ODAR

0474-EX-CN-2018 Text Documents

University of Central Florida

2018-06-18ELS_211473

ELVL-2016-0044593 April 18, 18 Orbital Debris Assessment for The CubeSats on the ICESat-2/ELaNa-18 Mission per NASA-STD 8719.14A Sensitive But Unclassified (SBU)

Signature Page Yusef ?ognson, Analyst, a.i. solutions Inc AIS2 4. ———~—<fafig Rex Engelhardt, Mission Manager, NASA KSC VA—C Jason Crusan, Program Executive, NASA HEOMD Suzanne Aleman, NASA HQ OSMA MMOD Program Executive Signatures Required for Final Version of ODAR Terrence W. Wilcutt, NASA Chief, Safety and Mission Assurance William Gerstenmaier, NASA AA, Human Exploration and Operations Mission Directorate

RECORD OF REVISIONS REV DESCRIPTION DATE 0 Basic Issue February 2017 A Deletion of CHIEFS at. Addition of ELFIN-Star and April2018 SURFS at 3

National Aeronauties and Space Administration John F. Kennedy Space Center, Florida Kennedy Space Center, FL 32899 ELVL—2016—0044593 Reply to Attn of: VA—H1 April 18, 18 TO: Scott Higginbotham, LSP Mission Manager, NASA/KSC/VA—C FROM: Justin Treptow, NASA/KSC/VA—H1 SUBJECT: Orbital Debris Assessment Report (ODAR) for the ELaNa—18 Mission (DRAFT) REFERENCES: A. NASA Procedural Requirements for Limiting Orbital Debris Generation, NPR 8715.6A, 5 February 2008 Process for Limiting Orbital Debris, NASA—STD—8719.14A, 25 May 2012 Preliminary Mission Analysis for the Delta II 7420/ICEAT—2 Spacecraft Mission — CDRL C4—1, PGAA#2, ULA—TP—16—163, Sept 2016 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 Safety for Lithium Batteries, UL 1642. UL Standard. 4th ed. Northbrook, IL, Underwriters Laboratories, 2007 Kwas, Robert. Thermal Analysis of ELaNa—4 CubeSat Batteries, ELVL—2012— 0043254; Nov 2012 Range Safety User Requirements Manual Volume 3— Launch Vehicles, Payloads, and Ground Support Systems Requirements, AFSCM 91—710 V3. 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—18 auxiliary mission launching in conjunction with the ICESAT2 primary 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.

The following table summarizes the compliance status of the ELaN a-18 auxiliary payload mission flown on IceSat-2. The four CubeSats comprising the ELaNa-18 mission are fully compliant with all applicable requirements. . Ta ble 1 0 rb1'tal Debr1s ' ReqmrementC om pJiance I' Ma t. nx 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 aQplicable No planned breakups 4.5-1 Compliant 4.5-2 Not aQQ).icable 4.6-l(a) Compliant Worst case lifetime 4.4 yrs 4.6-1(b) Not applicable 4.6-l(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 under ELaN a-18 mission 5

Section 1: Program Management and Mission Overview The ElaNa-18 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: DAVE: Dr. Jordi Puig-Suari & Dr. John Bellardo, Principal Investigators; Justin Foley, Project Manager ELFIN & ELFIN-Star: Lydia Bingley, Principal Investigator; Anais Zarifian, Systems Engineer SURFSat: Adrienne Dove, Principal Investigator, Joshua Cowell & Dawn Trout, Co:. Investigators 6

Program Milestone Schedule Task Date CubeSat Selection 11/16/2017 MRR 6/25/2018 CubeSat Integration into P-PODs 7/30/2018 CubeSat Delivery to VAFB 7/30/2018 Launch 9/12/2018 Figure 1: Program Milestone Schedule The ElaNa-18 mission will be launched as an auxiliary payload on the NASA ICESAT-2 mission on a Delta IT 7420-10 launch vehicle from VAFB, CA. The ElaNa-18 compliment, will deploy 4 pica-satellites (or CubeSats). The CubeSat slotted position is identified in Table 2: ElaNa-18 CubeSats. The ElaNa-18 manifest includes: Dave, ELFIN, ELFIN-Star, and SURFSat. The current launch date is in September 12,2017. The 4 CubeSats are to be ejected from PPOD deployers mounted on the Delta II second stage, placing the CubeSats in an orbit approximately 450 X 473 km at inclination of 93.0 deg (ref. (h)). The CubeSat dimensions range from the 1U configuration 10 em x lOcm x 10 em, to a 3U configuration of 10em x 10 em x 34 em with masses from about 3.2 kg to 3.7 kg total. The CubeSats have been designed and universities and government agencies and each have their own mission goals. 7

Section 2: Spacecraft Description There are 4 CubeSats flying on the ElaNa-18 Mission. Table 2: ElaNa-18 CubeSats outlines their generic attributes. Table 2: ElaNa-18 CubeSats CubeSat CubeSat P-POD# CubeSat size Names Masses (kg) 1 1U (lOcmx 10cmx llcm) DAVE 1.4 1 3U (10cm X lOcm X 34cm) ELFlN 3.4 1 3U (lOcm X lOcm X 34cm) ELFIN-Star 3.4 1 2U ( 1Ocm x lOcm x 22cm) SURFS at .89 The following subsections contain descriptions of these 4 CubeSats. 8

Dave — California Polytechnic University — 1U Shape Memory * Alloy {SMA) Actuatoir Single Pieca BeamfStructurne Segment Beam Locking Mechanism " Plezo Electric Actuator Particle Damper |_ ' Cavity Li—ion Battery Figure 2: DAVE Assembled View Overview: The Damping and Vibration Experiment (DAVE) CubeSat implements a payload to evaluate a mechanical damping technology in microgravity. This technology, called particle damping, exploits the dynamics of multiple constrained particles to dissipate vibration energy. Terrestrial applications demonstrate particle damping performance to be largely unaffected by extreme environments yet simple and cheap to implement. This feature set makes particle damping an attractive technology for applications in spacecraft, where dampers are needed to steady sensitive instrumentation and inhibit destructive structural resonant modes. In orbit, DAVE provides a low cost and low risk platform to characterize unknown particle damper microgravity behavior and provide flight heritage for particle damper technology. The completion of these objectives overcomes barriers currently inhibiting the employment of particle dampers in space. DAVE is equipped with one OmniVision imager. The primary purpose of the imager is verifying the rotation rates of the spacecraft prior to performing experiments. The secondary mission is acquiring Earth imagery to support public outreach activities. CONOPS: After deployment from the P—POD, the satellite will power on. Approximately 15 minutes later, antenna deployment will occur. 115 minutes after antenna deployment, the beacon will be activated and the satellite will be available to acquire with the ground station. A full parameter sweep vibration experiment will begin automatically within a few hours of launch. Results will be downloaded

over subsequent passes. Additional experiments can be commanded from the ground as necessary to improve confidence in the results. Materials: The structure is made entirely of 6061—T6 Aluminum. The antenna is made of NiTi and Delrin. The ceramic piezo electric beam actuators are lead zirconate titanate. The tips of the booms contain tungsten particles. The satellite contains mostly standard commercial off the shelf materials, electrical components, PCBs, and solar cells. Hazards: There are no pressure vessels, hazardous materials, or exotic materials. The cavities containing the tungsten particles are not freely vented. Batteries: There are 2x UL listed 3.7V 2600mAh Lithium—Ion 18650 batteries connected in parallel. The UL listing number is MH48285. There is battery protection circuitry and over—charge protection. 10

ELFIN/ELEIN—Star — UCLA —3U+ ( Payload Boards (siPs, orH, EPD—D1. _ a EPD—D2) Avianics Stack wil (sSerce 1 SBPCB 2 Rerrmmnmmimrinnes., . ecoam‘—< mernlil__ s sallhs: _ e itks PCPCB, ACB, LETC1 | ms '_—m;“—‘} nnas _| | ~——gde ‘L {Aominum, Tantalom) | somg ' 3 L8Alamincm, Tastalum} e |~~ 2e Battery _2A '\\\ Holder <_ D d EGZ (Roard, Brace, & | {BeCu) L___BLEZT_ Sik.. «~~ 1 Strap, Modalc} ’ & L—/_:" —— Figure 3: ELFIN Expanded View Overview: The Electron Losses and Fields Investigation (ELFIN) Mission, is a space weather CubeSat that will investigate the loss of relativistic particles from the radiation belts into the Earth‘s atmosphere. ELFIN will accomplish this using two primary payload instruments; a fluxgate magnetometer and an energetic particle detector. CONOPS: Upon deployment from the PPOD, ELFIN will power up and initiate a 45 minute timer counting down for antenna deployment. If tip off rates from the PPOD are large, ELFIN will execute an automatic detumble sequence in order to get the spacecraft in a stable attitude configuration. At 45 minutes, the UHF/VHF antennas will deploy, and the spacecraft will begin beaconing. After communication with the ground is established, spacecraft and instrument commissioning will begin. At a minimum of 2 weeks after deployment, the stacer boom will be commanded to deploy, the spacecraft will be spun up to ~20 rmp, and nominal operations will begin. Science will resume for a minimum of 3 months (nominally 6 months). Materials: ELFIN‘s structure is primarily composed of Aluminum 6061—T6, with some peek components as additional structural components. Most materials are standard commercial off the shelf, as well as standard electrical components, printed circuit boards, and solar cells. The Energetic Particle Detector is built with a combination of Aluminum and Tantalum parts. All Tantalum parts are internal components, and are relatively small. Hazards: There are no pressure vessels or hazardous materials on this satellite. Batteries: The power system uses 4 Molicel ICR18650J Lithium—ion batteries that are screened by the Aerospace Corporation before delivery to ELFIN. The UL listing number is BBCV2.MH27672. 11

SURFSat- University of Central Florida- 2U Figure 4: SURFSat Expanded View Overview: The space radiation environment in Earth's atmosphere is filled with hot and low-density plasmas that can cause charge to build up on spacecraft surfaces, resulting in high differential voltages and subsequent eleCtrostatic discharges. These discharges can damage avionics and/or scientific instruments on spacecraft. SURFSat will take in-situ measurements of the ground current waveforms from chosen common spacecraft dielectric material samples, measure the spacecraft and material potentials, and will use a Langmuir probe system to measure the ambient plasma environment. The sample materials will span a range of resistivities that will be chosen both for relevance and in order to maximize scientific return. Comparison of on-orbit ESD measurements with completed and ongoing plasma chamber charging experiments will be used to validate current plasma charging test methods. These experiments will be used to develop design criteria, and help avoid potentially disastrous discharging on spacecraft. CONOPS: Upon deployment from the PPOD, SURFS at will power up and initially enter a charging phase. It will then deploy two Langmuir Probe booms and begin collecting data. Data collection consists of voltage and current measurements from the dielectric surfaces on the experiment, and measurements from the dielectric probe. Langmuir probe and surface voltage measurements will be stored continuously during operation, but high data rate current data is recorded in a circular buffer, and only stored in long-term 12

memory if triggered by an an on-orbit ESD event. Data is stored onboard the computer until downlinked. Materials: The primary CubeSat structure is made of 6061 Aluminum. In addition to the solar cells on the outside of the spacecraft, the sample materials are made of aluminum substrates with aerospace industry standard paints and coatings. Other than that, the CubeSat contains all standard commercial off the shelf (COTS) materials, electrical components, and PCBs. Hazards: There are no pressure vessels, propulsion systems, hazardous or exotic materials on the SURFSat CubeSat Batteries: We use standard PCB material and electronics components. The solar cells are 23% Spectrolab CICs. The electrical power storage system consists of common Lithium Iron Phosphate (LFP) batteries with over-charge/current protection circuitry (UN38.3 passed). 13

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-18 CubeSat mission therefore this section is not applicable. 14

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 ElaN a-18 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)) Assessment of spacecraft compliance with Requirements 4.4-1 through 4.4-4 shows that with a maximum CubeSat lifetime of 4.4 years maximum the ElaNa-18 CubeSat is compliant. 15

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. The largest mean cross sectional area (CSA) among the three CubeSats is that of the ELFIN CubeSat with deployable extended (2x long antennas, 2x short antennas, Tuna Can, Stacer Boom and Sensor. : Figure 5: ELFIN Deployed Configuration 'f. Surface Area [2 * (w * l) + 4 * (w *h)] Mean CSA = = ---------- 4 4 Equation 1: Mean Cross Sectional Area for Convex Objects (Amax + A1 + A1) MeanCSA = 2 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 ELFIN (3.26 kg) orbit at deployment is 476 km apogee altitude by 450 km perigee altitude, with an inclination of 93 degrees. With an area to mass ratio of 0.019 m2/kg, DAS yields 4.4 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 lifetime ElaNa-18 CubeSats see an average of 0.00000 probability of collision. All CubeSats on ElaNa-18 were calculated to have a probability of collision of 0.00000. Table 4 below provides complete results. 16

a

Table 3: CubeSat Orbital Lifetime & Collision Probability ELFIN/ELFIN— CubeSat Dave S{ar SURFSat Mass (kg) 1.33 3.26 .895 Mean C/S Area (m42) 0.016 0.036 0278 § Area—to Mass (m"2/kg) 0.012 0.011 0.031 g Orbital Lifetime (yrs) 3.9 4.4 3.1 Probability of collision (10"X) 0.00000 0.00000 0.00000 3 Mean C/S Area (m4‘2) 0.062 qo>' Area—to Mass (m‘~2/kg) 0.019 §- Orbital Lifetime (yrs) 3.9 Probability of collision (10"X) 0.00000 Solar Flux Table Dated 8/4/2017 Sensitive But Unclassified (SBU)

The probability of any ElaNa-18 spacecraft collision with debris and meteoroids greater than 10 em 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-18 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-18 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 postrnission 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 SurfSat in its stowed configuration as the worst case. The area-to-mass is calculated for is as follows: Equation 3: Area to Mass 0.036 m 2 m2 3.26kg = .0.011-kg ELFIN and ELFIN-Star have 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: 476 km maximum apogee 450 km maximum perigee altitudes with an inclination of 93 degrees at deployment no earlier than November 2018 An area to mass ratio of 0.011 m 2/kg for the ELFIN/ELFIN-Star CubeSats was imputed. DAS 2.1.1 yields a 4.4 years orbit lifetime for ELFIN or ELFIN-Star 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. Sensitive But Unclassified (SBU)

Section 7: Assessment of Spacecraft Reentry Hazards A detailed assessment of the components to be flown on ElaNa—18 was performed. The assessment used DAS 2.0, a conservative tool used by the NA¥ASA 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 posses the same negligible risk as stainless steel components. See Table 4 and Table 4. Table 4: ELaNa—18 High Melting Temperature Material Analysis £4 HighTemp AVF q. ; j —,_— Demise Alt ‘Cu,ch:_n i Component Material Mass (g) (km) DAVE Antenna Wire Nickel Titanium 2.5 0 0 Tungsten DAVE Crystalline Powder Tungsten 20 0 0 ELFIN Back Wall Tantalum 19.35 0 13 ELFIN Side Wall (outer) Tantalum 11.91 0 10 Side Wall ELFIN (top&bot) Tantalum 16 0 13 ELEFIN Side Wall (inner) Tantalum 4.59 0 : ELFIN E Front Tantalum 16.73 0 9 Auxiliary Shield T ELFIN 1 Tantalum 7.93 0 6 Auxiliary Shield G ELFIN 1 Tantalum 8.98 0 6 Auxiliary Shield T ELFIN 2 Tantalum 6.44 0 4 Auxiliary Shield G ELFIN 2 | Tantalum 7.A7 0 4 * S—Band Radio assembly was modeled as all Stainless Steel, which is conservative. It is likely that less than % of the mass is actually stainless steel. 20

ELFIN Auxiliary Shield G 3 Tantalum 6.4 /0 s |w m u ELFIN Auxiliary Shield T 4 Tantalum 5.04 cJo|S ELFIN Auxiliary Shield G 4 Tantalum 5.26 ELFIN Back Wall Tantalum 19.35 5 ELFIN Side Wall Tantalum 6.03 o0 Un ELFIN Side Wall (Outer) Tantalum 4.21 w ELFIN Side Wall (Inner) Tantalum 1.7 °Sss |)+— ELFIN Mag Stage Front Tantalum 10.98 ta ELFIN Cone Wall Tantalum 7.21 2)}0 N ELFIN Auxiliary Shield M Tantalum 0.57 O ELFIN Payload Rods #4 Titanium Rod 1 8|00 0| ELFIN Auxiliary Shield T 3 Tantalum 5.69 w All components have less than 15J of energy upon reentry. As a result probability of Human Casualty is not calculated, resulting in automatic compliance with the 1:10,000 probability of Human Casualty Requirement 4.7—1. All CubeSats launching under the ElaNa—18 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. 21

Section 8: Assessment for Tether Missions ElaN a-18 CubeSats will not be deploying any tethers. ElaNa-18 CubeSats satisfy Section 8's requirement 4.8-1. 22

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 321-867-2098. /original signed by/ Yusef Johnson Flight Design Analyst a.i. solutions/KSC/AIS2 cc: V A-H/Mr. Carney V A-Hl/Mr. Beaver V A-Hl/Mr. Haddox VA -C2/Mr. Hall SA-D2/Mr. Frattin SA-D2/Mr. Hale SA-D2/Mr. Henry Analex-3/Mr. Davis Analex-22/Ms. Ramos 23

Appendix Index: Appendix A. ElaNa-18 Component List by CubeSat: DAVE Appendix B. ElaNa-18 Component List by CubeSat: ELFIN/ELFIN-Star Appendix C. ElaNa-18 Component List by CubeSat: SurfSat 24

Appendix A. ELaNa—18 Component List by CubeSat: DAVE § : Mass _ y CUBESAT . Name Qty Material —| Body Type| —(g) | mfl)«' 65 — eA (A ati | (W)‘ in ,‘(‘m;'_. x DAVE DAVE 1 Various Box 1.4 100 y DAVE CubeSat Structure 1 Aluminum 6061 Box 535 100 100 113.5 No — Demise DAVE Antenna Route 1 Delrin Square 7 65 65 3.5 No — Demise DAVE Antenna Wite 2 Nickel Titanium (NiTi) Rectangular 2.3 0.3 160 0.5 Yes 1400 c:;gyi?&w.;.t:bg$ DAVE Solar Cells 10 Eglass Rectangular 2.2512 0.5 68 40 No Demise DAVE Side Panels hy FR4 Multilayer PCB Rectangular 35 1.3 83 72 No = Demise DAVE Z—Panels 1 FR4 Multilayer PCB Square 45 1.5 100 100 No — Demise DAVE Cavity Caps 3 316 Stainless Stee| Box —10.5 20 13 13 Yes: 1400, Demise payg CemmicNcstoedidc Actuators ; Lead Zirconate Titanate Box 3.5 2.54 4445 12.7 No — Demise e esfi 2w fTengsten Powdet 20 ie 2 i Yes x2 |fi:fi?cfigt% $ DAVE SMA Actuators Boards 4 Nickel Titaninm {NiTi) Wire 0.5 0.05 100 N/A Yes 1400 Demise _ DAVE SMA Actuators wire 4 FR4 Multilayer PCB Rectangular 22 1.524 68.707 24.257 No — Demise DAVE Torque Shaft 1 Aluminum 6061 Cylindrical 3 4 62 No — Demise DAVE Locking springs 3 302 Stainless Cylingrical 3 69 10 — Yes 1500 Demise DAVE Sep/Actuating Switches 5 Plastic (PBT) Rectangular 2 6 8 7 No — Demise DAVE Batteries 2 Lithium Ion Cylindrical 90.7 26.3 65.8 — No — Demise DAVE Payload Board 2 FR4 Multilayer PCB Board 33 1.5 83 83 No — Demise DAVE Sensor Board 3 FR4 Multilayer PCB Board 3 1.5 32 32 No — Demise DAVE Comm Board 1 FR4 Multilayer PCB Board 12 1.5 83 36 No — Demise DAVE Breakout Board 1 FR4 Multilayer PCB Board 12 1.5 83 36 No — Demise DAVE C&DH Board 1 FR4 Multilayer PCB Board 30 1.5 83 83 No — Demise DAVE Fasteners 1 18—8 Stainless Screw 35 22 Various > Yes 1500 Demise DAVE Staking Compound 1 3M Scotch Weld 2216 Rectangular 15 — — = No — Demise L_’DAVE O_ Heat Shrink 1 RNF—100 Polyolefin Heat Shrink Tube 0 = — No 5 Demise DAVE Kapton Tape 1 Kapton Tape Tape 0 Various Various 0.05 No — Demise Sensitive But Unclassified (SBU)

Appendlx B. ElaNa—18 Component List by CubeSat: ELFIN/ELFIN—Star f : —| Body _| Mass t Diameter/ _ |. itapytsean—itacers"=t: 5J*Typi smrg)-*"»w;d&cm)w \_(m ELFIN 1 Box — Chassis Rail (+x,+y) 1 Aluminum 6061—T6 Bar 48.94 7 18.8 322.38 No — Demise Chassis Rail (—x,+y) 1 Aluminum 6061—T6 Bar 50.79 7 18.74 322.38 No — Demise Chassis Rail (+x,—y) 1 Aluminum 6061—T6 Bar 51.06 7 18.8 322.38 No — Demise Chassis Rail (—x,—y) 1 Aluminum 6061—T6 Bar 53.52 7 18.8 322.38 No — Demise Top Hat (—Z) 1 Aluminum 6061—T6 Block 55.179 100 100 24.3 No — Demise Top Hat (+2) 1 Aluminum 6061—T6 Block 100.97 100 100 24.3 No — Demise Tuna Can (+ Unit) 1 Windform LX2.0 Cylinder 48. 61.01 — 30 No — Demise Stacer Boom 1 Wrought Copper Rod — 29 750 ~ Yes 1085 Demise Stacer Tip Piece 2 Peek Block 4.6 5 20.08 49.82 No — Demise Mag Sensor 1 6061—T6 A, Copper, ferrite, NdFeB Box = # > No — Demise Mag Cable 1 6061—T6 A, Copper Cable — — — . No = Demise Antenna (long) 2 BeCu / Fiber Glass Thin sheet 6.9 13.8 609.6 — No — Demise Antenna (short) 2 BeCu / Fiber Glass Thin sheet 2.91 13.8 228.6 ~ No — Demise (+y — long) Solar Panel 1 FR4 PCB 48 1.65 82 146.33 No — Demise (+y — short) Solar Panel 1 FR4 PCB 38 1.65 82 112.95 No — Demise (+y) Solar Cell 4 GalnP2/GaAs/Ge Sheet 2.54 39.3 69.5 — No — Demise (—y) Solar Panel 1 FR4 PCB 111 1.65 82 329.29 No — Demise (—y) Solar Cell 6 GalnP2/GaAs/Ge Sheet 2.54 39.3 69.5 — No — Demise (+x) Solar Panel 1 FR4 PCB 112 1.65 82 329.29 No Demise (+x) Solar Cell 6 GalnP2/GaAs/Ge Sheet 2.54 39.3 69.5 — No — Demise (—x) Solar Panel 1 FR4 PCB 11 1.65 82 329.29 No — Demise (—x) Solar Cell 4 GalnP2/GaAs/Ge Sheet 2.54 39.3 69.5 — No — Demise (+z) Solar Panel 1 FR4 PCB 19 1.65 98.98 61.9 No — Demise (—z) Solar Panel 1 FR4 PCB 32 1.65 97.97 97.97 No — Demise Fasteners 48 Brass Rod 0.25 — — — No — Demise Shield Insert 1 Aluminum 6061—T6 Block 6.29 23.3172 19.8628 12.5222 No — Demise Aluminum Shield 1 Aluminum 6061—T6 Block 71.78 39.0144 33.8328 39.0144 No — Demise Back Wall 1 Tantalum Block 19.35 20.94992 459994 20.94992 Yes 2980 Survives — See Table 4 Side Wall (outer) 1 Tantalum Block L1.91 16.74876 2.99974 14.65072 Yes 2980 Survives — See Table 4 Side Wall (top&bot) #4 Tantalum Block 16 16.74876 2.99974 20.94992 Yes 2980 Survives — See Table 4 Side Wall (inner) 2 Tantalum Block 4.59 16.74876 54991 2.99974 Yes 2980 Survives — See Table 4 Spacer 1 Aluminum 6061—T6 Block 0.4 12.90066 0.89408 12.90066 No — Demise Insulator Side 1 PEEK Block 0.19 17.74952 4.4704 6.55066 No — Demise Wave Spring Washer 1 Beryllium Copper UNS C17200 Block 0.052 4.18846 0.127 — No — Demise 26

Pentpsrn l se 00 WMarrdiap _ __ |—— Body— _| Mass(g) — Diameter/ — | Length | H l Fogh BEteve NC Chor o eu.. >|o)tout/) worment|.mant| rnln.|fls ELFIN 1 PEEK Block 0.19 12.90066 0.84328 1290066 No ELEIN Spacer MSD 1 PEEK Block 0.138 12.99972 1.80086 12.99972 No ELFIN Foil Frame Back 1 Aluminum 6061—T6 Block 0.19 14.69898 0.73406 14.69898 No ELFIN Lexan Foil 1 Aluminum 6061—T6 Sheet 0.01 14.50086 — 14.50086 No ELFIN Foil Frame Front 1 Aluminum 6061—T6 Block 0.11 14.69898 0.5588 14.69898 No — Demise ELFIN E Front 1 Tantalum Block 16.73 20.94992 5.174802 20.94992 Yes 2980 Survives — See Table 4 ELFIN E Aperture 1 1 Phosphor Bronze Block 4.536 21.7932 1.61036 21.7932 No — Demise ELFIN Aperture Frame 1 Aluminum 6061—T6 Block 69.08 39.0144 48.895 39.0144 No — Demise ELFIN Auxiliary Shield T 1 2 Tantalum Block 7.93 18.71726 2.49936 10.28954 Yes 2980 Survives — See Table 4 ELEIN Auxiliary Shield G 1 2 Tantalum Block 8.98 23.3553 3.18008 10.28954 Yes 2980 Survives — See Table 4 ELFIN E Aperture 2 1 Phosphor Bronze Block 5.8 25:8064 1.61036 25.8064 No — Demise _ ELFIN Auxiliary Shield T 2 2 Tantalum Block 6.44 21.0058 1.80086 10.28954 Yes 2980 Survives — See Table 4 ELEIN Auxiliary Shield G 2 2 Tantalum Block 747 25.6032 299974 10.28954 Yes 2980 Survives — See Table 4 ELFIN E Aperture 3 1 Phosphor Bronze Block 5.06 26.1112 1.61036 26.1112 No — Demise ELFIN Auxiliary Shield T 3 2 Tantalum Block 5.69 21.51126 145034 11.03884 Yes 2980 Survives — See Table 4 ELFIN Auxiliary Shield G 3 2 Tantalum. Block 6.4 25.8572 2.90068 11.03884 Yes 2980 Survives — See Table 4 ELFIN E Aperture 4 1 Phosphor Bronze Block 4.07 21.7932 1.61036 21.7932 No — Demise ELFIN Auxiliary Shield T 4 2 Tantalum ° Block 5.04 22.96668 1.19888 11.03884 Yes 2980 Survives — See Table 4 ELFIN Auxiliary Shield G 4 2 Tantalum Block 5.26 26.28646 2.3495 11.03884 Yes 2980 Survives — See Table 4 ELFIN E Aperture 5 1 Phosphor Bronze Block 746 32.166 1.5748 32.166 No = Demise ELFIN Sensor E 1 [;‘;ggfi’,g;ggfi;i? Block 3.63 12.94892 970788 1294892 No — Demise ELFIN Preamp Cover Top 1 Aluminum 6061—T6 Block 22.17 56.90 19.02 43.33 No — Demise ELFIN Preamp Cover Base 1 Aluminum 6061—T6 Block 15.15 56.90 7.62 43.33 No — Demise ELFIN Preamp Spacer 4 Aluminum 6061—T6 Cylinder 0.09 3.81 4.57 — No — Demise ELFIN Aluminum Shell I 1 Aluminum 6061—T6 Block 44.39 45.42 19.46 39.01 No — Demise ELFIN Mag Stage Frame 1 Aluminum 6061—T6 Block 48.55 39.01 25.27 39.01 No — Demise ELFIN Back Wall 1 Tantalum Block 19.35 20.95 4.60 20.95 Yes 2980 Survives — See Table 4 ELFIN Side Wall 2 Tantalum Block 6.03 20.95 6.20 3.00 Yes 2980 Survives — See Table 4 ELFIN Side Wall (Outer) 1 Tantalum Block 4.21 14.65 6.20 3.00 Yes 2980 Survives — See Table 4 ELFIN Side Wall (Inner) 2 Tantalum Block 1.7 5.50 6.20 3.00 Yes — 2980 Survives — See Table 4 ELFIN Insulator Side 2 PEEK Block 0.19 17.75 6.10 7.27 No — Demise ELFIN Spacer 1 Aluminum 6061—T6 Block 0.4 12.90 0.89 12.90 No — Demise ELFIN Wave Spring Washer 1 *sy0C Block 0.052 4.19 0.13 — No — Demise ELFIN Insulator Back 1 PEEK Block 0.19 12.90 0.84 12.90 No — Demise ELFIN Spacer MSX 1 PEEK: Block 0.03 12.95 0.26 12.95 No — Demise 27

im apesmuircs m § sp—gure ud usns Oy 2eo f $ ELFIN 1 Tantalum Block 10.98 20.95 2.10 ~ See Table 4 ELFIN Insulator Front 1 PEEK Block 0.08 12.95 0.85 Demise ELEFIN Cone Wall 4 Tantalum Block egral 18.45 14.84 7122 Yes 2980 Survives — See Table 4 ELFIN Small WSW 2 Beryllium Copper UNS €17200 Block 0.03 7.62 0.13 — No — Demise ELFIN RF Shield EFE 1 Aluminum 6061—T6 Block 3.72 7.92 36.02 9.86 No — Demise ELFIN REMice,0C 1 Aluminum 6061—T6 Block 118 127 36.02 9.86 No — Demise ELFIN I Aperture Frame 1 Aluminum 6061—T6 Block 27.66 36.58 30.02 36.58 No — Demise ELFIN hebptp? ustsner Widget ; Aluminum 6061—T6. Block 0.86 5.59 13.50 762 No s Demise ELEIN Yoke 4 Hi Perm 49 Annealed Block 0.9325 10.30 8.30 2.24 No — Demise ELEIN Spring Retainer 1 Aluminum 6061—T6 Block 0.89 22.80 8.30 2.35 No — Demise ELFIN I Aperture 1 1 Phosphor Bronze Block 0.6 8.80 1.61 6.33 No — Demise ELFIN Outside Magnet 4 SmCo 2: 17 Block 0.92 4.15 8.30 3.20 No — Demise ELFIN Auxiliary Shield M 2 Tantalum Block 0.57 6.55 3.50 1.70 Yes 2980 Survives — See Table 4 ELFIN Inside Magnet 2 SmCo 2:17 Block 1.84 8.30 3.20 8.30 No — Demise ELFIN Magnet Retainer 1 Aluminum 6061—T6 Block 1.87 20.50 8.30 8.10 No — Demise ELFIN Strawman Bridge 1 Aluminum 6061—T6 Block 1.546 25.40 7.94 4.95 No — Demise ELFIN I to E Standoff 1 Aluminum 6061—T6 Block 0.49 38.86 8.59 1.22 No — Demise ELEIN I Aperture 2 1 Phosphor Bronze Block 6.73 24.00 1.61 24.00 No — Demise ELFIN I Aperture 2 Spacer 1 6063—T6 Block 2.88 24.00 8.29 24.00 No — Demise ELFIN I Aperture 3 1 Phosphor Bronze Block 6.01 26.00 1.61 26.00 No = Demise ELFIN I Aperture 3 Spacer 1 6063—T6 Block 3.15 ©26.00 8.29 26.00 No — Demise ELFIN I Aperture 4 1 Phosphor Bronze Block 6.88 31.00 1.61 31.00 No 2 Demise ELFIN I Aperture 4 Spacer 1 6063—T6 Block 3.61 31.00 8.29 31.00 No — Demise ELFIN 1 Aperture 5 1 Phosphor Bronze Block 7.61 36.60 1.60 36.60 No = Demise ELFIN SensorI 1 onmoonnnictoneg: Block 1.03 13.00 2.10 13.00 No — Demise ELFIN Stacer Can 1 Aluminum 6061—T6 Box 560 76.00 83.00 101.35 No — Demise ELEIN Payload Rods 4 #4 Titanium Threaded Rod Rod 1 2.85 3.5 — Yes 1650 Demise ELFIN EPD Digital 1 Board 1 FR4 PCB 58 1.57 $3.22 86.61 No — Demise ELFIN EPD Digital 2 Board 1 FR4 PCB 58 1.57 93.22 86.61 No — Demise rippy BPD Extended Froot ; FR4 PoB 10.6 49.91 69.6 10.77 No — Demise ELFIN EPD preamp 1 FR4 PCB 24 1.58 46.025 50.06 No — Demise ELFIN IDPU 1 FR4 PCB 62 1.57 93.23 86.61 No Demise ELFIN SIPS 1 FR4 PCB 31.13 1.37 90.68 86.61 No — Demise 28

ELFIN FGE (FGM Mechoa:sPesas * FR4, various 85.05 92.66 92.28 23.69 No Demise ELEIN FGE brace 1 Aluminum 6061—T6 Box 46.97 10.16 §7.02 §7.17 No Domise ———__——— & Ts _ & is ~aking 2 otal) _ C t FGE strap . 1 Peek Box 4.27 5.84 78.26 10.16 No Demise ELFIN T°‘q“sel’)Ll** Peek 30.9 95.15 241.3 7.49 No Demise ELEIN hiuon HTCCA Wire 43.7 — — « No Demise ELFIN T"rq“;;o‘f,‘l’“ —~A Peek 31.9 85.73 243.84 16.64 No Demise ELEN Terqueo ~ * HTCCA Wire 49.2 — — - No Demise ELFIN Battery Holders 2 Peek Block 26 82 83.83 8.53 No Demise ELFIN Batteries 4 Molicel ICR18650J Lithium—ion |_Cylinder 46.39 18.4 65.4 — No Demise ELEIN Battery Arcs 4 Aluminum 6061—T6 Block 3.61 16.71 5.74 28.35 No Demise ELEN SBPCB 2 ER4 PCB 28.78 55.83 55.88 16.16 No Demise ELEIN FCPCB 1 FRa PCB 19 55.88 55.88 16.16 No Demise ELEIN LETCI 1 FR4 PeB 174 55.88 55.88 16.16 No Demise ELEIN LETC i FRa PCB 15.63 55.88 55.88 16.16 No Demise ELFN ACB 1 Fra Pes 17.8 55.88 55.88 16.16 No Demise ELEFIN BETC 1 FRi PCB 40.44 55.88 55.88 16.16 No Demise ELFIN Radio 1 FRA/Aluminum PCB a8.5 is 82 82 No Demise 29

Appendix C. ElaNa-18 Component Listby CubeSat: SurfSat Mas!; (g) Diameter/ Length .High Melting Cl.JBESAT Nuroo Qt)' Mareriul Body Type (tetal) Width (nmll (nun) fleicbt (1D111) Temp Temp Survi'Qlbility SurfSat SurfSat 1 - - - - - - - - Demise SurfS at PanelAA 1 6061 Aluminum Plate 70.21 83 213 1.5 No - Demise SurfS at PanelBB 1 6061 Aluminum Plate 70.01 83 213 1.5 No - Demise SurfSat PanelCC I 6061 Aluminum Plate 70.21 83 213 1.5 No - Demise SurfSat Pane!DD I 6061 Aluminum Plate 70.01 83 213 1.5 No - Demise SurfSat Panel Bottom I 6061 Aluminum Plate 34.06 97 97 1.5 No - Demise SurfS at Panel Top I 6061 Aluminum Plate 34.06 97 97 1.5 No - Demise SurfS at Comer Bracket b 2 6061 Aluminum Rail 37.04 16.63 213 16.63 No - Demise - Demise · .. SurfS at Comer Brackefc 2 6061 Aluminum Rail 37.74 16.63 213 16.63 No SurfS at Comer Block A 4 6061 Aluminum Block 4.34 16.63 16.63 14.37 No - Demise I SurfSat Corner Block A2 2 6061 Aluminum Block 7.48 16.63 16.63 25.85 No - Demise Comer Block Separation Spring SurfSat 2 6061 Aluminum Block 3.98 16.63 16.63 14.37 No - Demise SurfSat 70cm Antenna 2 Steel Wire 1.4 1.2 162.14 - No - Demise SurfS at Antenna Hook 2 Aluminum Hook <I g each 10.16 17 6.36 No - Demise SurfS at Antenna Standoff 4 Brass Rod 9.02 4 .75 3.3 - No - Demise SurfSat Antenna Swing Assembly 2 PCB/Plastic Plate 4.5 16 23.17 17.1 No - Demise SurfSat Brass swing screw 2 Brass Rod I 4.76 17.46 - No - Demise SurfS at NiChrome Wire Mech Assembly 4 Teflon/Steel Plate 4.39 30 10 12.6 No - Demise SurfSat Langmuir Probe support I Steel Tape 15.11 12.7 216.74 25.4 No - Demise SurfSat Langmuir Probe cable l Coaxial cable Cable 2.25 2 .8 220 - No - Demise SurfS at Solar Panel (Side) 4 PCB/Glass Plate 27.98 82.55 95.25 2 No - Demise SurfSat Solar Panel (Top) 2 PCB/Glass Plate 30.13 93.98 93.98 2 No - Demise SurfSat Limit switch 2 Plastic Block I 5.08 12.7 10.2 No - Demise SurfS at Switch Plunger 2 Steel Cylinder <I g each 1.78 6.35 - No - Demise SurfSat Separation Spring 2 Stainless Steel Cylinder <I g each 3.45 11.31 - No - Demise SurfS at Mounting Plate 4 6061 Aluminum Plate 42 82.55 95.25 I No - Demise SurfSat Sample Plate I I 6061 Aluminum Plate 7.62 63.5 63.5 0.7 No - Demise SurfSat Paint sample I AZ-400-LSW paint <I g 63.5 63.5 0.6 No - Demise SurfS at Sample Plate 2 I 6061 Aluminum Plate 7.62 63.5 63.5 0.7 No - Demise SurfSat Paint sample I AZI-4020 paint - <lg 63.5 63.5 0.6 No - Demise SurfSat Sample Plate 3 1 6061 Aluminum Plate 7.62 63.5 63.5 0.7 No - Demise SurfS at Kapton Tape sample I Kapton Tape - <1 g 63.5 63.5 0.6 No - Demise SurfSat Sample Plate 4 I Anodized Aluminum Plate 7.62 63.5 63.5 I No - Demise SurfS at Permanent Magnet I Alnico Block 1.7 6.15 12.7 3.13 No - Demise 30

SurfSat Hysteresis Rod 2 Permalloy 80 Cylinder 0.618 1 90 — No Demise SurfSat Raspberry Pi CCDR 2 PCB Plate 70 87 125 14 No Demise SurfSat Picoscope Oscilloscope Board 1 PCB Plate 110 95.1 89.1 10.9 No Demise SurfSat Langmuir probe board 1 PCB Plate 30 125 104 22 No Demise SurfSat Electrometer board 1 PCB Plate 100 76.7 80.4 12.3 No Demise SurfSat AntennaDeployment and Link 1 PCB Plate 28.5 78.78 91.38 1.37 No Demise SurfSat Comm Board 2 PCB Plate 28.5 94 94 10 No Demise SurfSat Battery Board 1 PCB Plate 21.64 94 94 10 No Demise SurfSat Battery charge tracking board 1 PCB Plate 47.5 94 94 10 No Demise SurfSat C&DH Board 1 PCB Plate 13.29 94 94 10 No Demise SurfSat Electronics Bottom Mounting Plate 1 6061 Aluminum Plate 33.54 97 97 1.6 No Demise SurfSat Fastening screw 58 Steel Cylinder > & z — No Demise SurfSat Fastening screw 2 Steel Cylinder — — — — No Demise SurfSat Electronics board standoff 28 Steel Cylinder — z — > No Demise SurfSat Electronics board standoff 16 Steel Cylinder — — — No Demise SurfSat Limit switch bolt 1 2 Steel Cylinder s — — z No Demise SurfSat Limit switch bolt 2 2 Steel Cylinder — — — No Demise SurfSat Gecko Connector 6 PCB Plate = — — — No Demise SurfSat Coaxial cable 10 Copper alloy — — = — — No Demise 31


Document Created: 2018-05-30 12:44:08
Document Modified: 2018-05-30 12:44:08
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