ODAR

0341-EX-CN-2017 Text Documents

California Polytechnic State University

2017-05-03ELS_191468

ELVL-2017-0044744 April 20, 2017 (Rev1) Orbital Debris Assessment for The CubeSats on the Virgin Galactic LauncherOne /ELaNa-20 Mission per NASA-STD 8719.14A (FCC)

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National Aeronautics and Space Administration John F. Kennedy Space Center, Florida Kennedy Space Center, FL 32899 ELVL-2017-0044744 April 7, 2017 Reply to Attn of: VA-H1 TO: Justin Treptow LSP Mission Manager, NASA/KSC/VA-C FROM: Yusef Johnson, a.i. solutions/KSC/AIS2 SUBJECT: Orbital Debris Assessment Report (ODAR) for the ELaNa-20 Mission (FCC Rev 1) 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. VCLS Spacecraft to LauncherOne Interface Control Document (ICD), MA- 0002 Rev 4. Virgin Galactic 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 Rev 1 removes references to CNGB, AeroCube 12A/B, and SurfSat as they have been demanifested from the ELaNa-20 mission. The intent of this report is to satisfy the orbital debris requirements listed in ref. (a) for the ELaNa-20 auxiliary mission launching on the Virgin Galactic LauncherOne vehicle. 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-20 payload mission to be flown using Virgin Galactic’s LauncherOne. The 13 CubeSats comprising the ELaNa-20 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 7.2 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 under ELaNa-20 mission 4

Section 1: Program Management and Mission Overview The ELaNa-20 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: ALBus: Kathryn Shaw, Project Manager CACTUS-1: Sandy Antunes, Technical Point-of Contact CAPE 3: Jacob Desotels, Project Manager ExoCube: Alex Saunders, Technical Point of Contact INCA: Steven Stochaj, Principal Investigator MicroMAS2b: William Blackwell, Principal Investigator MiTEE: Brian Gilchrist, Principal Investigator PICS: David Long, Principal Investigator PolarCube: Albin Gasiewski, Principal Investigator Q-PACE: Joshua Colwell, Principal Investigator RadFXSat-2: Robert Reed SHFT-2: Jim Lux (JPL), David Pfundstein, Technical SETA 5

Program Milestone Schedule Task Date CubeSat Selection 6/10/2016 Mission Readiness Review 8/1/2017 CubeSat Delivery to TriSept 11/9/2017 Launch 12/1/2017 Figure 1: Program Milestone Schedule The ELaNa-20 mission will be launched as payloads on the Virgin Galactic LauncherOne launch vehicle from Mojave, CA. The ELaNa-20 mission will deploy 13 pico-satellites (or CubeSats). Each CubeSat slotted position is identified in Table 2: ELaNa-20 CubeSats. The ELaNa-20 manifest includes: ALBus, Cactus-1, CAPE 3, ExoCube, INCA, MicroMAS2b, MiTEE, PICS, PolarCube, Q-PACE, RadFXSat-2, and SHFT-2. The current launch date is in December 1, 2017. The 17 CubeSats will be ejected from the FANTM-INVERSE carrier which is the vehicle’s main payload, placing the CubeSats in an orbit approximately 500 X 500 km at inclination of 90 deg. The CubeSats on this mission range in size from a 10 cm x 10 cm x 11 cm to 11.5 cm x 11.5 cm x 37.5 cm, with masses from about 1.3 kg to 5.1 kg, with a total mass of 55.29 km being manifested on this mission. The CubeSats have been designed and universities and government agencies and each have their own mission goals. 6

Section 2: Spacecraft Description There are 13 CubeSats flying on the ELaNa-20 Mission. Table 2: ELaNa-20 CubeSats outlines their generic attributes. Table 2: ELaNa-20 CubeSats CubeSat CubeSat CubeSat CubeSat size Masses Names Quantity (kg) CACTUS-1 1 3U (36.6 x 10.3 x 11 cm3) 2.8 ALBus 1 3U (34.05 x 11.6 x 11.6 cm3) 4.0 Cape-3 1 1U (11.35 x 10 x 10 cm3) 1.3 Q-PACE 1 3U (30 x 10 x 10 cm3) 4.2 MiTEE 1 3U (34 x 10 x 10 cm3) 4.0 RadFXSat-2 1 1U (11.35 x 11.1 x 11.1 cm3) 1.3 PICS 2 1U (11.2 x 11.2 x 11.2 cm3) 2.7 INCA 1 3U (37.5 x 11.5 x 11.5 cm3) 3.83 MicroMas-2b 1 3U (34.05 x 10 x 10 cm3) 4.5 EXOCUBE 1 3U (35.05 x 10 x 10 cm3) 3.2 PolarCube 1 3U (34 x 10.1 x 10.5 cm3) 3.9 SHFT-2 1 3U (34.05 x 10 x 10 cm3) 5.1 The following subsections contain descriptions of these 13 CubeSats. 7

CACTUS-1 – Capital Tech University – 3U Figure 1: CACTUS-1 Expanded View. Overview The overall goal of the CACTUS-1 mission is to profile and capture micrometeorites and micro-debris using aerogel in an effort to initiate the cleanup of LEO as well as provide a platform for a technology demonstration for an experimental communication and command subsystem. The CACTUS-1 flight system is a 3U CubeSat (roughly 10 x 11 x 36 cm3, 2.8 kg) that will operate in low Earth orbit. The payload consists of the main payload, a debris capture mechanism, the HERMES CPU and data modem, and imaging camera. CONOPS Upon deployment from the FANTM-Rail dispenser, CACTUS-1 will conduct one or more charge-up orbits. Once sufficient power is available, the CPU will power up, verify system status, and automatically activate the nichrome burn wires to release the dipole (tape measure) antenna. Within the first available contact passes with our primary ground station, we will request health-and-safety telemetry. The TRAPSat subsystem passively collects orbital debris; image data of the captured particles will be periodically requested via ground commands after initial health and safety telemetry is validated. The secondary Hermes payload will power up after at least 3 days of charging orbits to receive commands and send health and safety data via the Iridium network. 8

Materials The primary CubeSat structure is made of Aluminum 7075. It contains all standard commercial off the shelf (COTS) materials, electrical components, PCBs and solar cells Hazards CACTUS-1 contains no pressure vessels. The aerogel being used as a debris capture mechanism, could be considered an exotic material. This material is contained as two 51 x 51 x 13 mm3 volumes. There is also a small amount of aerogel being using as thermal blanketing. Power System/Batteries The electrical power storage system consists of common Lithium Ion (Li-ion) batteries with over-charge/current protection circuitry. The primary EPS is a direct energy transfer system using the solar array to produce 3.08W average. This is composed of (6) 1U and (2) 0.5U solar panels using Trisol 28% efficient GaAs triple junction solar cells, it utilizes (4) COTS 18650 3.7V 28090 mAhr Lithium Ion battery cells. The EPS drives the primary PiSat board, which acts as the distribution hub for the sensors and payloads. Nominal power usage is 1.77W with an additional +1.1W when transmitting. The Hermes experiment EPS consists of (4) 0.5U solar panels using Trisol GaAs 28% efficiency solar cells, and (3) COTS 18650 battery cells. To turn on the entire CubeSat, there are two power inhibit switches and 1 SW timer to ensure that the spacecraft is triggered on when launched from the dispenser. 9

ALBus – NASA Glenn Space Flight Center – 3U CubeSat Figure 2: ALBus Stowed View Figure 3: ALBus Expanded/Deployed View 10

Overview The Advanced Electrical Bus (ALBus) mission is a pathfinder engineering demonstration of a high power 3-U CubeSat. The primary objectives include demonstration of 100 W power distribution in the 3-U form factor and functional demonstration of shape memory alloy retention and release mechanisms for solar array deployment and power transfer. CONOPS Upon deployment from the CubeSat deployer, the ALBus CubeSat will power up and hold for the duration prescribed by the launch provider. Following the prescribed hold, ALBus will attempt deployment of the deployable solar arrays and antennas utilizing the shape memory alloy retention and release mechanism. Following these deployments, the CubeSat will begin beaconing in an attempt to establish communication with the ground network. Once communication is established, the ALBus will undergo a series of automated checkouts prior to moving into a stand-by mode. A series of permissives will be checked on-board and the system will schedule its first test to demonstrate the key objective, which is delivery of 100 W of electrical power to a passive load bank. The 100 W demonstration will run until prescribed temperature limits are reached on control thermocouple or another system shutdown parameter is activated. A series of tests will follow varying length, duration, system initial conditions and environmental conditions to characterize the performance of the system. Materials The primary CubeSat structure is made of Aluminum. It contains standard commercial off the shelf (COTS) materials, electrical components, PCBs and solar cells. The retention and release mechanism and hinge assembly for the deployable solar arrays are designed and built in house and primarily consist of off the shelf materials. The shape memory alloys used for actuation of the solar array deployment are a customized alloy of Nickel-Titanium, made at NASA GRC. Hazards There are no pressure vessels, hazardous or exotic materials. Batteries The electrical power storage system consists of common COTS Li-Ion batteries from GOM Space with over-charge/current protection circuitry. 11

CAPE3 –University of Louisiana – 1U Figure 4: CAPE3 Expanded View Overview CAPE 3’s primary mission is to create a CubeSat, improving upon the CAPE program’s previous satellites, with the intent of generating grade school interest and involvement in aerospace. This includes the use of portable smartphone-controlled ground stations as an educational outreach. The secondary mission includes experimental radiation detection through triboluminescent crystals, as well as taking pictures of the earth utilizing active attitude control. CONOPS CAPE-3 will begin in BLUE mode upon deployment from the PPOD, and for 30 minutes after deployment will remain on, but inactive. Following the 30 minutes, the satellite will begin attempts to deploy antennas. Upon successful deployment of antennas, the satellite will enter PINK mode. The satellite will then send telemetry beacons until a ground station receives a successful transmission, and is able to activate the satellite into normal operations. From this point, the satellite will enter one of three modes (GREEN, 12

ORANGE, or RED) autonomously based on several factors from the satellite, such as temperature, power levels, and others. Material The primary CubeSat structure will be composed of Aluminum 6061 and stainless steel. The antenna deployment mechanism will be made of Delrin material. The scientific payload will consist of triboluminescent crystals. The rest of the satellite will contain COTS materials, electrical components, PCBs, and solar cells. There are no pressure vessels or hazardous materials on the satellite. The solar panel cover glass will be coated with ITO. A boom constructed from LoadPath P/N 1106- 03TS-0050-180-041-005 polymer will be used. The communications and science antennas will be constructed from steel measuring tape. Hazards There are no pressure vessels, hazardous, or exotic materials. Power Systems/Hazards The electrical power storage system consists of the Clyde Space Third Generation 10Whr Lithium Polymer battery. The battery has over-charge, over-current, over-voltage, and under-voltage protection circuitry. The battery is qualified to NASA standards EP-Wi- 032. 13

Q-PACE – University of Central Florida – 3U Figure 5: Q-PACE Expanded View Overview Q-PACE is a planetary mission to the orbital free-fall environment necessary for long duration microgravity experiments to study collisions in the early protoplanetary disk. The CubeSat will observe low-velocity collisions between cm-scale and smaller particles and the formation of clusters of particles. The experiments run during the 3 years mission time will make it possible to determine whether collisional growth can proceed into this size range, confronting the decades-old question of how bodies grow past the meter-size barrier into planetesimals that can go on to become planets through gravitational accretion. CONOPS After deployment, Q-PACE will start its on-orbit experiment plan consisting of 5-minute experiment runs. During each experiment run, the experiment test cell (ETC) containing the dust particles will be agitated in a sequence of high and low frequencies, while video of the colliding particles will be recorded by the on-board camera. After each experiment 14

run, the video data will be processed on board and downlinked for analysis. During the 3- year mission time, four different particle combinations will be studied amongst cm-, mm- and 100 µm-sized particles Materials The primary CubeSat structure is made of Aluminum 6061-T6. The experiment cell is made of Aluminum 6061 and includes two transparent fused quartz plates to allow for the particle observation. The particles contained in the experiment cell will be composed of SiO2 either in the form of glass beads or as dust particles, brass and meteoritic material. The Q-PACE camera is a GoPro Hero3+ black edition. We use standard PCB material and electronics components. Hazards There are no pressure vessels, hazardous or exotic materials. Batteries The solar cells are 23% Spectrolab CICs. The electrical power storage system consists of common LFP (Lithium Iron Phosphate) batteries with over-charge/current protection circuitry (UN38.3 passed). 15

MiTEE– University of Michigan – 3U Langmuir Battery PCB Probe PCB CDH Main Langmuir Board Constant Current Probe Power Supply End- Body Radio PCB CubeSat Structure Antenna EPS/Plasma Magnetorquers PCB High Voltage Power Supply Figure 7: MiTEE Expanded View Overview MiTEE will demonstrate the use of CubeSat capabilities to deploy a Pico/Femto Satellite- tether system (satellite mass up to 200 g). The mission will allow students to work on a real-world, research driven, mission to assess the key dynamics and electrodynamic fundamentals of a very short tether system for pico/femto satellites. The central technical questions motivating the student mission include: (I) (Primary) Can the miniature tether provide stable, practical thrust for drag make-up and basic propulsion for “smart phone” sized pico/femtosatellites? (II) (Secondary) Can the miniature tether and pico/femtosatellite system serve in other roles. This could include, among others, that the miniature tether can be the basis for a useful, enhanced antenna for communication with the ground. CONOPS Upon deployment from the PPOD, MiTEE will wait around 15 minutes before powering up and beginning a subsystem and instrument performance assessment. After this check out is complete, MiTEE will initiate the antenna deployment, Langmuir probe deployment, and de-tumble procedure. We will then perform a check the performance of the Langmuir probe and antenna array, and begin transmission and plasma measurement as soon as possible. It is anticipated that after 2 days, MiTEE will be rotating less than 0.5 degrees per second. At this time, MiTEE can initiate the boom deployment procedure. A ~120 g end-body will deploy 100 cm by means of a semi-rigid boom. After a payload instrument checkout, MiTEE will proceed to begin the primary science mission by biasing the end-body, activating the thermionic cathode, and measuring the current flow through controlled voltage sweeps. 16

Materials The primary material of the structure is 6061 Aluminum. It contains commercial off the shelf components, electrical components, science instruments, PCBs, and solar cells Hazards There are no pressure vessels, hazardous or exotic materials. Batteries The electrical power storage system consists of common lithium-ion batteries with over- charge/current protection circuitry. 17

RadFXSat 2– Vanderbilt University – 1U Figure 8: RadFXSat-2 Expanded/Deployed View Overview RadFxSat-2 is a 1U CubeSat designed by Vanderbilt University and AMSAT. It is controlled by AMSAT. Its mission has two objectives: collect data on the effects of space radiation on SRAMs designed using FinFETs for the purpose of validating single-event error rate predictions, and two-way linear transponder communications in the amateur radio band. The experiment consists of four boards: VUC, LEP, LEPF, and REM. The linear transponder (radio) consists of two boards: RX/TX and ICR. CONOPS Upon deployment from the PPOD, MiTEE will wait around 15 minutes before powering up and beginning a subsystem and instrument performance assessment. After this check out is complete, MiTEE will initiate the antenna deployment, Langmuir probe deployment, and de-tumble procedure. We will then perform a check the performance of the Langmuir probe and antenna array, and begin transmission and plasma measurement as soon as possible. It is anticipated that after 2 days, MiTEE will be rotating less than 0.5 18

degrees per second. At this time, MiTEE can initiate the boom deployment procedure. A ~120 g end-body will deploy 100 cm by means of a semi-rigid boom. After a payload instrument checkout, MiTEE will proceed to begin the primary science mission by biasing the end-body, activating the thermionic cathode, and measuring the current flow through controlled voltage sweeps. Materials The primary material of the structure is 6061 Aluminum. It contains commercial off the shelf components, electrical components, science instruments, PCBs, and solar cells Hazards There are no pressure vessels, hazardous or exotic materials. Batteries The electrical power storage system consists of common lithium-ion batteries with over- charge/current protection circuitry. 19

PICS– University of Michigan – 1U Figure 9: ALBus Stowed/Deployed View Overview The primary objective of PICS is to demonstrate inspection of the parent vehicle by a passive, fly-away probe. PICS will evaluate structural condition, validate state vector models, identify potential separation debris, and confirm separation. CONOPS After deployment, they rapidly bootup and image the launch vehicle. Out of view of the upper stage, each will characterize the other’s tumble using the cameras. At 30 mins, the cameras will be used to observe each PIC’s own antenna deployment. At 45 mins, the system will downlink primary mission data, including telemetry used for evaluating system performance. Materials The primary CubeSat structure is made of 6061 Aluminum. It contains all standard commercial off the shelf (COTS) materials, electrical components, PCBs and solar cells. Hazards There are no pressure vessels, hazardous or exotic materials. Batteries The electrical power storage system consists of common LiPo batteries with over- charge/current protection circuitry. They are not UL listed. 20

INCA– New Mexico State University – 3U Figure 10: ALBus Expanded/Deployed View Overview The Ionospheric Neutron Content Analyzer (INCA) is a 3U CubeSat being built by New Mexico State University carrying a scintillator (silicon photomultiplier-based neutron detector) being built by NASA’s Goddard Space Flight Center. The INCA mission will, for the first time, study the latitude and time dependencies of the neutron spectrum in low Earth orbit (LEO). INCA will focus on albedo neutrons; however, the instrumentation will also be sensitive to solar neutrons. CONOPS Upon deployment from the launch vehicle, INCA will enter a 45 min sleep period. Once the sleep period is complete, it will deploy its antenna and solar panels. After deployment, the vehicle will begin science operations, and begin the de-tumbling sequence. Once the vehicle is detumbled, it will be spin stabilized about the Z-axis, with the +Z axis pointed towards the sun. Materials The primary material of the structure is Aluminum 7075. It contains standard commercial off the shelf components, electrical components, science instruments, PCBs, and solar cells. 21

Hazards There are no pressure vessels, hazardous or exotic materials. Batteries The electrical power storage system consists of common lithium-ion batteries with over- charge/current protection circuitry. 22

MicroMAS-2b – Massachusetts Institute of Technology – 3U Figure 10: MicroMAS-2b Deployed View Overview The Micro-sized Microwave Atmospheric Satellite (MicroMAS-2b) will validate new ultra-compact and low-power technology for CubeSat-sized scanning microwave radiometer including 1) multiband (W/F band 89 GHz – 120 GHz and G band 175 GHz – 207 GHz) total power radiometer payload with 2) cross track scanner assembly in a dual- spinning local vertical local horizontal (LVLH) stabilized 2U CubeSat spacecraft. These core technology elements will directly improve atmospheric science measurements by demonstrating high-fidelity, well-calibrated radiometric sensing from very small satellite platforms, thereby enabling new architectural approaches for atmospheric monitoring. CONOPS After launch and deployment, MicroMAS2b will be power inhibited for 45 minutes, then execute autonomous solar panel and communications antenna deployment for 4 minutes and reach safe mode waiting for ground command. It will be then commanded through a progression of detumble and slew attitude control states to reach LVLH stabilized attitude. While in a stabilized attitude, the spacecraft will collect payload radiometer data while scanning over +/- 56o cross-track from nadir. The payload will cycle between data collection and standby power modes at 50% duty cycle to manage power consumption. In order to prevent EMI into the sensitive payload microwave channels, data will not be collected while the high power downlink radio is operating for nominal 8 minute pass near the ground station. Materials MicroMAS2b is a 3U CubeSat consisting of a 2U PC104 avionics stack/ADCS module connected to a 1U radiometer payload via a brushless scanner assembly and slip ring. It contains all standard electrical components, PCBs and solar cells. The structural housing consists of four Al 6061 side panels and four Al 7075 rails confirming to the PPOD 3U 23

dimensional standards. Total mass is approximately 4.5 kg. There are no hazardous or exotic materials. Microwave electronics components are packaged in small (approx. 1-3 cu in) soldered unsealed waveguide housings. A thermal switch is packaged in a hermetically sealed stainless steel housing filled with dry nitrogen, tested to MIL-STD- 202. Hazards There are hazardous or exotic materials. A thermal switch is packaged in a hermetically sealed stainless steel housing filled with dry nitrogen, tested to MIL-STD-202. Batteries The electrical power storage system consists of common ClydeSpace Ltd Lithium ion polymer chemistry batteries with over-charge/current protection circuitry and battery control with triple safety inhibits suitable for International Space Station manned spaceflight as per NASA JSC 20793 Rev B 24

EXOCUBE – California Polytechnical Univeristy – 3U Figure 11: EXOCUBE Stowed/Deployed View Overview ExoCube2 will measure in-situ densities of selected ions and neutrals in the upper ionosphere and lower exosphere. These measurements will be used to characterize the climatology of the upper ionospheric and lower exospheric composition. They will help improve current empirical and climatological atmospheric models. The densities are measured using a gated time-of-flight mass spectrometer designed and built by NASA Goddard. A satellite bus to house the mass spectrometer was designed and built by Cal Poly. The bus includes an environmental chamber to protect the instrument and a 3-axis attitude determination control system (ADCS) that will maintain stable Nadir and Ram pointing necessary for accurate data measurement. The ADCS uses gravity gradient stabilization with deployable booms and a momentum wheel to stabilize the roll axis and Ram pointing. The mission life is expected to be 6 months to a year. CONOPS After deployment from the P-POD, the satellite will power on. Approximately 40 minutes later, antenna deployment will occur. Upon verification of antenna deployment, the beacon will be activated and the satellite will acquire with Cal Poly’s ground station. The ground station will uplink the current time and TLEs. The detumble process will then begin. Magnetometers and solar sensors will determine orientation and magnetorquers will stabilize ExoCube2. Onboard GPS will acquire lock for position and time keeping. Once spin rates have been reduced, the PD controller and Kalman Filter will be activated and the booms will deploy. The camera on the –Z panel will take pictures to verify boom deployment. Once Nadir pointing is acquired, the momentum wheel will begin spinning 25

up. Around 4 hours later, the wheel will be at full speed and the satellite will reacquire Nadir and Ram pointing. The camera on the –Z panel will take pictures to verify the satellite is pointed in the correct direction. Once the correct orientation is verified, the science payload will be powered on. The mass spectrometer will take data over the Earth’s poles and several ground stations throughout the mission. Every pass over a ground station (approx. every 12 hours), the satellite will downlink data from the instrument and uplink the current time for the clock and new TLEs to maintain accuracy of the orbital propagator. Materials The structure is made entirely of 6061-T6 Aluminum. The deployable booms are made of FR4, the tips are constructed from brass. The antennas are made of NiTi and Delrin. The satellite contains mostly standard commercial off the shelf materials, electrical components, PCBs, and solar cells. The cathode inside of the instrument is made of tungsten, but the tungsten is small enough that it burns up during re-entry. Hazards There are no pressure vessels, hazardous materials, or exotic materials. Batteries There are 4 1-cell batteries on the satellite. They are all Tenergy Li-Ion, 3.7 V 2600 mAh batteries. The UL listing number is MH48285. There is battery protection circuitry and over-charge protection circuitry. All batteries are connected in parallel. 26

PolarCube – Colorado Space Grant Consortium – 3U Figure 12: PolarCube Expanded View Overview The PolarCube mission will collect Earth surface and atmospheric temperature data using a passive microwave radiometer operating at the 118.7503 GHz O2 resonant frequency. To accomplish this, PolarCube is utilizing an existing 3U CubeSat bus, the Agile Low- cost Laboratory for Space Technology Acceleration and Research (ALL-STAR), designed and built entirely by students at COSGC. The objective is to collect brightness temperature spectra at high spatial resolution at a very low cost for remote sensing science and technology evaluation. CONOPS Upon deployment from the PPOD, PolarCube will power on EPS and begin a 60 minute software inhibit. After 60 minutes, EPS will trigger the frangibolt deployment and subsequently power on the ALL-STAR bus. PolarCube will then enter a bus commissioning phase. Once ground operators are satisfied with the bus operations, they will command the payload commissioning phase to begin. Once the payload has been commissioned, PolarCube will enter a minimum mission success phase where the payload will collect brightness temperature data over pre-determined orbit sectors, and will finally enter an open science collection phase until decommissioning and end of life operations. Materials 27

PolarCube’s primary structure is made of Aluminum 6061 with an anodized finish and Teflon coating on the rails. The system contains all standard commercial materials (IC’s), FR-4 PCB’s, brass RF components, and ITJ solar cells. Hazards There are no pressure vessels, hazardous, or exotic materials. Batteries The electrical power storage system consists of common lithium ion batteries with overcharge/current protection circuitry. UL Listing information is as follows MH48285. 28

SHFT-2 – DARPA – 3U Figure 15: SHFT-2 Expanded/Deployed View Overview The SHFT mission will collect radio frequency signals in the HF (5-30 MHz) band to study the galactic background emissions, the HF signals from Jupiter, and the signals from terrestrial transmitters after having passed through the earth’s ionosphere. The ionosphere changes its characteristics on a minute to minute basis, particularly changing between day and night, but also in response to geomagnetic phenomena and solar events. CONOPS After deployment from the PSC CSD, the SHFT Cubesat will power up, deploy the solar panels and UHF telecom antennas, establish positive power state and wait for ground communications. Upon ground command, the HF antenna (4 tape measure type antenna, each 3 meters long) will be deployed. Over the next 3 months, the spacecraft will periodically record signals in the 5-30 MHz band for 10 minutes, then will transmit the recorded signals to the ground station on subsequent passes for analysis. Materials The primary CubeSat structure is made of Aluminum. It contains all standard commercial off the shelf (COTS) materials, electrical components, PCBs and solar cells. The deployable 3 meter HF antenna elements are made of cold rolled steel (i.e. they are standard construction tape measures). 29

Hazards There are no pressure vessels, hazardous or exotic materials. Batteries The electrical power storage system consists of common Lithium ion batteries with over- charge/current protection circuitry in the spacecraft power controller. 30

CubeSat Measurement Specifications Figure 16: 1U CubeSat Specification Figure 17: 3U CubeSat Specification 31

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-20 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-20 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)) The whole manifest of ELaNA-20 contains 3U or smaller CubeSats. Therefore, they are included in the 3U or smaller mentioned in 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 7.2 years maximum the ELaNa-20 CubeSats are 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 13 CubeSats is that of the INCA CubeSat with solar arrays deployed (37.5 X 11.5 X 11.5 cm with four deployed arrays each 37.5 cm X 11.5 cm): Figure 6: INCA Deployed Configuration '*+,#-" (+"# /∗ 1∗2 +.∗ 1∗4 !"#$ &'( = = . . Equation 1: Mean Cross Sectional Area for Convex Objects (5#6 + (7 + (7 !"#$ &'( = / 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 INCA (3.83 kg) orbit at deployment is 500 km apogee altitude by 500 km perigee altitude, with an inclination of 90 degrees. With an area to mass ratio of 0.09 m2/kg, DAS yields 4.7 years for orbit lifetime for its stowed state, which in turn is used to obtain the collision probability. Even with the variation in CubeSat design and orbital lifetime ELaNa-20 CubeSats see an average of 0.0 probability of collision. All CubeSats on ELaNa-20 were calculated to have a probability of collision of 0.0. Table 4 below provides complete results. 34

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

CACTUS- CubeSat 1 ALBus SurfSat CAPE-3 Q-PACE Mass (kg) 2.8 4.0 2.5 1.3 4.2 Mean C/S Area (m^2) 0.0459 0.0462 .0287 .035 0.035 Stowed Area-to Mass (m^2/kg) 0.0164 0.0116 0.0115 0.0269 0.00833 Orbital Lifetime (yrs) 5.2 5.6 5.7 4.7 6.2 Probability of collision (10^X) 0.00000 0.00000 0.00000 0.00000 0.00000 Mean C/S Area (m^2) 0.189 0.1224255 0.072377275 0.057272 0.092685182 Deployed ** Area-to Mass (m^2/kg) 0.016 0.013 0.0119 0.029 0.019 Orbital Lifetime (yrs) 1.4 2 2.2 0.6 1.1 Probability of collision (10^X) 0.00000 0.00000 0.00000 0.00000 0 Solar Flux Table Dated 1/26/2016 **Note: Blacked out areas represent CubeSats which do not have deployables Table 3: CubeSat Orbital Lifetime & Collision Probability

MicroMAS- CubeSat MITEE RadFXSat PICS INCA 2b Mass (kg) 1.3 2.7 2.7 3.83 4.5 Mean C/S Area (m^2) 0.039 0.0188 0.0188 0.147 0.039 Area-to Mass (m^2/kg) 0.00975 0.0144 0.00697 0.0384 0..00868 Stowed Orbital Lifetime (yrs) 5.9 5.3 6.6 4.3 6.1 Probability of collision 0.00000 0.00000 0.00000 0.00000 0.00000 (10^X) Mean C/S Area (m^2) 0.0220 0.1224255 0.0979 0.107 Deployed Area-to Mass (m^2/kg) 0.0055 0.013 0.0255 0.0238 Orbital Lifetime (yrs) 7.2 2 4.7 4.8 Probability of collision 0.00000 0.00000 0.00000 0.00000 0.00000 (10^X) Table 4: CubeSat Orbital Lifetime & Collision Probability (cont.) **Note: Blacked out areas represent CubeSats which do not have deployables 37

CubeSat EXOCUBE PolarCube SHFT-2 Mass (kg) 3.2 3.9 5.1 Mean C/S Area (m^2) 0.0406 0.0410 0.0391 Area-to Mass (m^2/kg) 0.0127 0.0105 0.00766 Stowed Orbital Lifetime (yrs) 5.5 5.8 3.2 Probability of collision 0.00000 0.00000 0.00000 (10^X) Mean C/S Area (m^2) 0.136 0.110 Deployed Area-to Mass (m^2/kg) 0.0425 0.0282 Orbital Lifetime (yrs) 4.2 4.6 Probability of collision 0.0 0.0 (10^X) Table 5: CubeSat Orbital Lifetime & Collision Probability (cont.) **Note: Blacked out areas represent CubeSats which do not have deployables 38

The probability of any ELaNa-20 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-20 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-20 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 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 disposal among the CubeSats finds MiTEE in its deployed configuration as the worst case. The area-to-mass is calculated for is as follows: !"#$ & ' ()"# *+ *+ = ()"# − 12 − !#,, !#,, -. -. Equation 3: Area to Mass 0.0222013 89 89 = 0.0055 4 ;< ;< MiTEE 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 2.1.1 Orbital Lifetime Calculations: DAS inputs are: 500 km maximum apogee 500 km maximum perigee altitudes with an inclination of 90 degrees at deployment no earlier than December 2017. An area to mass ratio of 0.0055 m2/kg for the MiTEE CubeSat was used. DAS 2.1.1 yields a 7.2 years orbit lifetime for MiTEE in its deployed 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.

Section 7: Assessment of Spacecraft Reentry Hazards A detailed assessment of the components to be flown on ELaNa-20 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. See Table 6 and Table 6. Table 6: ELaNa-20 High Melting Temperature Material Analysis (1/2) Demise Kenetic CubeSat Name Material Mass (kg) Alt (km) Energy (J) Stainless Steel CACTUS-1 Mounting screws .001 77.4 0 (generic) Stainless Steel CACTUS-1 Nuts .000128 77.8 0 (generic) Stainless Steel CACTUS-1 Threaded rod .01 78.0 0 (generic) CACTUS-1 Battery case Aluminum 7075-T6 .160 75.8 0 Stainless Steel ALBus Threaded Rod .00068 78 0 (generic) ALBus Baseplate Aluminum 7075-T6 0.0008 78 0 ALBus Springs Titanium (generic) 0.0069 78 0 Stainless Steel ALBus Gravity mass 0.0009 78 0 (generic) ALBus Screws Steel AISI 304 0.0004 78 0 ALBus Spacers Steel AISI 304 0.0058 78 0 ALBus Battery pack Aluminum 7075-T6 0.0228 78 0 40

Table 7: ELaNa-20 High Melting Temperature Material Analysis (2/2) Demise Alt Kenetic CubeSat Name Material Mass (g) (km) Energy (J) CAPE-3 Magnetorquers Iron .003156 75.8 0 CAPE-3 Separation springs Stainless Steel (generic) .0014 76.6 0 CAPE-3 Weight ballast Aluminum 6061-T6 .230 72.4 0 MiTEE Metal magnetorquer Nickel .058 71.0 0 MiTEE Deployment switch Titanium (generic) .0000005 78.0 0 MiTEE Boom housing Aluminum 6061-T6 .148 74.4 0 MiTEE Langmuir probe Titanium (generic) .001 0.0 0 MiTEE Antenna mounting probe Aluminum 6061-T6 .158 74.7 0 RadFXSat-2 PCB standoffs Aluminum 6061-T6 .0005 77.5 0 PICS Camera lens housing Stainless Steel (generic) .004 0.0 0 PICS Antenna hinge 1 Aluminum 7075-T6 .00013 78.0 0 PICS Antenna hinge 2 Aluminum 7075-T6 .00013 77.9 0 PICS Bracket Aluminum 6061-T6 .01018 76.9 0 INCA Detector lid Aluminum 6061-T6 .026 78.0 0 MicroMAS-2b Payload balance ring Aluminum 6061-T6 .166 75.9 0 MicroMAS-2b Payload ballast Tungsten .001 0.0 3 MicroMAS-2b Scanner housing Titanium (generic) .388 0.0 240 EXOCUBE Reaction wheel Aluminum 6061-T6 .0122 77.2 0 EXOCUBE Battery bracket Aluminum 6061-T6 .09325 76.1 0 EXOCUBE Tip mass brackets Aluminum 7075-T6 .001558 77.9 0 EXOCUBE Rough pass through Aluminum 7075-T6 .04905 74.8 0 EXOCUBE Boom hinge Aluminum 6061-T6 .00256 77.7 0 PolarCube Battery bracket Aluminum 6061-T6 .018 77.2 0 PolarCube Star camera bracket Aluminum 6061-T6 .0153 77.2 0 PolarCube Isolator plate Aluminum 6061-T6 .040 76.9 0 PolarCube Frangibolt assembly Aluminum 6061-T6 .0117 0.0 3 SHFT-2 ADCS Aluminum 6061-T6 .895 68.3 0 SHFT-2 rails Aluminum 7075-T6 .00399 77.9 0 Table 8: ELaNa-20 Summary of Surviving High Temperature Material Components CubeSat Name Material Mass (g) Demise Alt (km) Kinetic Energy (J) MiTEE Langmuir probe Titanium (generic) .001 0 9 PICS Camera lens housing Stainless Steel (generic) .004 0.0 0 MicroMAS-2b Payload ballast Tungsten .001 0.0 3 MicroMAS-2b Scanner housing Titanium (generic) .388 0.0 240 PolarCube Frangibolt assembly Aluminum 6061-T6 .0117 0.0 3 The majority of stainless steel 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: Table 9: Requirement 4.7-1 Compliance by CubeSat 41

Risk of Human Name Status Casualty CACTUS-1 Compliant 1:0 ALBus Compliant 1:0 CAPE-3 Compliant 1:0 Q-PACE Compliant 1:0 MiTEE Compliant 1:0 RadFXSat-2 Compliant 1:0 PICS Compliant 1:0 INCA Compliant 1:0 MicroMAS-2b Compliant 1:198200 EXOCUBE Compliant 1:0 PolarCube Compliant 1:0 SHFT-2 Compliant 1:0 *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 CubeSats that have surviving components like ALBus, MiTEE, PICS have a 1:0 probability as none of their components have more than 15J of energy. MicroMAS-2 has 1 component with greater than 15J of energy but the CubeSat’s probability of risk of human casualty still exceeds the NASA requirement on an order of magnitude All CubeSats launching under the ELaNa-20 mission are shown to be in compliance with Requirement 4.7-1 of NASA-STD-8719.14A. 42

Section 8: Assessment for Tether Missions ELaNa-20 CubeSats will not be deploying any tethers. ELaNa-20 CubeSats satisfy Section 8’s requirement 4.8-1. 43

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 A. Johnson Flight Design Analyst a.i. solutions/KSC/AIS2 cc: VA-H/Mr. Carney VA-H1/Mr. Beaver VA-H1/Mr. Haddox VA-G2/Mr. Treptow SA-D2/Mr. Frattin SA-D2/Mr. Hale SA-D2/Mr. Henry Analex-3/Mr. Davis Analex-22/Ms. Ramos 44

Appendix Index: Appendix A. ELaNa-20 Component List by CubeSat: ALBus Appendix B. ELaNa-20 Component List by CubeSat: CACTUS-1 Appendix C. ELaNa-20 Component List by CubeSat: CAPE 3 Appendix D. ELaNa-20 Component List by CubeSat: ExoCube Appendix E. ELaNa-20 Component List by CubeSat: INCA Appendix F. ELaNa-20 Component List by CubeSat: MicroMAS2b Appendix G. ELaNa-20 Component List by CubeSat: MiTEE Appendix H. ELaNa-20 Component List by CubeSat: PICS Appendix I. ELaNa-20 Component List by CubeSat: PolarCube Appendix J. ELaNa-20 Component List by CubeSat: Q-PACE Appendix K. ELaNa-20 Component List by CubeSat: RadFXSat-2 Appendix L. ELaNa-20 Component List by CubeSat: SHFT-2 45

Appendix A. ELaNa-20 Component List by CubeSat: ALBus Mass Diamete Melting Item Body Length Height High CUBESAT Name Qty Material (g) r/ Width Temp Survivability Number Type (mm) (mm) Temp (total) (mm) (Fº) ALBus 1.1 Discharge Board 1 PCB Box 50 95 95 3 No - Demise ALBus 1.2 MSP430 Board 1 PCB Box 50 95 95 3 No - Demise ALBus 1.3 Boost Convertor Board 1 PCB Box 50 95 95 3 No - Demise Battery Pack /(GOMSpace ALBus 1.4 1 No - Demise Battery) Aluminum 7075 Cylinder 720 94 88 20 ALBus 1.7 Threaded rod 2 Stainless Steel Cylinder 136 2.8 50 -- Yes 2642º Demise ALBus 2.1.1 Baseplate 1 Aluminum 7075 Box 33 95 95 95 Yes 1175º Demise ALBus 2.1.2 Release slide post 4 Stainless Steel Cylinder 3.5 3.2 21 21 No - Demise ALBus 2.1.5 SMA actuator 1 NiTi Cylinder <1g 0.3 59 59 Yes 2370º Demise ALBus 2.1.9 Release plate 1 Aluminum 7075 Box 30 95 95 95 No - Demise ALBus 2.2.1 Auxiliary Board 1 PCB-FR4 Box 50 95 95 95 No - Demise ALBus 3.1 Radio Support Board 1 PCB-FR4 Box 50 95 95 95 No - Demise ALBus 3.5 Radio Board 1 PCB-FR4 Box 50 95 95 95 No - Demise rectangular ALBus No - Demise 4.1.1 Solar panel Substrate 4 PCB-FR4 prism 80 83 315 0.76 rectangular ALBus Yes 2370º Demise 4.1.2 SMA Spring 8 NiTi prism 3.6 15 55 0.7 ALBus 4.1.3 Lugs 4 Stainless Steel cylinder 5.4 11 21 1.3 No - Demise ALBus 4.1.5 Hinge pin 4 Stainless Steel cylinder 20 3.175 76 --- No - Demise rectangular ALBus Yes - Demise 4.2.5 Gravity Gradient Mass 4 Stainless Steel prism 40 63.5 38.1 2.1 rectangular ALBus 1 16 No - Demise 4.3.1 Heat Sink Aluminum 6061 prism 350 100 100 ALBus 4.3.2 Hinge brackets 4 Aluminum 7075 cube 7 14 14 5 No - Demise rectangular ALBus 0.5 No - Demise 4.3.8 Lock hook 4 Stainless Steel prism 1 5 5 ALBus 5.1 Load Bank Board 1 PCB Box 75 95 95 10 No - Demise ALBus 6.1 Chassis 1 Aluminum 7075 Box 210 98 98 307 No - Demise

ALBus 6.4 Body mounted solar array 4 FR4 PCB Box 54 54 83 .76 No - Demise ALBus 7.1 Screws 97 Stainless Steel 304 Cylinder 43.16 Various - - Yes 2642º Demise Stainless Steel 304/ ALBus 32 Cylinder 16.84 Various - - No - Demise 7.2 Nuts Nylon ALBus 7.3 Spacers 28 Stainless Steel 304 Cylinder 12.56 Various - - Yes 2642º Demise Appendix B. ELaNa-20 Component List by CubeSat: CACTUS-1 Mass Diameter Melting Item Body Length Height High CUBESAT Name Qty Material (g) / Width Temp Survivability Number Type (mm) (mm) Temp (total) (mm) (Fº) 2838.1 CACTUS-1 1 CACTUS - 1 3U Cubesat 1 - Box - - - - - - 93 CACTUS-1 2 Aerogel Monolith 2 Silica Aerogel Box 7 50.8 50.8 12.7 No - Demise CACTUS-1 3 Tab Base 1 Aluminum 7075 Flat Plate 296 113 364 3.5 No - Demise CACTUS-1 4 Frame 1 Aluminum 7075 Box 391 101.5 364 100 No - Demise CACTUS-1 5 End Mount (Comms side) 1 Aluminum 7075 Flat Plate 43 97 98.5 13.5 No - Demise Hermes End Mount CACTUS-1 6 1 Aluminum 7075 Flat Plate 44 97 98.5 13.5 No - Demise (Antenna) CACTUS-1 7 Tape Antenna 2 Steel Flat Plate 12.8 25.4 32 3 No - Demise CACTUS-1 8 Aerogel Capture Bay (ACB) 2 Aluminum 7075 Box 160 75.54 125.54 42.2 No - Demise CACTUS-1 9 Battery Case 1 Aluminum 7075 Box 99 86.74 91.2 39 Yes - Demise CACTUS-1 10 Battery Case Lid / Burn Box 1 Aluminum 7075 Box 73 90.74 91.2 32 Yes - Demise CACTUS-1 11 End Mount (ACB side) 1 Aluminum 7075 Box 44 97 98.5 13.5 No - Demise CACTUS-1 12 Hermes End Mount (Interior) 1 Aluminum 7075 Flat Plate 44 97 98.5 13.5 No - Demise CACTUS-1 13 RASC Locks 4 Aluminum 7075 Flat Plate 28 12 125.54 16.5 No - Demise CACTUS-1 14 Batteries 7 Li-Ion Cylinder 350 18.4 64.8 - No - Demise CACTUS-1 15 Pointing Magnet 1 NdFeB grade 42 Cylinder 20 9.525 38.1 - No Demise Mounting Screws M3 x (4, 6, Varies (4, CACTUS-1 16 64 Stainless Steel Cylinder 64 3 - Yes 2642º Demise 8, 10) 6, 8, 10) Solar Panel PCB (Top and CACTUS-1 17 2 PCB FR-4 Flat Plate 156 100 264 1.6 No - Demise Bottom) 47

CACTUS-1 18 Solar PCB (Left, Right Side) 2 PCB FR-4 Flat Plate 48 90 91 1.6 No - Demise Small Solar PCB (Left, Right CACTUS-1 19 2 PCB FR-4 Flat Plate 22 40 90 1.6 No - Demise Side) CACTUS-1 20 Hermes Solar PCB (Sides) 2 PCB FR-4 Flat Plate 26 50 90 1.6 No - Demise CACTUS-1 21 Hermes Solar PCB (Bottom) 1 PCB FR-4 Flat Plate 25 86.5 100 1.6 No - Demise CACTUS-1 22 Antenna PCB 1 PCB FR-4 Flat Plate 18 60 97 1.6 No - Demise CACTUS-1 23 Hermes Solar PCB (Top) 1 PCB FR-4 Flat Plate 15 50 100 1.6 No - Demise CACTUS-1 24 Hermes Helix Antenna 1 Varies Cylinder 14 18 48 - No - Demise CACTUS-1 25 Mylar Support Wire 4 Steel Cylinder 6 1 72.54 - No - Demise Flat CACTUS-1 26 Solar Panels 454 Solar Cell 79.5 8 26.3 0.16 No - Demise Plane Est. 330- CACTUS-1 27 Nylon String (Antenna) 1 Nylon Wire 0.15 1.0 - No - Demise 380 CACTUS-1 28 Mylar sheets N/A PET Mylar Flat Plate 1 N/A N/A 0.01 No - Demise CACTUS-1 29 M3 Weld Nuts 56 Stainless steel Cylinder 56 7.5 3 - Yes 2642º Demise Varies (4, CACTUS-1 30 M2 x (4,8) mm Screws 12 Stainless steel Cylinder 12 2 - No - Demise 8) CACTUS-1 31 Threaded Rod 1 2 Stainless Steel Cylinder 10 3 95.4 - No - Demise CACTUS-1 32 Threaded Rod 2 2 Stainless steel Cylinder 10 3 93.4 - No - Demise CACTUS-1 33 M3 Nuts 16 Stainless steel Cylinder 8 5.5 2.4 - Yes 2642º Demise CACTUS-1 34 M2 Nuts 8 Stainless steel Cylinder 4 4.5 1.6 - Yes 2642º Demise CACTUS-1 35 Hysteresis Rods 2 Permalloy 80 Cylinder 14 2 95 - No - Demise Bus Insulation (Top, Left, CACTUS-1 36 3 Aerogel Blanketing Flat Plate 18 84.4 97 2 No - Demise Right) Battery Insulation (Front, CACTUS-1 37 2 Aerogel Blanketing Flat Plate 10 80.2 82.74 2 No - Demise Back) CACTUS-1 38 Bus Insulation (Back) 1 Aerogel Blanketing Flat Plate 6 93.5 95 2 No - Demise CACTUS-1 39 Bus Insulation (Front) 1 Aerogel Blanketing Flat Plate 6 88.5 93.5 2 No - Demise CACTUS-1 40 Bus Insulation (Bottom) 1 Aerogel Blanketing Flat Plate 5 84.4 97 2 No - Demise Insulation packer (Battery CACTUS-1 41 2 Aerogel Blanketing Flat Plate 4 26.1 82.74 2 No - Demise Top and Bottom) Insulation Packet (Battery CACTUS-1 42 2 Aerogel Blanketing Flat Plate 2 26.1 80.2 2 No - Demise sides) CACTUS-1 43 RASC W/ coatings 2 PLA Plastic, RTV Box 112 56 69 26.8 No - Demise 48

CACTUS-1 44 Hermes Battery Mount 2 ABS plastic Box 35.2 22.25 73 21.5 No - Demise Cactus Plastic Battery Thermoplastic CACTUS-1 45 1 Box 26 76.2 78.74 22.1 No - Demise Housing Polyester, Aluminum Copper, Plastic, CACTUS-1 46 Coaxial Cable 1 Wire 2 5 40 - No - Demise Polyethylene 28 AWG, Copper, CACTUS-1 47 Wiring N/A Cylinder 35 1.5 N/A - No - Demise Teflon CACTUS-1 48 Solder 1 Tin/Lead N/A 10 N/A N/A N/A No - Demise Rod / CACTUS-1 49 Nichrome Burn Wire 1 Nichrome 0.003 0.16 200 - No - Demise wire PCB FR4, Glass, CACTUS-1 50 TTL- jpeg camera 2 Block ? 22.3 32 32 24.75 No - Demise Plastic BUS Boards ( Power, PCB FR-4, Surface Flat CACTUS-1 51 4 248 90.17 95.885 12.75 No - Demise Comms, Sensor, CPU ) Mount Components Plane PCB FR-4, Surface Flat CACTUS-1 52 Hermes Electrical PCB 1 25.4 90.17 95.88 1.6 No - Demise Mount Components Plane Hermes Iridium Modem PCB FR-4, Surface CACTUS-1 53 1 Block 31 35.75 61 12.5 No - Demise 9603 Mount Components PCB FR-4, Surface Flat CACTUS-1 54 Hermes Raspberry Pi 0 1 11 31 65 4.5 No - Demise Mount Components Plane Raspberry Pi Compute PCB FR-4, Surface Flat CACTUS-1 55 1 5.76 30 67.6 1 No - Demise Module Mount Components Plane 5 mm LED (Dimensions not CACTUS-1 56 4 Generic LED Cylinder 1.08 5 5.6 - No - Demise including wires) CACTUS-1 57 Foot Switch 2 Plastic, steel Box 2 15.2 20.1 6.4 No - Demise .75 734 RTV conformal coating Silicone Rubber CACTUS-1 58 Fluid N/A N/A N/A N/A N/A No - Demise (Electronics) MIL-A-46106 oz. .75 3145 RTV conformal coating Silicone Rubber CACTUS-1 59 Fluid N/A N/A N/A N/A N/A No - Demise (Structure) MIL-A-46146 oz. CACTUS-1 60 Double Sided Tape N/A Polyimide Kapton Flat Plate 12 N/A N/A 0.01 No - Demise CACTUS-1 61 Nylon spacer 16 mm 8 Nylon 66 Cylinder 4 4.5 16 - No - Demise CACTUS-1 62 Nylon spacer 18 mm 8 Nylon 66 Cylinder 4 4.5 18 - No - Demise CACTUS-1 63 Nylon spacer 14 mm 4 Nylon 66 Cylinder 2 4.5 14 - No - Demise CACTUS-1 64 Nylon spacer 22 mm 4 Nylon 66 Cylinder 2 4.5 22 - No - Demise CACTUS-1 65 Nylon spacer 19mm 4 Nylon 66 Cylinder 2 4.5 19 - No - Demise 66 CACTUS-1 Nylon M3 Nut 2 Nylon 66 Cylinder 1 5.5 2.4 - No - Demise 49

Appendix C. ELaNa-20 Component List by CubeSat: CAPE-3 Diameter Melting Item Body Mass (g) Length Height High CUBESAT Name Qty Material / Width Temp Survivability Number Type (total) (mm) (mm) Temp (mm) (Fº) CAPE-3 0 CubeSat 1 Aluminum 6061 Cube 1330 100 113.5 100 No - Demise CAPE-3 1 Frame 1 Aluminum 6061 Cube 180 100 113.5 100 No - Demise CAPE-3 2 Battery Cells 4 Lithium Ion Cylinder 45 26 70 n/a No - Demise CAPE-3 3 Solar Cells 12 Crystalline Silicon Flat Plate 2.24 39.5 68.9 n/a No - Demise Silver alloy gold CAPE-3 4 Deployment Switches 2 Box 0.28 6.1 No - Demise plated 8.1 2.7 CAPE-3 5 RBF Pin 1 Stainless Steel Cylinder n/a n/a n/a n/a No - Demise CAPE-3 6 Screws/Bolts X Stainless Steel Cylinder 0.6 3 11 n/a No - Demise CAPE-3 7 Long Antenna 4 Nitinol Thin wire 0.87 0.5 508 n/a No - Demise CAPE-3 8 Short Antenna 4 Nitinol Thin wire 0.25 0.5 178 n/a No - Demise CAPE-3 9 Antenna Platforms 2 Delrin Flat Plate 40 100 100 6 No - Demise CAPE-3 10 Motherboard 1 PCB Flat Plate 40 97 97 1.6 No - Demise CAPE-3 11 Comm board 2 PCB Flat Plate 40 97 97 1.6 No - Demise CAPE-3 12 Comm board 1 PCB Flat Plate 40 97 97 1.6 No - Demise CAPE-3 13 Battery Board 1 PCB Flat Plate 30 97 97 1.6 No - Demise CAPE-3 14 Power Board 1 PCB Flat Plate 40 97 97 1.6 No - Demise CAPE-3 15 Exterior PCBs 4 PCB Flat Plate 30 97 97 1.6 No - Demise CAPE-3 16 Separation Springs 2 Stainless Steel Cylinder 1.4 0.07 0.6 n/a Yes 2642º Demise CAPE-3 17 Cabling/wiring X copper, rubber wire variable variable variable variable No - Demise Rectangl CAPE-3 18 Cell Housing 1 Cotton lacing cord n/a 2.38 n/a 0.397 No - Demise ular Cylindric CAPE-3 19 PCB Connecting Rods 4 Stainless Steel 6 3 100 n/a No - Demise al Rod Rectangl CAPE-3 20 Mezanine Connectors 10 Thermoplastic 1.163 8 51.5 4.86 No - Demise e 50

CAPE-3 21 Reaction Wheel 1 DC Motor Cube 55 28 31 26 No - Demise Cylindric CAPE-3 22 Magnetorque Core 2 Iron 3.156 3.2 50 n/a Yes 2800º Demise al CAPE-3 23 Magnetorque Wire 2 Copper Wire Wire 0.318 0.12 7854 n/a No - Demise CAPE-3 24 Control Board 1 PCB Square 45 97 97 1.6 No - Demise CAPE-3 25 Payload Board 1 PCB Square 50 97 97 1.6 No - Demise CAPE-3 26 Crystals 2 Triboluminescent Paste variable variable variable variable No - Demise Cylindric CAPE-3 27 Camera 1 Plastic/glass 6.862 10 10 10 No - Demise al CAPE-3 28 Geiger Counter 1 sensor Box 3.55 16 28 6 No - Demise Cylindric CAPE-3 29 LED's 2 semiconductor 0.25 5 9 n/a No - Demise al rectangle CAPE-3 30 Weight Ballast X Aluminum 6061 230 variable variable variable Yes 1205º Demise s 51

Appendix D. Elana-20 Component List by CubeSat: EXOCUBE Mass Diameter Melting Item Body Length Height High CUBESAT Name Qty Material (g) / Width Temp Survivability Number Type (mm) (mm) Temp (total) (mm) (Fº) EXOCUBE 1 ExoCube++ 3U CubeSat 1 Various Box 3864 100 100 340.5 No - Demise Black Anodized 1228.8 EXOCUBE 2 CubeSat Structure 1 Box 100 100 340.5 No - Demise Aluminum 6061 7 EXOCUBE 3 Antenna 2 Nitinol Wire Cylinder 2.7 0.15 80 N/A No - Demise EXOCUBE 4 Antenna Route 1 Delrin Box 4.73 64.48 64.4 3.4 No - Demise EXOCUBE 5 Solar Cell 24 Eglass Box 7.45 69 40 1 No - Demise EXOCUBE 6 X Panel 2 FR-4 Multilayer PCB Box 91.67 83 289 1.6 No - Demise EXOCUBE 7 Y Panel 2 FR-4 Multilayer PCB Box 87.12 83 334 1.6 No - Demise Aluminum 6061, Nitronic 60 (UNS EXOCUBE 8 Reaction Wheel 1 S21800) SS, Delrin, Box 122 40.64 40.64 19.05 Yes 2795º Demise Samarium Cobalt, SS 416 EXOCUBE 9 Magnetorquer Route 3 Delrin Box 3.5 82 51 4 No - Demise EXOCUBE 10 Magnetorquer Wire 3 Copper Cylinder 9 3 260 N/A No - Demise EXOCUBE 11 GPS Patch 1 Ceramic Box 20 25.1 25.1 5.2 No - Demise EXOCUBE 12 Batteries 4 Lithium Ion Cylinder 45 19.16 66 N/A No - Demise EXOCUBE 13 Battery Bracket 1 Aluminum 6061 Box 93.25 81 89.85 28.15 Yes 1205º Demise -Z System Board w/ EXOCUBE 14 1 FR-4 Multilayer PCB Box 60 83 100 13.8 No - Demise Components -Z Payload Interface and EXOCUBE 15 1 FR-4 Multilayer PCB Box 50 83 83 3 No - Demise Battery Board +Z Payload Extension EXOCUBE 16 1 FR-4 Multilayer PCB Box 50 83 83 5.15 No - Demise Board EXOCUBE 17 +Z Panel 1 FR-4 Multilayer PCB Box 30 100 100 2.5 No - Demise EXOCUBE 18 -Z Panel 1 FR-4 Multilayer PCB Box 30 100 100 2.5 No - Demise EXOCUBE 19 Tip Mass Brackets 2 7075-T6, Plate (SS) Box 15.58 31.57 79.47 5 Yes 2795º Demise EXOCUBE 20 Rough Pass Through 1 Aluminum 6061 Cylinder 49.05 31.75 36.66 30.23 Yes 1205º Demise RNF-100 Polyolefin EXOCUBE 21 Heat Shrink 1 Tube 1 63.5 25.4 0.5 No - Demise Heat Shrink 52

3M Scotch Weld Rectangula EXOCUBE 22 Staking Compound 1 50 N/A N/A N/A No - Demise 2216 r EXOCUBE 23 Kapton Tape 1 Kapton Tape Tape 0 Various Various 0.05 No - Demise Rectangula EXOCUBE 24 Sep/Actuating Switches 5 Plastic (PBT) 2 6 8 7 No - Demise r Rectangula EXOCUBE 25 Boom Mass 2 Brass Alloy 360 200.69 33.5 67.8 16.8 No - Demise r EXOCUBE 26 Boom Truss 2 FR-4 Multilayer PCB Box 27.3 68 299.4 2 No - Demise Rectangula EXOCUBE 27 Kit Kat 2 Aluminum 6061 3.01 11.4 28.05 5.18 No - Demise r AISI 316 Annealed EXOCUBE 28 Boom Spring 2 Cylinder 1 6.1 20 N/A No - Demise SS Bar EXOCUBE 29 Screw - Representative 152 Stainless Steel 316 Cylinder 0.87 2.8 10 N/A No - Demise EXOCUBE 30 Boom Hinge 2 Aluminum 6061 Box 2.56 15 46 6.5 Yes 1205º Demise FR-4 Multilayer PCB, Stainless Steel, EXOCUBE 31 Goddard Instrument 1 Aluminum 6061 Box 400 74 75 1.59 No - Demise Chromate Conversion, Ultem, EXOCUBE 32 GPS Board 1 FR-4 Multilayer PCB Box 24 45.72 71.12 11.09 No - Demise EXOCUBE 33 Battery Board 1 FR-4 Multilayer PCB Box 50 58.51 78.51 8.12 No - Demise EXOCUBE 34 Solar Angle Sensor Board 4 FR-4 Multilayer PCB Box 20 20 30 1.6 No - Demise 53

Appendix E. Elana-20 Component List by CubeSat: INCA Mass Diameter Melting Item Body Length Height High CUBESAT Name Qty Material (g) / Width Temp Survivability Number Type (mm) (mm) Temp (total) (mm) (Fº) INCA 2 Deployable Solar Panels 1 Aluminum 7075 Box 154 100 341.8 100 No - Demise INCA 3 Fixed Solar Panels 4 PCB Flat Plate 39.4 82 332 3 No - Demise INCA 4 Neutron Detector Case 4 PCB Flat Plate 40 82 250 3 No - Demise INCA 5 Neutron Detector Lid 1 Aluminum 6061 Box 855 88 223 86 Yes 1205º Demise INCA 6 Scintillators Crystals 1 Aluminum 6061 Flat Plate 26 88 223 3 No - Demise INCA 7 Scintillators Holders 2 P-Terfinal Cylinder 966 51 42 No - Demise INCA 8 Veto Boards 2 Aluminum Box 245 72 72 76 No - Demise INCA 9 Battery Pack 4 EJ-212 Flat Plate 235 69 219 3 No - Demise Aluminum 6061 INCA 10 Beagle Bone 1 Box 247 No - Demise and Lithium INCA 11 Link Star Radio 1 PCB Flat plate 40 86 53 ~10 No - Demise unkno Unkno INCA 12 Intrepid XY 1 PCB Flat plate Unknown Unknown No - Demise wn wn INCA 13 Novatel OEM-615 GPS 4 PCB Flat plate 32 103 83 ~5 No - Demise INCA 14 Intrepid Systems Board 1 PCB Flat plate 22 71 46 12 No - Demise INCA 15 Intrepid -Z 1 PCB Flat plate 104 94 83 ~2 No - Demise INCA 16 Sun Sensor 1 PCB Flat plate 96 91 91 ~5 No - Demise Miscellaneous Nuts and INCA 17 1 PCB - - - - - No - Demise Screws INCA 18 Missilaneous Wires Unknown Steel - - - - - No - Demise 54

Appendix F. Elana-20 Component List by CubeSat: MicroMAS-2b Mass Diameter Melting Item Body Length Height High CUBESAT Name Qty Material (g) / Width Temp Survivability Number Type (mm) (mm) Temp (total) (mm) (Fº) MicroMAS- Payload Antenna/Gband 1 1 Al 6061 Box 115 80 20 No - Demise 2b Mixer MicroMAS- 2 Payload G RFE 1 Al, Au coated Box 30 80 50 30 No - Demise 2b MicroMAS- 3 Payload W/F RFE 1 Al, Au coated Box 42 No - Demise 2b MicroMAS- PCB FR4, Dupont 4 IF Processor 1 Box 118 68 58 25 No - Demise 2b 9K7 LTCC MicroMAS- 5 Payload Interface Module 1 PCB FR4 Board 16 70 60 10 No - Demise 2b MicroMAS- Payload Voltage Regulator 6 1 PCB FR4 Board 20 65 35 10 No - Demise 2b Module MicroMAS- Payload Dielectric Resonant 7 1 Box 54 32 41 16 No - Demise 2b Oscillator stainless steel, MicroMAS- hermetically 8 Payload Heaters/Thermostat 1 Cylinder 10 16 - 13 No - Demise 2b sealed dry nitrogen Al 6061 passivated; MicroMAS- tungsten; Various 9 Payload Structures, fasteners n/a 275 100 100 100 No 6191º Survives 2b fastnerers: plates stainless steel 304L MicroMAS- 10 Payload Harnesses n/a Cables 40 - - - No - Demise 2b MicroMAS- Various 11 Payload Balance Ring 1 Al 6061 166 80 - 10 Yes 1205º Demise 2b plates MicroMAS- 12 Payload Ballast 10 tungsten screw 1 3 25 Yes 6191º Survives 2b MicroMAS- 13 Bus Avionics TIB/Gyro 1 PCB: FR4 Board 111 96 90 16 No - Demise 2b MicroMAS- 14 Bus Avionics Processor 1 PCB: FR4 Board 104 96 90 11 No - Demise 2b MicroMAS- 15 Bus Avionics BIB 1 PCB: FR4 Board 54 96 90 8 No - Demise 2b MicroMAS- 16 Bus Avionics Radio 1 Housing: Al Board 138 68 79 15 No - Demise 2b 55

MicroMAS- 17 Bus Radio UHF Filter 1 Box 36 35 14 10 No - Demise 2b MicroMAS- Antenna: spring 18 Bus Radio UHF Antenna 1 Plate 30 8 178 - No - Demise 2b steel; cables: FEP MicroMAS- 19 Bus Avionics EPS 1 PCB: FR4 Board 150 90 85 11 No - Demise 2b MicroMAS- PCB: FR4; cells: 20 Bus Avionics Battery 1 Board 173 95 86 15 No - Demise 2b Li cobalt oxide Housing: Al 6061; MQT: MicroMAS- Bus Avionics ADCS 21 1 electromagnet Box 638 100 100 56 No - Demise 2b Housing ferrite 66; PCB: FR4 Neodymium MicroMAS- Bus Avionics ADCS reaction magnet, stainless 22 3 Box 160 40 20 20 No - Demise 2b wheels steel case, ceramic balls PCB: FR4 PCB; MicroMAS- cells:GaInP2/GaA 23 Bus Solar Panel Assembly 4 Board 250 82 326 1.6 No - Demise 2b s/Ge; Hinges: Al 6082 MicroMAS- 24 Bus Solar Panel Harness Set 1 PTFE Cables 30 - - - No - Demise 2b MicroMAS- RTD: alumina; 25 Bus Thermal Control 1 Cable 50 - - - No - Demise 2b Wires: PTFE Rails: Al 7075 anodized; Sides: MicroMAS- Bus Housing Assembly, Al 6061 alodined; Various 26 1 328 - 200 90 No - Demise 2b fasteners Fasteners: plates stainless steel 304L MicroMAS- 27 Bus Wiring n/a ETFE-SB Cables 39 - - - No - Demise 2b Housing, shaft: Al 6061; Hub: titanium; Bearings:, MicroMAS- 28 Scanner Housing 1 stainless steel Cylinder 388 73 - 42 Yes 3034º Survives 2b balls, Braycote 601 lubricant; Encoder grating: soda lime glass Rotor: stainless MicroMAS- steel 455; Stator: 29 Scanner Motor 1 Cylinder 163 68 - 25 No - Demise 2b neodymium boron iron magnet 56

Appendix G. ELaNa-20 Component List by CubeSat: MITEE Mass Diameter Melting Item Body Length Height High CUBESAT Name Qty Material (g) / Width Temp Survivability Number Type (mm) (mm) Temp (total) (mm) (Fº) MiTEE 1 MiTEE 3U Cubesat - - - - - - - - - - MiTEE 2 CubeSat Main Walls 2 6061 Aluminum Box 98 100 10 340 No - Demise MiTEE 3 Cubesat Side Walls 2 6061 Aluminum Box 290 100 10 340 No - Demise Oriented Rhenium, MiTEE 4 Langmuir Probe 1 Cylinder 50 4 53 4 Yes 3034º Yes Titanium, Molybdeum Langmuir Probe Deployment MiTEE 5 1 6061 Aluminum Hinge 10 12 95 15 No - Demise Mechanism MiTEE 6 Antennae 4 302 Steel Tape 20 1.5 17 1 No - Demise MiTEE 7 Radio Board 1 PCB Board 60 93 97 10 No - Demise MiTEE 8 Radio 1 Aluminum Box 52 32 62 9 No - Demise MiTEE 9 Langmuir Probe Board 1 PCB Board 60 93 97 16 No - Demise MiTEE 10 Metal Core Magnetorquer 2 Nickel-Alloy Cylinder 58 25 55 13 Yes 2651º Demise Square MiTEE 11 Air Core Magnetorquer 1 PLA 58 70 70 20 No - Demise Coil MiTEE 12 Magnetorquer Board 1 PCB Board 18 93 97 35 No - Demise MiTEE 13 ADCS PCB 1 PCB Board 60 93 97 13 No - Demise MiTEE 14 CDH PCB 1 PCB Board 60 93 97 8 No - Demise MiTEE 15 EPS/Plasma PCB 1 PCB Board 60 93 97 8 No - Demise MiTEE 16 EPS Battery PCB 1 PCB Board 430 93 97 35 No - Demise MiTEE 17 Batteries 4 Lithium Ion Cylinder 45 18 65 18 No - Demise MiTEE 18 HVPS PCB 1 PCB Board 75 93 97 16 No - Demise Constant Current Power MiTEE 19 1 PCB Board 68 93 97 19 No - Demise Supply PCB Concave MiTEE 20 Thermionic Cathode 2 Stainless Steel1 5 10 13 9 No - Demise Repellor MiTEE 21 Boom Tape 4 Stainless Steel Tape 0.7 20 1 50 No - Demise 57

6061-T6 MiTEE 22 Boom Housing 1 Box 148 60.5 50 41.8 Yes 1205º Demise Aluminum MiTEE 23 Anode End Body 1 6061 Aluminum Box 50 80 80 20 No - Demise MiTEE 24 Deployment Switch 2 Titanium Cylinder 2 5 5 26 Yes 3034º Demise MiTEE 25 Solar Panel PCB 4 PCB Board 138 80 340 2 No - Demise InGaP/InGaAs/Ge MiTEE 26 Solar Cell 24 Flat Cell 3 80 23 0.5 No - Demise Solar Cell MiTEE 27 Photodiode 13 Silicon Sensor 1 1 3 0.4 No - Demise MiTEE 28 Backplane PCB 1 PCB Board 62 200 2 No - Demise Polyester and Header MiTEE 29 Backplane Connectors 18 1 6 23 8 No - Demise Copper Connector MiTEE 30 Fasteners 70 Stainless Steel Bolt <1 5 5 Various No - Demise MiTEE 31 Cabling 4 Copper Cylinder 1 2 10 2 No - Demise MiTEE 32 Wedgelocks 18 6063 Aluminum Box 2 6 74 6 No - Demise MiTEE 33 Antenna Mounting Plate 1 6061 Aluminum Plate 158 100 100 19 Yes 1205º Demise 58

Appendix H. ELaNa-20 Component List by CubeSat: PICS Mass Diameter Melting Item Body Length Height High CUBESAT Name Qty Material (g) / Width Temp Survivability Number Type (mm) (mm) Temp (total) (mm) (Fº) PICs-A/B Identical 1U PICS 1 1 Aluminum 6061 Box 1209.4 116 116 116 No - Demise CubeSats PICS 2 CubeSat Structure 1 Aluminum 6061 Box 330 102.5 100 110 No - Demise PICS 3 Antennae 4 Copper 101 Cylinder 4.5 3 69 - No - Demise PICS 4 Solar Harvester Board 6 Fiberglass FR4 Box 35 83 100 2 No - Demise PICS 5 Solar Cell 12 GaAs Box 2.2 40 69 0.14 No - Demise PICS 6 Separation Switch 2 PBT Box 3 13 7 6 No - Demise PICS 7 Separation Spring 2 Steel Cylinder 3 3 13 - No - Demise PICS 8 Camera Lens 6 Glass Cylinder 3 14 8 - No - Demise PICS 9 Camera Lens Housing 6 Stainless Steel Cylinder 4 19 4 - Yes 2642º Yes PICS 10 Antenna Hinge Side 1 4 Aluminum 7075 Box 3 26.5 6 6 Yes 1205º Demise PICS 11 Antenna Hinge Side 2 4 Aluminum 7075 Box 3 13.8 5.7 4.45 Yes 1205º Demise Stainless Steel PICS 12 Antenna Hinge Spring 4 Cylinder 1 6 4 - No - Demise 301 PICS 13 Antenna Inhibit Wire 4 Nylon Wire 1 0.3048 10 - No - Demise Antenna Deployment Burn PICS 14 4 Nichrome Wire 1 0.0762 7 - No - Demise Wire PICS 15 CubeSat Feet 8 Aluminum 6061 Box 1.25 8 8.5 8.5 No - Demise PICS 16 Bracket 4 Aluminum 6061 Box 10.18 60 8 8 Yes 1205º Demise PICS 17 Camera Mount 6 Aluminum Box 14.6 4 50 48.4 No - Demise Aluminum 1100- PICS 18 Mounting Rods 4 Cylinder 1 2.4 72 - No - Demise O PICS 19 Hex Standoff 8 Aluminum Cylinder 1 5.5 15.5 - No - Demise PICS 20 Solar Harvester Connectors 6 Nylon 66 Box 0.218 3.2 15.5 4.2 No - Demise PICS 21 Camera 6 Fiberglass FR4 Box 25 35 25 22 No - Demise PICS 22 Camera Housing 6 Aluminum Box 15 16 16 16 No - Demise 59

PICS 23 Camera Board 6 Fiberglass FR4 Box 10 35 25 1.65 No - Demise Fiberglass Isola PICS 24 Radio 1 Box 50 45 45 8 No - Demise FR408 PICS 25 Antenna Board 1 Fiberglass FR4 Box 15 88 88 1.65 No - Demise PICS 26 Battery Boards 4 Fiberglass FR4 Box 10 51 51 2 No - Demise PICS 27 C&DH Board 1 Fiberglass FR4 Box 40 88 88 3 No - Demise PICS 28 FPGA SoM 1 Fiberglass FR4 Box 11 30 57 1.6 No - Demise Phillips Screw with Lock Stainless Steel 18- PICS 29 20 Cylinder 0.24 4.7 6.3 - No - Demise Washer 8 Phillips Screw with Lock Stainless Steel 18- PICS 30 18 Cylinder 0.27 4.7 7.9 - No - Demise Washer 8 Stainless Steel 18- PICS 31 Flat Head Phillips Screw 16 Cylinder 0.35 5.4 8 - No - Demise 8 Metric Phillips Machine Stainless Steel 18- PICS 32 4 Cylinder 0.02 3.2 11.3 - No - Demise Screw 8 Steel, Class 8, PICS 33 Zinc Plated Steel Hex Nut 1 Cylinder 0.04 3.7 1.3 - No - Demise Zinc Plated Metric Flat Head Phillips PICS 34 4 Steel, Zinc Plated Cylinder 0.193 4.7 5 - No - Demise Machine Screw Metric Cheese Head Slotted PICS 35 4 Steel, Zinc Plated Cylinder 0.074 2.6 5.9 - No - Demise Machine Screw Steel, Black PICS 36 Socket Head Cap Screw 24 Cylinder 0.13 3 6.6 - No - Demise Oxide Alloy PICS 37 Wires 180 Copper Wire 0.03 0.321 40 - No - Demise PICS 38 Thermal Strap/Sink 3 Aluminum 6061 Box 3 30 5 - No - Demise PICS 39 Batteries 4 LiPo Box 17 34 48 5.5 No - Demise Passive Electro-magnetic PICS 40 5 Copper Cylinder 4 5 30 No - Demise Stabilization Coils PICS 41 Camera Connectors 6 Nylon 66 Box 0.2002 3.2 14.25 4.2 No - Demise 60

Appendix I. ELaNa-20 Component List by CubeSat: POLARCUBE Mass Diameter Melting Item Body Length Height High CUBESAT Name Qty Material (g) / Width Temp Survivability Number Type (mm) (mm) Temp (total) (mm) (Fº) POLARCUBE 1 PolarCube 3U CubeSat 1 Aluminum 6061 Box - - - - No - Demise POLARCUBE 2 Bus Deployed Solar Panel 4 FR-4, GaAs Plate 75 84 340 2 No - Demise POLARCUBE 3 Bus Exo-Frame (Rails) 4 Aluminum 6061 Plate 55.9 98.5 340.5 8.5 No - Demise POLARCUBE 4 Bus Exo-frame Solar Panel 4 FR-4, GaAs Plate 55 84 340 2 No - Demise POLARCUBE 5 Bus X PEZ Frame 2 Aluminum 6061 Plate 35.4 82.5 165.1 6.1 No - Demise POLARCUBE 6 Bus Y PEZ Frame 2 Aluminum 6061 Plate 27.7 82.5 165.1 13.3 No - Demise POLARCUBE 7 Payload PEZ Frame 4 Aluminum 6061 Plate 79 82.5 195.1 13.3 No - Demise POLARCUBE 8 Payload Reflector 1 Aluminum 6061 Disk 40 94.56 75.69 34.99 No - Demise POLARCUBE 9 Payload Reflector Housing 1 Aluminum 6061 Plate 45 72.09 69.43 20.32 No - Demise POLARCUBE 10 Payload Deployment Rail 1 Steel Rod 37.69 7 158.88 5 No - Demise POLARCUBE 11 Bus Tx Antenna 1 Brass, FR-4 Can 13 60 32.6 - No - Demise POLARCUBE 12 Bus Rx Antenna Bracket 2 Aluminum 6061 Block 7.4 22 26 10 No - Demise POLARCUBE 13 Bus solar panel hinge 12 Steel 304 Plate 3.4 7.8 31.8 3 No - Demise POLARCUBE 14 Bus Rx Antenna Axle 2 FR-4, Copper Plate 10 10 200 0.76 No - Demise POLARCUBE 15 Bus Deployment Claws -Z 4 Aluminum 6061 Block 1.8 10.8 13.8 12.3 No - Demise POLARCUBE 16 Bus Rx Antenna 2 Copper Rod 1.4 1 200 - No - Demise POLARCUBE 17 Bus Deployment Claws +Z 4 Aluminum 6061 Block 0.2 6.1 8.9 8.7 No - Demise POLARCUBE 18 Bus CDH board 1 FR-4, Copper Plate 62 74.2 169.2 11.6 No - Demise POLARCUBE 19 Bus EPS Main board 1 FR-4, Copper Plate 56 78.3 82.5 12.4 No - Demise POLARCUBE 20 Bus COM RF board 1 FR-4, Copper Plate 50 78.3 82.5 11.3 No - Demise POLARCUBE 21 Bus EPS Li-ion cell 4 Li-Ion Rod 46 18.4 66.5 - No - Demise POLARCUBE 22 Bus ACS Main board 1 FR-4, Copper Plate 45 78.3 82.5 5.1 No - Demise POLARCUBE 23 Bus COM Digital board 1 FR-4, Copper Plate 44 78.3 82.5 8.7 No - Demise 61

POLARCUBE 24 Bus Reaction Wheel 3 Aluminum 6061 Disk 21.2 57.2 5.1 - No - Demise POLARCUBE 25 Bus ACS Star Camera board 1 FR-4, Copper Plate 25 44.5 82.6 6.3 No - Demise POLARCUBE 26 Bus GPS board 1 FR-4, Copper Plate 18 46 71 13 No - Demise POLARCUBE 27 Bus EPS battery bracket 2 Aluminum 6061 Box Frame 18 26.5 80.7 12 Yes 1205º Demise POLARCUBE 28 Bus Star Camera Bracket 1 Aluminum 6061 Plate 15.3 22 82.5 10.5 Yes 1205º Demise Bus ACS Motor Driver 1 FR-4, Copper Plate 15.2 40.6 54.6 8.7 No - Demise POLARCUBE 29 board POLARCUBE 30 Bus Magnetic Torque Rod 3 Steel, Copper Rod 12.5 12 50 - No - Demise POLARCUBE 31 Bus RWM Bracket 3 Aluminum 6061 Plate 10.4 60 66.8 1.6 No - Demise POLARCUBE 32 Payload Board Enclosures 1 Aluminum 6061 Box 277.54 86.03 103.63 50.8 No - Demise POLARCUBE 33 RAD_RF_Oscillator 1 Brass Box 176.72 28.7 60.69 22.1 No - Demise POLARCUBE 34 RAD_RF_Tuner 1 Brass Box 5 19.05 31.45 19.05 No - Demise POLARCUBE 35 RAD_RF_PIN-SwitchDiode 1 Brass Box 63 18.39 30.95 5.99 No - Demise POLARCUBE 37 RAD_RF_Mixer 1 Brass Box 72 30.48 31.75 20.32 No - Demise POLARCUBE 38 Isolater Plate 1 Aluminum 6061 Plate 40 85.52 86.03 3.05 Yes 1205º Demise POLARCUBE 39 Payload IF Board 1 FR-4, Copper Plate 46 66.95 103.89 8.7 No - Demise POLARCUBE 40 Payload VA Board 1 FR-4, Copper Plate 52 66.95 103.89 8.7 No - Demise POLARCUBE 41 Payload Digital Board 1 FR-4, Copper Plate 43 80.77 81.99 8.7 No - Demise POLARCUBE 42 Payload Adapter Board 1 FR-4, Copper Plate 30 73.79 73.79 8.7 No - Demise Aluminum 6061, Bus frangibolt assembly 1 Tube 11.7 21 25 22.8 Yes 3034º Yes POLARCUBE 43 Titanium Bus Star Camera Lens & 1 Glass & Steel Disk/Rod 10.8 22 18.9 - No - Demise POLARCUBE 44 Frame POLARCUBE 45 Bus Star Camera Baffle 1 Aluminum 6061 Tube 10.1 25.2 27.2 - No - Demise POLARCUBE 46 Bus GPS wire harness 1 Copper Wires 8.5 No - Demise POLARCUBE 47 Bus EPS wire harness 1 1 Copper Ribbon 6 25 350 2 No - Demise Coiled Bus Deployment Spring 2 Spring Steel 3.5 12.9 8.2 - No - Demise POLARCUBE 48 Sheet POLARCUBE 49 Bus RF Cabling 3 Copper Wire 3 No - Demise POLARCUBE 50 Bus Standoffs 12 Steel (304, 316) Rod 3 3.7 6.5 - No - Demise 62

POLARCUBE 51 Bus Tx Antenna Bracket 2 Aluminum 6061 Plate 2.8 16.8 36.4 7.6 No - Demise POLARCUBE 52 Bus Reaction Wheel Motor 3 Multiple (Steel) Rod 2.5 6 20 - No - Demise POLARCUBE 53 Bus board clips 1 15 Aluminum 6061 Block 1.8 7.6 18.2 6.8 No - Demise POLARCUBE 54 Bus EPS wire harness 2 2 Copper Ribbon 1.5 20 50 4 No - Demise POLARCUBE 55 Bus Dep Spring Spool 2 Aluminum 6061 Tube 1.5 9 8.2 - No - Demise .125 - Bus SS Fasteners 298 Steel (304, 316) Rod 1 #0, #2, #4 - No - Demise POLARCUBE 56 .5" POLARCUBE 57 Bus board clips 2 6 Aluminum 6062 Block 0.9 5.7 10.8 6.4 No - Demise POLARCUBE 58 Bus Spring Plunger 2 Steel 316 Rod 0.5 3 10.6 - No - Demise 63

Appendix J. ELaNa-20 Component List by CubeSat: Q-PACE Mass Diameter Melting Item Body Length Height High CUBESAT Name Qty Material (g) / Width Temp Survivability Number Type (mm) (mm) Temp (total) (mm) (Fº) Q-PACE 1 QPACE 3U CubeSat - 6061-T6 (SS) Box 453.67 - - - No - Demise Q-PACE 2 QPACE Structure - 6061-T6 (SS) Box 66.43 453.67 99.262 99.002 No - Demise Q-PACE 3 Super Structure Rails 4 6061-T6 (SS) Flat Plate 8.88 66.43 17.89 17.89 No - Demise Q-PACE 4 Solar Panels - Flat Plate 8.88 92.075 79.375 No - Demise Q-PACE 5 S-Band Patch Antenna 1 - Flat Plate 3 17.98 93.98 93.98 No - Demise Quintbass Guitar Antenna Q-PACE 6 1 - - 3 700 0.91 0.91 No - Demise String Q-PACE 7 Rail Mount Fasteners 4 6061-T6 (SS) Box No - Demise Q-PACE 8 Battery System 1 - - - - - - No - Demise Q-PACE 9 Batteries 6 Lithium Ion Cylinder 24.04 29 40.64 40.64 No - Demise Q-PACE 10 Battery PCB 1 PCB Box 40 24.04 83 83 No - Demise Q-PACE 11 GoPro Hero3+ Black 1 Various Box 71 40 41 60 No - Demise Q-PACE 12 CCDR - system - 45 71 - - No - Demise Q-PACE 13 Raspberry Pi 1 PCB Box 45 45 83 83 No - Demise Q-PACE 14 Interface Eletronics 1 PCB Box 45 83 83 No - Demise Q-PACE 15 WTC/PD PCB 1 PCB Box 42 42 83 83 No - Demise Q-PACE 16 MPPT/ Charger PCB 1 PCB Box 42 42 83 83 No - Demise Experiment Control Q-PACE 17 1 PCB Box 147 42 83 83 No - Demise Electronic PCB include d in Q-PACE 18 Comms/RF Module 1 PCB Box 147 89 89 No - Demise structur e included Q-PACE 19 ETC Structure 1 6061-T6 (SS) Box 14.5 in - - No - Demise structure Q-PACE 20 12 V Push Solonoids Alloy Steel Box 14.5 14 13 No - Demise 64

Alloy Steel Q-PACE 4 Wire Mimi Stepper Motor 1 Box No - Demise 21 2.4 4.5 6 4 Wire Mimi Stepper Q-PACE 1 6061-T6 (SS) Box No - Demise 22 Motorw/ Gear 40 2.4 11 6 Q-PACE 23 Glass Plate 1 Glass Flat Plate 40 2.5 2.1 No - Demise Q-PACE 24 Cabling various PCB - 453.67 - - - No - Demise 65

Appendix K. ELaNa-20 Component List by CubeSat: RadFXSat-2 Mass Diameter Melting Item Body Length Height High CUBESAT Name Qty Material (g) / Width Temp Survivability Number Type (mm) (mm) Temp (total) (mm) (Fº) RadFXSat-2, updated RadFXSat-2 1 - - box (1U) - - - - - - Demise August 30, 2016. Aluminum 5052 sheet w/ RadFXSat-2 2 CubeSat Walls 2 32. 200. 108. 1. - - Demise H32 bends RadFXSat-2 3 Solar Panels (+Z, -Z) 2 Fiberglass sheet 42. 97. 97. 1.6 - - Demise Solar Panels (+X, -X, +Y, - RadFXSat-2 4 4 Fiberglass sheet 43. 81. 108. 1.6 - - Demise Y) stepped RadFXSat-2 5 Rail Ends 8 Aluminum 6061 4. 21. 21. 10. - - Demise box RadFXSat-2 6 Antenna 1 Nitinol wire 1. 0.5 165. - - - Demise RadFXSat-2 7 Antenna 1 Nitinol wire 1. 0.5 530. - - - Demise RadFXSat-2 8 Antennae Posts 2 Copper cylinder 1. 5. 4. - - - Demise RadFXSat-2 9 Antennae Posts 2 Fiberglass cylinder 1. 5. 4. - - - Demise RadFXSat-2 10 Antennae Posts 4 Delrin cylinder 1. 5. 4. - - - Demise RadFXSat-2 11 PCB Stack mounts 12 Delrin box 1. 14. 14. 7. - - Demise RadFXSat-2 12 PCB Stack screws 4 stainless steel cylinder 1.3 2.8 98. - - - Demise RadFXSat-2 13 VUC PCB 1 Fiberglass sheet 38. 95. 95. 1.6 - - Demise RadFXSat-2 14 REM PCBs 3 Fiberglass sheet 45. 95. 95. 1.6 - - Demise NiCad "A" RadFXSat-2 15 Batteries 6 cylinder 31. 17. 49. - - - Demise battery RadFXSat-2 16 Hysteresis Rods 2 Permalloy cylinder 4.8 3.2 70. - - - Demise Battery PCB (excl RadFXSat-2 17 1 Fiberglass sheet 50. 95. 95. 1.6 - - Demise Batt,Hyst,Tan) RadFXSat-2 18 MPPT PCB (excl Lead,Tan) 1 Fiberglass sheet 49. 95. 95. 1.6 - - Demise RadFXSat-2 19 IHU PCB (excl Tan) 1 Fiberglass sheet 46. 95. 95. 1.6 - - Demise ICR PCB (pop excl RF RadFXSat-2 20 1 Fiberglass sheet 48. 95. 95. 1.6 - - Demise Shield) 66

RX/TX PCB (pop excl RF RadFXSat-2 21 1 Fiberglass sheet 44. 95. 95. 1.6 - - Demise Shield,Tan) RadFXSat-2 22 RF Shields 2 Copper sheet 18. 80. 80. 0.5 - - Demise hollow RadFXSat-2 23 PCB Standoffs 20 Aluminum 6061 0.5 6.4 8.2 - Yes 1205º Demise cylinder hollow RadFXSat-2 24 PCB Standoffs 8 Copper 0.8 4.8 8.2 - - - Demise cylinder hollow RadFXSat-2 25 PCB Standoffs 8 Delrin 0.3 6.4 8.2 - - - Demise cylinder RadFXSat-2 26 Magnet 1 Neodymium cylinder 5.3 6.4 19. - - - Demise RadFXSat-2 27 Fasteners, cabling, misc 1 varies - 33. - - - - - Demise RadFXSat-2 28 Lead ballast 1 Lead sheet 210. 74.9 74.9 3.1 - - Demise RadFXSat-2 29 Tantalum radiation shield 2 Tantalum sheet 1.8 9. 24. 0.5 - - Demise RadFXSat-2 30 Tantalum radiation shield 1 Tantalum sheet 1.9 15. 15. 0.5 - - Demise RadFXSat-2 31 Tantalum radiation shield 1 Tantalum sheet 1.1 9. 15. 0.5 - - Demise RadFXSat-2 32 Tantalum radiation shield 1 Tantalum sheet 0.8 6. 15. 0.5 - - Demise RadFXSat-2 33 Tantalum radiation shield 2 Tantalum sheet 0.9 8. 13. 0.5 - - Demise RadFXSat-2 34 Tantalum radiation shield 2 Tantalum sheet 0.6 7. 10. 0.5 - - Demise RadFXSat-2 35 Tantalum radiation shield 2 Tantalum sheet 0.3 4. 9. 0.5 - - Demise RadFXSat-2 36 Tantalum radiation shield 1 Tantalum sheet 0.4 6. 8. 0.5 - - Demise RadFXSat-2 38 Tantalum radiation shield 4 Tantalum sheet 0.3 5. 6. 0.5 - - Demise RadFXSat-2 39 Tantalum radiation shield 5 Tantalum sheet 0.2 5. 5. 0.5 - - Demise RadFXSat-2 40 Tantalum radiation shield 6 Tantalum sheet 0.2 4. 5. 0.5 - - Demise RadFXSat-2 41 Tantalum radiation shield 2 Tantalum sheet 0.1 4. 4. 0.5 - - Demise RadFXSat-2 42 Tantalum radiation shield 9 Tantalum sheet 0.1 3. 3. 0.5 - - Demise RadFXSat-2 43 Tantalum radiation shield 6 Tantalum sheet 0.1 2. 3. 0.5 - - Demise RadFXSat-2 44 Tantalum radiation shield 8 Tantalum sheet 0. 2. 2. 0.5 - - Demise 67

Appendix L. ELaNa-20 Component List by CubeSat: SHFT-2 Diamet Melting Item Body Mass (g) er/ Length Height High CUBESAT Name Qty Material Temp Survivability Number Type (total) Width (mm) (mm) Temp (Fº) (mm) SHFT-2 1 3U CubeSat 1 Box 5100 113.1 365.8 112.48 - - Demise SHFT-2 2 CubeSat Structure 1 Al 7075-T651 Box 378.7 100 270.7 100 - - Demise SHFT-2 3 Antenna - deployed 4 Steel, Ultem, Al 6061 Boom 458.1 19.05 6000 0.28 - - Demise SHFT-2 4 Solar Panels - deployed 2 FR4, glass, Al 6061 Flat Plate 305 138.38 326.49 57.25 - - Demise SHFT-2 5 ADCS 1 Al 6061 Box 895 100 100 50 Yes 1205º Demise UHF/GPS Antenna System - Al 6061, brass, RO3006 SHFT-2 6 1 Box 260.3 274 274 115.42 - - Demise deployed 005 R3 AD350A, RO450F, SHFT-2 7 S-Band Antenna 1 Box 75 83.82 83.82 5.08 - - Demise RO4003C SHFT-2 8 Rails 2 Al 7075-T651 Flat Plate 39.9 13.5 366 2.95 Yes 1175º Demise SHFT-2 9 IXC/GPS Board 1 Polyimide Box 107.2 95.88 90.17 15.75 - - Demise SHFT-2 10 SBC Board 1 Polyimide Flat Plate 88.5 95.88 90.17 10.9 - - Demise SHFT-2 11 EPS Boards with Spacers 1 Polyimide, Al 6061 Box 218.6 95.88 90.17 24.94 - - Demise Polyimide, Al 6061, SHFT-2 12 Battery Assembly 1 Box 298.6 95.88 90.17 27.35 - - Demise 2200SF gap pad, Li Ion OFHC Copper, Al 6061, SHFT-2 13 Radio 1 Box 576 96.65 96.65 30.91 - - Demise Polyimide SHFT-2 14 Payload Boards 1 Polyimide, Al 7075 Box 1093.9 116 96.65 76 - - Demise 18-8 SSTL, 316 SSTL, <1 g/item 3 (head SHFT-2 15 Internal Fasteners 85 cylinder 10 - - - Demise Alloy Steel 85 g total 5mm) <1 g/item 3 (head SHFT-2 16 External Fasteners 134 18-8 SSTL, 316 SSTL cylinder 10 - - - Demise 134 g total 5mm) SHFT-2 17 External Covers 6 Al 6061 flat plate 3.4 (each) 1.60 20 40 - - Demise <50g SHFT-2 18 Internal Cabling Copper Alloy wires 0.5 150 - - - Demise (total) 68


Document Created: 2017-04-20 12:09:57
Document Modified: 2017-04-20 12:09:57
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