions. The probability of collision on orbit for the un-deployed system, fully deployed system, and ½ the system in the event of a tether severing event was calculated to be << 0.001. CubeSail is also compliant with Requirements 4.6-1 to 4.6-4 (Postmission Disposal), given the low 500km x 500km, this orbit will have CubeSail passively deorbit in 5.5 years if the system does not deploy, <<0.1 years if the system does deploy, and <<0.1 year if the tether breaks into two equal parts as calculated via DAS 2.0.2. All three scenarios are compliant with the Requirement 4.6-1 to 4.6-4. Figure 22: Tether Assessment of CubeSail ELaNa-19 CubeSat, CubeSail satisfies Section 8’s requirement 4.8-1. 42

Section 9-14 ODAR sections 9 through 14 for the launch vehicle are not covered here. If you have any questions, please contact the undersigned at 321-867-2958. /original signed by/ Justin Treptow Flight Design Analyst NASA/KSC/VA-H1 cc: VA-H/Mr. Carney VA-H1/Mr. Beaver VA-H1/Mr. Haddox VA-G2/Mr. Atkinson VA-G2/Mr. Marin SA-D2/Mr. Frattin SA-D2/Mr. Hale SA-D2/Mr. Henry Analex-3/Mr. Davis Analex-22/Ms. Ramos 43

Appendix Index: Appendix A. ELaNa-19 Component List by CubeSat: ANDESITE Appendix B. ELaNa-19 Component List by CubeSat: CeREs Appendix C. ELaNa-19 Component List by CubeSat: CHOMPTT Appendix D. ELaNa-19 Component List by CubeSat: CubeSail Appendix E. ELaNa-19 Component List by CubeSat: DaVinci Appendix F. ELaNa-19 Component List by CubeSat: ISX Appendix G. ELaNa-19 Component List by CubeSat: NMTSat Appendix H. ELaNa-19 Component List by CubeSat: RSat Appendix I. ELaNa-19 Component List by CubeSat: Shields-1 Appendix J. ELaNa-19 Component List by CubeSat: STF-1 Appendix K. ELaNa-19 Component List by CubeSat: TOMSat EAGLESCOUT Appendix L. ELaNa-19 Component List by CubeSat: TOMSat R3: Appendix M. ELaNa-19 Component List by CubeSat: GEOStare: Appendix N. ELaNa-19 Component List by CubeSat: SHFT-1 44

Appendix F. ELaNa-19 Component List by CubeSat: ISX (1/2) Diameter/ Row Individual Length Height High Melting CUBESAT Name Qty Material Body Type Width Survivability Number Mass (g) (mm) (mm) Temp Temp (mm) ISX 1 ISX 3U CubeSat 1 Various Box 3699.3 100 100 340.5 No - Demise ISX 2 CubeSat Structure 1 Aluminum 6061 Box 456 100 100 340.5 No - Demise ISX 3 +Z Panel 1 PCB Box 30 100 100 2.5 No - Demise ISX 4 -Z Panel 1 PCB Box 30 100 100 2.5 No - Demise ISX 5 Radio Daughter Board 1 PCB Box 15 36 83 2.5 No - Demise ISX 6 GPS Daughter Board 1 PCB Box 15 39 83 2.5 No - Demise ISX 7 GPS Patch 1 Ceramic Box 11.4 25.1 25.1 5.2 No - Demise ISX 8 C-Band Patch 1 Ceramic Box 2.1 12 12 4.3 No - Demise ISX 9 Antenna Routes 3 Delrin Box 5 65 65 3.4 No - Demise ISX 10 Antenna 6 Nitonol Wire Box 2 0.31 165 0.51 No - Demise ISX 11 System Board 1 PCB Box 60 100 83 3 No - Demise ISX 12 Payload Interface and Battery Board 1 PCB Box 50 83 83 3 No - Demise ISX 13 Side Panel 4 PCB Box 120 83 320 2.5 No - Demise ISX 14 Solar Cell 20 Eglass Box 2.3 70 40 0.5 No - Demise ISX 15 Solar Angle Sensor Board 5 PCB Box 5 20 30 2.5 No - Demise ISX 16 Solar Angle Sensor Apperture 5 Aluminum Box 3 19 21 5 No - Demise ISX 17 Battery Bracket 1 Aluminum 6061 Box 168 76 82 67 No - Demise ISX 18 Heat Shrink 2 RNF-100 Polyolefin Heat Shrink Tube 2 63.5 25.4 0.5 No - Demise ISX 19 Batteries 9 Lithion Ion Cylinder 45 18.4 65.1 N/A No - Demise ISX 20 Dummy Cell 1 Delrin Cylinder 10 19 66 N/A No - Demise 53


Document Created: 5310-04-26 00:00:00
Document Modified: 5310-04-26 00:00:00
© 2024 FCC.report
This site is not affiliated with or endorsed by the FCC