ODAR Rev E

0353-EX-CN-2017 Text Documents

Boston University

2018-04-03ELS_207463

ELVL-2017-0044671 April 3, 2018 Orbital Debris Assessment for The CubeSats on the ELaNa-XIX Mission per NASA-STD 8719.14A (FCC) Rev E

Signature Page n. Reviewer, NASA KSC VA—H10 [(> Justin Treptow, 6!{al)'st & Mission Manager, NASA KSC VA—G2

National Aeronautics and Space Administration John F. Kennedy Space Center, Florida Kennedy Space Center, FL 32899 ELVL-2017-0044671 Reply to Attn of: VA-H1 April 3, 2018 TO: Justin Treptow, LSP Mission Manager, NASA/KSC/VA-G2 FROM: Justin Treptow, NASA/KSC/VA-G2 SUBJECT: Orbital Debris Assessment Report (ODAR) for the ELaNa-XIX Mission (FCC) Rev E REFERENCES: A. NASA Procedural Requirements for Limiting Orbital Debris Generation, NPR 8715.6A, 5 February 2008 B. Process for Limiting Orbital Debris, NASA-STD-8719.14A, 25 May 2012 C. Armstrong, Jason; TriSept Corp. “ODAR info” email, Oct 20, 2016. D. McKissock, Barbara, Patricia Loyselle, and Elisa Vogel. Guidelines on Lithium- ion Battery Use in Space Applications. Tech. no. RP-08-75. NASA Glenn Research Center Cleveland, Ohio E. UL Standard for Safety for Lithium Batteries, UL 1642. UL Standard. 4th ed. Northbrook, IL, Underwriters Laboratories, 2007 F. Kwas, Robert. Thermal Analysis of ELaNa-4 CubeSat Batteries, ELVL-2012- 0043254; Nov 2012 G. Range Safety User Requirements Manual Volume 3- Launch Vehicles, Payloads, and Ground Support Systems Requirements, AFSCM 91-710 V3. H. HQ OSMA Policy Memo/Email to 8719.14: CubeSat Battery Non-Passivation, Suzanne Aleman to Justin Treptow, 10, March 2014 I. Electron LV-Payload Interface Control Document, ELVL-2016-0044579, Received October 24, 2016 The intent of this report is to satisfy the orbital debris requirements listed in ref. (a) for the ELaNa-19 primary mission payload. It serves as the final submittal in support of the spacecraft Safety and Mission Success Review (SMSR). Sections 1 through 8 of ref. (b) are addressed in this document; sections 9 through 14 fall under the requirements levied on the primary mission and are not presented here. This mission is being launch under an FAA commercial license and the FAA has the responsibility to address the OD mitigation requirements for the launch vehicle for the ELaNa-19 primary mission. 3

Rev A: • Initial Release Rev B: • Updates the ODAR with the removal of GEOStare and replaces them with ALBus. • Updates CHOMPTT battery holder survivabiity analysis resulting in a 6J reentry energy for those components. • Additional CONOPs have been updated for CubeSail identifying deployment of the system. All details alleviate concerns and strengthen their compliance with the NASA Orbital Debris policy. • ANDESITE Nodes have been added into orbit lifetime calculations, Probability of Collision, and mission deployment CONOPS. All details alleviate concerns and strengthen their compliance with the NASA Orbital Debris policy. Rev B2: • Identified on page 3 that FAA is responsible for LV OD mitigation requirements. Rev C: • Update NMTSat payload Extremely Low Resource Optical Identifier (ELROI) and component list, this update has no effect on analysis supporting the ODAR. Rev D: • Update ANDESITE Node deployment to reflect deployment at 350km altitude to reflect revised CONOPS. Node orbit lifetime shown to be 0.25 years in Table 4. Rev E: • Updated ANDESITE and CubeSail Mission Descriptions to reflect deploy of science objective below 350km. • Updated CubeSail orbit lifetime (Table 4) and Section 8 Req 4.8-1 Tether Analysis as a result of CONOPS redesigned for tether deployment to occur below ISS at 350km altitude. • Additional row in Table 4 identifying CubeSail orbit life with sail deployment at 350km. • Appendix O was added to capture CubeSail CONOPS documentation. • Update Table 8: Requirement 4.7-1 Compliance by CubeSat to correct CHOMPTT probability of casualty to show 1:0. Revision Summary ELaNa-19 ODAR has continually met the NASA 8719.14A Requirements and continues to be in compliance. Updates to the ODAR have largely been driven by FCC request for updated evidence that exceeds NASA requirements. 4

The following table summarizes the compliance status of the ELaNa XIX (ELana-19) auxiliary payload mission flown on ELaNa-19. The fourteen CubeSats comprising the ELaNa-19 mission are fully compliant with all applicable requirements. Table 1: Orbital Debris Requirement Compliance Matrix Requirement Compliance Assessment Comments 4.3-1a Not applicable No planned debris release 4.3-1b Not applicable No planned debris release 4.3-2 Not applicable No planned debris release 4.4-1 Compliant On board energy source (batteries) incapable of debris-producing failure 4.4-2 Compliant On board energy source (batteries) incapable of debris-producing failure 4.4-3 Not applicable No planned breakups 4.4-4 Not applicable No planned breakups 4.5-1 Compliant 4.5-2 Not applicable 4.6-1(a) Compliant Worst case lifetime 5.9 yrs 4.6-1(b) Not applicable 4.6-1(c) Not applicable 4.6-2 Not applicable 4.6-3 Not applicable 4.6-4 Not applicable Passive disposal 4.6-5 Compliant 4.7-1 Compliant Non-credible risk of human casualty 4.8-1 Compliant ELaNa-19 includes the CubeSail mission, containing a 250m solar sail / tether 5

Section 1: Program Management and Mission Overview The ELaNa-19 mission is sponsored by the Human Exploration and Operations Mission Directorate at NASA Headquarters. The Program Executive is Jason Crusan. Responsible senior scientific / management personnel are as follows: ANDESITE: Walsh Brian, Principle Investigator CeREs: Summerlin Errol, Principle Investigator CHOMPTT: Conklin John, Principle Investigator CubeSail: Carroll David, Principle Investigator DaVinci: Finman Lorna, Principle Investigator ISX: Bellardo John, Principle Investigator NMTSat: Jorgensen Anders, Principle Investigator RSat: Kang Jin, Principle Investigator Shields-1: Thomsen Laurence, Principle Investigator STF-1: Grubb Matthew, Principle Investigator TOMSat EAGLESCOUT: Hattersley Bonnie, Principle Investigator TOMSat R3: Hattersley Bonnie, Principle Investigator GEOStare: de Vries Wim, Principle Investigator SHFT-1: Lux Jim, Principle Investigator ALBus: Kathryn Shaw, Project Manager 6

Program Milestone Schedule Task Date CubeSat Selection CSLI award February 2016 CubeSat Mission Readiness review: December 4-7th 2017 CubeSat delivery to TriSept April 9-13, 2018 CubeSat integration with LV May 10, 2018 Launch date May 30, 2018 Figure 1: Program Milestone Schedule The ELaNa-19 mission will be launched as the primary payload on the VCLS RocketLabs ELaNa-19 mission on an US made Electron launch vehicle from New Zealand range. The ELaNa-19 compliment, will deploy 14 pico-satellites (or CubeSats). The CubeSat slotted position is identified in Table 2: ELaNa-19 CubeSats. The ELaNa- 19 manifest includes: ANDESITE, CeREs, CHOMPTT , CubeSail, DaVinci, ISX, NMTSat, RSat, Shields-1, STF-1, TOMSat EAGLESCOUT, TOMSat R3, SHFT-1, and ALBUS. The current launch date opens May 30, 2018 extending till June 7, 2018. The 14 CubeSats are to be ejected from the Electron shortly after the launch, placing the CubeSats in an orbit approximately 500 X 500 km at inclination of 85 deg (ref. (i)). Each CubeSat ranges in sizes from a 10 cm x 10cm x 30 cm to 10 cm x 20 cm x 30 cm, with masses from about 1.56 kg to ~5.13 kg total. The CubeSats have been designed and universities and government agencies and each has their own mission goals. 7

Section 2: Spacecraft Description There are 14 CubeSats flying on the ELaNa-19 Mission. Table 2: ELaNa-19 CubeSats outlines their generic attributes. Table 2: ELaNa-19 CubeSats CubeSat CubeSat CubeSat Masses CubeSat size Quantity Names (kg) 1 6U (24 cm x 36.3 cm x 11 cm) ANDESITE 10.36 1 3U (10 cm x 10 cm x 34 cm) CeREs 4.50 1 3U (10 cm x 10 cm x 34 cm) CHOMPTT 3.59 1 3U (10 cm x 10 cm x 31 cm) CubeSail 3.52 1 3U (11.7 cm x 11.3 cm x 34.05 cm) DaVinci 3.38 1 3U (11.2 cm x 11.1 cm x 34.05 cm) ISX 3.50 1 3U (10 cm x 10 cm x 34 cm) NMTSat 2.48 1 3U (11.3 cm x 11.3 cm x 34.05 cm) Rsat 3.07 1 3U (10.6 cm x 10.6 cm x 34.05 cm) Shields-1 6.93 1 3U (11.5 cm x 11.5 cm x 34.05 cm) STF-1 3.01 TOMSat 1 3U (10.3 cm x 10.3 cm x 34.05 cm) 5.03 EAGLESCOUT 1 3U (10.3 cm x 10.3 cm x 34.05 cm) TOMSat R3 4.66 1 3U (11.3 cm x 11.2 cm x 36.6 cm) SHFT-1 5.10 1 3U (34.05 x 11.6 x 11.6 cm3) ALBus 2.91 The following subsections contain descriptions of these 14 CubeSats. 8

ANDESITE - Boston University – 6U Figure 2: ANDESITE System and Expanded View Figure 3: ANDESITE Sensor Node Deployment & Node Expanded View Figure 4: Sensor Node Expanded View OVERVIEW The design of ANDESITE relies on deploying several small “sensor nodes'' from a main spacecraft—a 6U “mule” designed to comply with CubeSat Canisterized Satellite Dispenser (CSD) standards. Each sensor node holds a magnetometer that will provide three-axis magnetic field measurements with roughly ten nanotesla accuracy. By distributing the sensor nodes spatially, the system measures relative variations of the field as it flies through the aurora. With Ampere's law from Maxwell's equations and a priori knowledge of Earth’s background magnetic field we can calculate and map the current densities due to energetic charged particles moving into and out of the atmosphere in the polar regions where the aurora occurs. 9

CONOPS ANDESITE consists of 8 identical deployable Sensor Nodes, and a 6U “data Mule.” All 9 satellites deploy from the launch vehicle with the Sensor Nodes contained in the 6U Mule (see the above Figure 1a). At the time of deployment from the launch vehicle, the attitude control system stabilizes the aggregate satellite using magnetic torque coils. When stabilized, the Mule will begin collecting and downloading magnetometer data. When the Mule has deorbited to 350 km altitude, mission control will command that the Sensor Nodes be ejected from the Mule, one pair per orbit. A higher drag to mass ratio will cause the ejected Sensor Nodes to continue lose altitude relative to the Mule, and move away from it. Each Sensor Node, 19.05 x 9.40 x 2.29 cm. cm, mass 380 g, contains its own electrical system, battery and solar panels. Following the Sensor Nodes data gathering phase of the mission, the Sensor Nodes will continue to move away from the Mule and one another, out of radio contact and having no contact will shut down, while the main 6U will remain active to downlink data through the GlobalStar network. The Sensor Nodes will deorbit within about 3 months after being deployed from the Mule, while the Mule will continue collecting and downloading single point magnetometer data for the remainder of the mission. The Mule will stay in orbit for about 4 years total (see the Orbital Debris Assessment Report for details). Materials The primary CubeSat structure is made of aluminum 6061. The baseplate is made of aluminum 7075 and is hard anodized. The CubeSat contains all standard commercial off the shelf (COTS) materials, electrical components, PCBs and solar cells. It has eight deployable picosatellites that eject while in orbit, and two deployable solar panel wings that deploy upon exit of the Canesterized Satellite Dispenser (CSD). The picosatellites have an aluminum 6061 structure and PCBs for solar cells and on board electronics. Stainless steel 6-32 and 2-56 screws are used to fasten the CubeSat, and helicoils are inserted for back-out protection. Hazards There no pressure vessels, hazardous or exotic materials. Batteries The electrical power storage system consists of common Lithium-Ion Polymer batteries with over-charge/current protection circuitry provided by a Clyde Space EPS. Clyde Space battery part number C3-USM-5016-CS-30Wh. 10

CeREs -GSFC – 3U Figure 5: CeREs CubeSat Expanded View OVERVIEW CeREs is a 3U CubeSat carrying a single instrument to study radiation belt dynamics in support of the Van Allen Probes. Specifically, the detector, MeRIT, a combination of solid state detectors (SSDs) and avalanche photo diodes (APDs) will measure electrons with energies between 10keV and 10 MeV with extremely fast (5ms) cadence. This unprecedented measurement range comes from seamlessly combing SSD technology, sensitive to higher energy electrons with new APDs which are sensitive to lower energy electrons. The high measurement cadence is supported advanced application specific integrated circuits that can handle millions of events per second. Electrons at these energies precipitating over the poles can have sudden bursts of intensity that last only a few microseconds called microbursts. These were first seen by the SAMPEX mission with a 20 ms cadence for electrons greater than 1 MeV, but because of the limited instrument capability, it is still unknown exactly how short these bursts can be and what the distribution of electron energies is within these events. Microbursts have intensities an order of magnitude larger than typical rates of precipitating electrons and one of the goals of the Van Allen Probes was to investigate the origins of these events. CeREs will help Van Allen Probes achieve this objective by 11

providing direct measurements of precipitating electrons that can be correlated with events observed on Van Allen Probes at lower latitudes along the same magnetic field line. CONOPS Upon Release, CeREs will power-up, deploy its solar arrays, and enter sun acquisition mode. It will then deploy its antenna and use its GPS to decide when to “beacon” to help with initial ground contact. Once initial ground contact is established, CeREs will begin science operations. These will consist of pointing the instrument toward zenith above ~60 degrees latitude and entering a power saving/sun acquisition mode at low latitudes on the night/day side respectively. Twice per day, power permitting, the sun acquisition mode will be interrupted for a 15 minutes ground contact with WFF. As the mission continues, power levels will be monitored to ensure that sufficient time is being allocated for power acquisition daily and the 60 degree latitude value will change as solar panel efficiencies and battery power degrades. The mission will generate and transmit up to 2.7 Gb of data daily that will consist of distribution functions of energetic electrons over 3-orders of magnitude in energy. Ground contacts, data acquisition rates, and the latitude at which science operations begin are all controlled via tables uploaded to the spacecraft regularly and can be changed in response to spacecraft status. Materials The primary CubeSat structure is made of Aluminum 6061-T6. The detectors are made of silicon and the shielding for the detectors is made of tungsten and aluminum. Instrument front end electronics and on-board processor cards are copper and FR4. The front end electronics also have a high voltage power supply that is housed in Urethane. The XB1 avionics package, includes lithium-ion batteries, C&DH processor, L3 Cadet Radio, and the ACS system. These are housed in an aluminum shell. The solar panels contain primarily FR4 and Aluminum with steel hinges. Hazards There are no pressure vessels, hazardous or exotic materials. Batteries The electrical power storage system consists of common Lithium-Ion batteries with under temperature (hardware set), cell balancing, under voltage and over voltage protection features. Specs on the EPS system can be found here (http://bluecanyontech.com/wp- content/uploads/2016/07/PowerSystems_F.pdf). 12

CHOMPTT-University of Florida – 3U Figure 6: CHOMPTT Expanded View Figure 7: CHOMPTT Zenith (left) and Nadir (right) Views 13

Figure 8: CHOMPTT Stowed View Overview CHOMPTT (CubeSat Handling of Multisystem Precision Time Transfer) is a CubeSat mission that will synchronize an atomic clock on a CubeSat with one on the ground with an accuracy of 200 ps by exchanging short laser pulses between the two. One limitation of radio frequency time-transfer is that it is susceptible to time-delay uncertainties in the ionosphere that can be difficult to model. This effect is inversely proportional to the emitted electromagnetic frequency squared and can therefore be greatly reduced by utilizing optical synchronization methods. The CHOMPTT satellite will maintain its time with a chip scale atomic clock (CSAC). When the satellite passes over a satellite laser ranging facility (SLR), the SLR facility emits a laser pulse toward the satellite. That pulse is time-stamped with respect to the ground clock when it leaves the SLR facility and after it reflects of off a retroreflector on the satellite, the returned pulse is time-stamped when it arrives back at the SLR facility with respect to the ground clock. An avalanche photodetector on the satellite simultaneously detects the pulse’s arrival time and time-stamps it with respect to the clock on the satellite with an event timer. The combination of these three timing measurements provides both the range between the SLR facility and CHOMPTT and the time offset between the ground clock and the space clock. The CHOMPTT mission is owned and operated by the University of Florida. The CHOMPTT satellite consists of a 1.5U EDSN/NODeS-derived CubeSat bus and a 1U OPTI (Optical Precision Timing Instrument) payload. NASA does not claim ownership of any experimental, developmental or operational equipment that involves the use of the electromagnetic spectrum for transmission, reception, or both that is developed or procured under this contract. The University of Florida’s use of any experimental, developmental or operational equipment that involves the use of the electromagnetic spectrum for transmission, reception, or both that is operated under this contract shall be under University of Florida’s discretion and control; NASA does not claim any authority over the operations of the electromagnetic spectrum systems. 14

CONOPS Upon deployment from the deployer, CHOMPTT will enter a safe-mode for 30 min. where all of the subsystems are nominally off. After the safe-mode period checks out, the spacecraft will power on, begin counting, beacon the spacecraft time every 60 s, and begin de-tumbling via magnetorquer for 90 min. Every 25 hour minor cycle, the spacecraft will autonomously acquire GPS data and downlink spacecraft data to the University of Florida RF ground station. UF will coordinate with a satellite laser ranging (SLR) facility located at Kennedy Space Center to perform a time transfer and RF uplink the time transfer schedule to the spacecraft. During a time transfer, the spacecraft will point nadir, turn on the laser beacon diode for SLR tracking, and turn on all of the payload subsystems. The spacecraft will be pulsed with a laser from the SLR facility until the scheduled time transfer is over, and the spacecraft will return to its nominal counting/beacon mode. Materials The primary CubeSat structure is made of Aluminum and contains a 1.5U EDSN/NODeS derived bus and a 1U UF Optical Precision Timing Instrument (OPTI). The EDSN/NODeS derived bus is custom with a few commercial off the shelf (COTS) components. The custom spacecraft materials are all spacecraft PCBs, all payload components, retroreflector array, TASC 1U solar panels, structures, and reaction wheel system. The COTS spacecraft materials are the GOMSpace P110 1U solar panels with magnetorquers, MEMSpace Sun Sensors, Pumpkin large aperture plate on the 1U nadir face, GPS patch antenna, GPS radio, lithium-ion batteries, Lithium-1 Radio, and StenSat Radio. 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. UL Listing information is as follows UL 1642. 15

CubeSail – UIUC/CUA – 3U Middle Plate Radio (2) Solar Panels (8) Torque Coil (10?) Power Board (2) Patch Antennas (2) Solar Sail C&DH Board (2) Batteries Structural Rails (8) Battery Board Figure 9: CubeSail Expanded View Overview The primary goal of the CubeSail mission is to demonstrate orbit raising from solar sail propulsion. A secondary goal is to then spin-up the satellites like a propeller with the sail extending between them. A final goal is to then deorbit the satellites using the same solar sail. CONOPS* Additional CONOPS clarification has been provided in Rev B seen below As stowed aboard the launch vehicle, the two sections of CubeSail are rigidly coupled by the separation release unit (SRU), and flexibly coupled by the solar sail film. Following a successful launch and orbit insertion of the satellite into near sun-synchronous orbit, communication with mission control will be initiated to verify satellite functionality. Next, a detumbling maneuver utilizing the magnetic torquers will commence. After detumbling, the CubeSail spacecraft will be monitored regularly until its orbit has decayed to an altitude of 350 km. This decay is anticipated to take approximately 2 years during which its instrumentation, communications, and ADCS will be tested extensively in its un-deployed state. Once the orbital altitude has decayed to 350 km or lower, a command is given for CubeSail to orient such that its sail will be perpendicular to Earth’s surface in the long dimension, and edge-on to the ram direction, and face-on to the sun direction after deployment. Once the satellite is stable in this attitude and diagnostic data has been reviewed, the ground station will command initiation of the programmed solar sail 16

deployment sequence, with the scheduled time for initiation specified in the command. The ground station at the University of Illinois campus is the only one that will be used to support this mission. At the scheduled time, the sail deployment initiates and takes place from beginning to end as a programmed sequence, and does not depend on real-time ground control. Each satellite section has a unique sequence of actions which must be executed during deployment. By incorporating appropriate delays in the sequence, sensitivity to clock synchronization has been reduced. On the ground communication pass prior to the intended deployment, both satellite buses will receive clock updates. Additional details of the CubeSail CONOPS can be found in Appendix O. Materials Satellite structure is made from AL60601T6, while the solar panels are Carbon fiber with an aluminum backing. The CubeSail payload is significantly aluminized mylar film. PCBs are made from FR-4 and using automotive grade or worse components. Hazards There are no hazardous systems on board. There are no pressure vessels nor thrusters nor any chemical reactants. Batteries The electrical power storage system consists of common lithium-ion batteries with over- charge/current protection circuitry. The charging system incorporates an MPPT logic. The lithium batteries carry the UL-listing number MH12210. 17

DaVinci - LCF Enterprises – 3U Figure 10: DaVinci Expanded View Overview The DaVinci mission is a 3U CubeSat being developed by North Idaho STEM Charter Academy in partnership with LCF Enterprises. The primary mission goal is STEM outreach, which will be achieved with the platform payloads. The payloads will be a basic imager to take photographs of the Earth, an amateur radio and a duplex radio modem to connect with the GlobalStar communications network. A morse code message will be communicated as the satellite orbits. CONOPS Upon deployment from the ISIS Quad pack, DaVinci will begin it’s separation sequence. All transmissions and deployments are delayed from 45 minutes from the satellite being deployed. During separation sequence the panels shall be deployed, following on from this DaVinci will minimize the platform angular rate before deploying the UHF/VHF antennas. At this point the initial communication with the ground station/globalstar network shall be made. At this point data will be analyzed to ensure a successful separation has occurred before beginning the primary mission mode. In this mode the satellite can take images and provide a link to the globalstar network via the platform Eyestar modem payload. Materials The primary CubeSat structure is made of Aluminum 6082. 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 Lithium Ion Polymer batteries with over-charge/current protection circuitry. UL Listing information is as follows UL1642. 18

ISX (Ionospheric Scintillation eXplorer) – Cal Poly, SLO – 3U Figure 11: ISX Expanded View Overview The Ionospheric Scintillation eXplorer (ISX) is a satellite developed by undergraduate and graduate students as part of the PolySat research group in collaboration with SRI. The satellite is sponsored by NSF. ISX will measure the scintillation of disrupts in ionospheric plasma tubules using DTV signals. ISX will study the multi-frequency radio wave propagation properties of intermediate-to-large scale ionospheric structures of Equatorial Spread F that cause rapid phase and amplitude fluctuation of transionospheric signals. CONOPS Upon deployment from the PPOD, ISX will power on. Approximately 15 minutes later, the antenna will deploy. 115 minutes after antenna deployment, the beacon will be activated and the satellite will be available to acquire with the ground station. Acquisition and verification of the correct orientation and rates of the satellite will take place one week into the mission. The payload will then start taking data for one year. Materials The structure is made of 6061-T6 Aluminum. The antenna is made of NiTi. The antenna route is made of Delrin. It contains standard commercial off the shelf (COTS) materials, electrical components, PCBs, and solar cells. Hazards There are no pressure vessels, hazardous or exotic materials. 19

Batteries The electrical power storage system consists of nine 3.7V 2600mAh Lithium-Ion 18650 batteries, model LR1865SK, with over-charge/current protection circuitry. There are three strings in parallel, with each string consisting of three batteries in series. UL Listing information is as follows BBCV2.MH48285. 20

NMTSat –New Mexico Institue of Mining and Technology – 3U+ Figure 12: NMTsat Transparent View Overview NMTSat is a 3U+ CubeSat developed by students at New Mexico Institute of Mining and Technology. Its mission is primarily educational. NMTSat contains the following instruments or experiments: two magnetometers (MAG), one Langmuir Plasma Probe (LPP), one GPS receiver for ionospheric occultation measurements (GAMMA), one electrical health monitoring experiment (EHM) which is integrated with the power control module (PCM), and one FPGA testbed, integrated with the C&DH, one Extremely Low Resource Optical Identifier (ELROI). CONOPS After deployment NMTSat will power up. A timer will start waiting a time (TBD) before deploying the antennas. NMTSat will then power up the PCM, including EHM, and the magnetometers and begin to collect housekeeping data from these. NMTSat will then begin to emit a identifying beacon signal for a designated amount of time and listen for commands. Ground commands to power up and down instruments are then expected as well as commands to download collected data. A watchdog timer is implemented in the power supply to power-cycle NMTSat to its initial configuration when the timer expires. Regular operation involves uplink of commands to configure the satellite and instruments, and to downlink collected data. 21

Materials The primary CubeSat structure is made of Aluminum 6061. 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 a P31u power-management unit made by GomSpace which uses common Li- batteries with over-charge/current protection circuitry. The design is based on heritage from the satellites AAU Cubesat and AAUSAT II. 22

RSat - United States Naval Academy – 3U Bus Frame Arm 2 Arm 1 Robotics Bay Figure 13: RSat Expanded View Overview RSat is a 3U (10 x 10 x 33 cm) cube satellite with two 60 cm, seven degree of freedom robotic arms fitted with manipulators. It is intended to latch onto a host satellite and maneuver, image, and potentially repair various components. The RSat launched through ELaNa XIX will be a free floating launch, intended to validate these capabilities and provide flight heritage and confidence for future launches. CONOPS Upon deployment from the PPOD, RSat will power up and attempt deploy its antenna. It will then wait until it has detumbled to less than 1" /$ before deploying the robotic arms. After deployment the arms will move through a series of test patterns designed to simulate various on-orbit tasks. These patterns will focus on precision, aiming for the ability to maneuver on another satellite with a minimum accuracy across the full range of motion. 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. The arms are made of a space suitable 3D printed material. 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. UL Listing information is as follows: UL1642. 23

Shields-1 NASA Langley Research Center – 3U Figure 14: Shields-1 Expanded View Overview The Shields-1 mission with passive attitude control is a technology demonstration for radiation shielding a CubeSat electronics and a radiation shielding experiment to measure the shielding performance with respect to aluminum. There is also a charge dissipation film resistance measurement. In Figure 1, there is a vault for the flight system electronics and a research payload. The satellite is a standard 3U form factor, approximately 10cm x 10cm x 34 cm and weighs 6.9 Kg. The vault section of the CubeSat takes approximately 1.2U of the 3U, with the rest of the area the research payload, which contains the shielding and charge dissipation film resistance experiments. The satellite has four Lithium-Ion batteries. Solar panels cover all 4 3U faces for battery charging. The satellite has an aluminum/ titanium/ tantalum structure for its vault. The research payload structure is made of aluminum with 2 aluminum/ titanium/ tantalum shielding samples and one aluminum titanium sample. During the 1 year mission, the satellite will take dosimetry data from 8 µdosimeters behind various shielding thicknesses, charge dissipation film resistance measurements, and experimental thermal measurements. The satellite will also be taking light and temperature readings from solar panel sensors. The satellite has a turnstile antenna system by ISIS AntS-A up to 55cm in length for each antenna, deployed after the launch vehicle ejects the satellites into orbit. The turnstile antennas are the only protrusions from the flat faces of the satellites (see Figure 1 above). 24

CONOPS Upon deployment from the PPOD, Shields-1 will power up after a 30 minute software timer delay and deploy the turnstile antenna. It will slowly self-orient its long axis in the direction of magnetic field lines over a period of days and spin using passive magnetic attitude control. The ground station is located at Wallops Island, Virginia. Upon initial ground station communication with Wallops Island, Shields-1, Mission Objective A, the Shields-1 Atomic Number (Z) Grade Radiation Shielding Research Experiments using total ionizing dose measurements with 7 µdosimeters in the Research Payload and 1 µdosimeter in the Vault along with thermal measurements, Figure 1, will be turned on and data will be collected four times per orbit. Mission Objective B, the vault µdosimeter, thermal and system telemetry measurements, including solar panel thermal and photodiode measurements will be combined to analyze the commercial system flight boards’ performance. Mission Objective C, the charge dissipation film resistance and thermal measurements will be taken a minimum of one time daily after the initial communication with the spacecraft. Mission Objectives A, B, and C are planned to last for at least a year. Materials The primary CubeSat research payload structure and antenna housing is made from aluminum, Figure 1. The Z-Grade Vault, figure 1, contains the FCPU and radio board, battery board, EPS, and two research payload boards. The Z-grade Vault is made of aluminum, titanium, and tantalum. There are two Z-grade radiation shielding material samples in the research payload section of the spacecraft, Figure 1. The charge dissipation film experiment, which is housed in the antenna housing structure, figure 1, contains 4 stainless steel electrodes, inside a commercial Ultem plastic housing. The Shields-1 electronics 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 Lithium Ion batteries with over- charge/current protection circuitry. UL Listing information is as follows: UL 1642. 25

STF-1 NASA IV&V and West Virginia University – 3U Figure 15: STF-1 Expanded View Overview The NASA IV&V objective of Simulation-to-Flight 1 (STF-1), is to demonstrate the utility of the NASA Operational Simulator for Small Satellites across the CubeSat development cycle, from concept planning to mission operations. The STF-1 mission will demonstrate a highly portable simulation and test platform that allows seamless transition of mission development artifacts to flight products. The experimental objectives of this mission are to advance engineering and physical- science research currently being developed at West Virginia University (WVU). Specifically, the STF-1 mission aims to enhance precise orbit determination with commercial GPS receivers, increase IMU performance in the CubeSat form-factor, test the durability and radiation tolerance of III-V Nitride based LEDs, and measure dynamic properties of the ionospheric plasma system. CONOPS Upon deployment from the PPOD, STF-1 will enter the power-up sequence and hold for 30 minutes before deployment of the UHF and Langmuir probe elements. 45 minutes after deployment from the PPOD the UHF radio will be activated for telemetry to be transmitted to the Wallops Island ground station. After initial checkout with the ground station, and at which point the solar panels have sufficiently charged the batteries, STF-1 will enter the experimental mode. In this mode the spacecraft will make decisions on which experiment to execute, based on its position, power available, and experiment priority. The highest priority experiment at the beginning of the operations will be the LED experiment, in order to provide a baseline measurement of the LED performance to be compared with subsequent measurements. 26

Materials The primary structure is made of Aluminum 6082, with body mounted solar panels assembled from PCBs, Kapton adhesive, and commercial solar cells. Internally are a combination of commercial off the shelf (COTS) materials, electrical components, PCBs, and experimental payloads developed at WVU. Hazards There are no pressure vessels, hazardous or exotic materials. Batteries The electrical power storage system consists of common Lithium Ion Polymer batteries with over-charge/current protection circuitry. 27

TOMSat: EAGLESCOUT / R3 - Aerospace Corporation -3U Figure 16:One of two AC11/TOMSat spacecraft with solar panels deployed. Overview & CONOPS The AeroCube 11/Testbed for Optical Missions Satellite (AC11/TOMSat) program consists of two nearly-identical spacecraft that will demonstrate the technological capability of two imaging sensors. One satellite will host a pushbroom time delay integration (TDI) sensor that will provide normalized difference vegetation index (NVDI) data for comparison to NVDI provided by Landsat’s Operational Land Imager (OLI). The second AC11/TOMSat spacecraft will host an SB-501 focal plane array that will image terrestrial, lunar, and stellar targets. Both satellites will have a laser communication downlink. The goal of AC11/TOMSat is to show that these sensors perform comparably to flagship missions, such as Landsat. Materials The AC11/TOMSat spacecraft are 3U CubeSats with outer dimensions of 34 cm x 11 cm x 11 cm. Deployable solar panels extend off the long axis of the spacecraft with dimensions 34 cm x 10 cm. The exterior bus is made from 6061-T6 aluminum and houses all payload and electronics components. The nadir face contains an earth sensor and a sun sensor for attitude determination, a fish-eye camera, laser collimator and uplink receiver, and a radio patch antenna. The zenith face also contains a radio patch antenna as well as two star trackers. The payload for each spacecraft is a custom-made telescope made from aluminum, glass lenses, and titanium spacers and uses about 1.5U of space. A radiator is built into the bus to help the payload maintain proper temperatures. About 1U is dedicated to the avionics block, which houses mission electronics, reaction wheels, batteries, and data storage. These components share flight heritage with previous AeroCube launches. A significant portion of AC11/TOMSat’s flight hardware is derived from earlier AeroCube spacecraft already in orbit. 28

Hazards There are no pressure vessels, hazardous or exotic materials. Batteries Power for the AC11/TOMSat spacecraft is generated by solar cells mounted onto panels that will be deployed from both sides of the bus, as well as cells affixed to the spacecraft bus. These cells are capable of producing up to 23 W of power. Power is stored on-board with lithium-ion batteries. The satellite has 4 batteries mounted in an aluminum 6061-T6 structure as a unit and are shock and thermally isolated by a low-outgassing rubber grommet. Each battery is composed of two cells. Two batteries are rated at 9 W-hr while the other two are rated at 6 W-hr, for a total of 30 W-hr on the spacecraft. Table 3: TOMSat Battery Specs Model Number Number Manufacturer Energy Stored (UL Listing) of Cells <=9 W-hr per cell ICR18650H Molicel 2 (2 batteries total) <=6 W-hr per cell IBR18650BC Molicel 2 (2 batteries total) The batteries are consumer-oriented devices. The batteries have been recognized as UL tested and approved. UL recognition has been determined through the UL Online Certifications Directory, which clearly shows that these cell batteries have undergone and passed UL Standards. Furthermore, safety devices incorporated in these batteries include pressure release valves, over-current charge protection, and over-current discharge protection. 29

SHFT-1 – DARPA / STO - 3U Figure 17: SHFT 3U Cube-sat Expanded View Figure 18: SHFT 3U Cube-sat Deployed view with 3 meter HF antennas Figure 19: SHFT 3U Cube-sat Stowed configuration 30

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). 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. 31

ALBus – NASA Glenn Space Flight Center – 3U CubeSat Figure 20: ALBus Stowed View Figure 21: ALBus Expanded/Deployed View 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 32

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. 33

Section 3: Assessment of Spacecraft Debris Released during Normal Operations The assessment of spacecraft debris requires the identification of any object (>1 mm) expected to be released from the spacecraft any time after launch, including object dimensions, mass, and material. The section 3 requires rationale/necessity for release of each object, time of release of each object, relative to launch time, release velocity of each object with respect to spacecraft, expected orbital parameters (apogee, perigee, and inclination) of each object after release, calculated orbital lifetime of each object, including time spent in Low Earth Orbit (LEO), and an assessment of spacecraft compliance with Requirements 4.3-1 and 4.3-2. No releases are planned on the ELaNa-19 CubeSat mission therefore this section is not applicable.

Section 4: Assessment of Spacecraft Intentional Breakups and Potential for Explosions. There are NO plans for designed spacecraft breakups, explosions, or intentional collisions on the ELaNa-19 mission. The probability of battery explosion is very low, and, due to the very small mass of the satellites and their short orbital lifetimes the effect of an explosion on the far-term LEO environment is negligible (ref (h)). The CubeSats batteries still meet Req. 56450 (4.4-2) by virtue of the HQ OSMA policy regarding CubeSat battery disconnect stating; “CubeSats as a satellite class need not disconnect their batteries if flown in LEO with orbital lifetimes less than 25 years.” (ref. (h)) ELaNa-19 manifest one, 6U CubeSats which are not included in the 3U or smaller mentioned in ref. (h). However, this CubeSat has protective circuitry in their designs and COTS components. ANDESITE’s EPS and battery system has over-current poly switch protection, over- current bus protection, and battery under-voltage protection built into the EPS system. The ANDESITE CubeSat use UL listed battery cells. Limitations in space and mass prevent the inclusion of the necessary resources to disconnect the battery or the solar arrays at EOM. However, the low charges and small battery cells on the CubeSat’s power system prevents a catastrophic failure, so that passivation at EOM is not necessary to prevent an explosion or deflagration large enough to release orbital debris. Assessment of spacecraft compliance with Requirements 4.4-1 through 4.4-4 shows that with a maximum cubesat lifetime of 5.9 years maximum the ELaNa-19 CubeSat is compliant. 35

Section 5: Assessment of Spacecraft Potential for On-Orbit Collisions Calculation of spacecraft probability of collision with space objects larger than 10 cm in diameter during the orbital lifetime of the spacecraft takes into account both the mean cross sectional area and orbital lifetime. The largest mean cross sectional area (CSA) among the fourteen CubeSats is that of the CubeSail CubeSat with solar sail / tether deployed (250m X 0.08m solar sail): Figure 22: CubeSail Deployed Config ∑ +/01'2& ,0&' [5 ∗ (8 ∗ 9) + 3 ∗ (8 ∗ <)] %&'( *+, = = 3 3 Equation 1: Mean Cross Sectional Area for Convex Objects (,>'? + ,@ + ,@ ) %&'( *+, = 5 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 D for component dimensions used in these calculations The CubeSail (3.52 kg) orbit at deployment is 500km apogee altitude by 500 km perigee altitude, with an inclination of 85 degrees. With an area to mass ratio of 2.853 m2/kg, DAS yields < 0.1 years for orbit lifetime for its deployed state, which in turn is used to obtain the collision probability. Even with the variation in CubeSat design and orbital 36

lifetime ELaNa-19 CubeSats see an average of 0.00000 probability of collision. All CubeSats on ELaNa-19 were calculated to have a probability of collision of 0.00000. Table 4 below provides complete results. There will be no post-mission disposal operation. As such the identification of all systems and components required to accomplish post-mission disposal operation, including passivation and maneuvering, is not applicable. 37

Table 4: CubeSat Orbital Lifetime & Collision Probability Stowed Deployed Area-to Orbital Probability Mean C/S Area-to Orbital Probability of Component CubeSat Mass (kg) Mean C/S Area (m^2) Mass (m^2/kg) Lifetime (yrs) of collision (10^X) Area (m^2) Mass (m^2/kg) Lifetime (yrs) collision (10^X) ANDESITE 10.36 0.076 0.007 5.3 0.00000 0.108 0.016 4.1 0.00000 ANDESITE – Node* 0.452 - - - - 0.012 0.025 0.25 0.00000 CeREs 4.50 0.039 0.009 5.0 0.00000 0.074 0.016 4.1 0.00000 CHOMPTT 3.59 0.039 0.011 4.6 0.00000 0.041 0.012 4.5 0.00000 CubeSail 3.52 0.036 0.010 4.7 0.00000 CubeSail Sail deploy delayed till 350km alt** CubeSail Sail Deploy ** 3.52 - - - - 10.036 2.851 ~2 days 0.00000 DaVinci 3.38 0.046 0.014 4.3 0.00000 0.101 0.030 3.5 0.00000 ISX 3.50 0.044 0.013 4.4 0.00000 0.045 0.013 4.4 0.00000 NMTSat 2.48 0.042 0.017 4.3 0.00000 0.049 0.020 4.2 0.00000 Rsat 3.07 0.045 0.015 4.2 0.00000 0.063 0.020 3.9 0.00000 Shields-1 6.93 0.042 0.006 5.9 0.00000 0.049 0.007 5.5 0.00000 STF-1 3.01 0.047 0.016 4.1 0.00000 0.049 0.016 4.1 0.00000 TOMSat EAGLESCOUT 5.03 0.041 0.008 5.1 0.00000 0.063 0.013 4.4 0.00000 TOMSat R3 4.66 0.041 0.009 5.0 0.00000 0.063 0.014 4.3 0.00000 SHFT-1 5.10 0.048 0.009 4.9 0.00000 0.186 0.036 4.1 0.00000 ALBus 2.91 0.046 0.016 4.1 0.00000 0.102 0.035 3.4 0.00000 *ANDESITE – Node is examined deploying at 350km, resulting in ~3-month orbit lifetime Solar Flux Table Dated 11/07/2016 ** CubeSail has outlined a CONOPS to deploy sail at 350km to alleviate concerns from the FCC

The probability of any ELaNa-19 spacecraft collision with debris and meteoroids greater than 10 cm in diameter and capable of preventing post-mission disposal is less than 0.00000, for any configuration. This satisfies the 0.001 maximum probability requirement 4.5-1. Since the CubeSats have no capability or plan for end-of-mission disposal, requirement 4.5-2 is not applicable. Assessment of spacecraft compliance with Requirements 4.5-1 shows ELaNa-19 to be compliant. Requirement 4.5-2 is not applicable to this mission. Section 6: Assessment of Spacecraft Postmission Disposal Plans and Procedures All ELaNa-19 spacecraft will naturally decay from orbit within 25 years after end of the mission, satisfying requirement 4.6-1a detailing the spacecraft disposal option. Planning for spacecraft maneuvers to accomplish postmission disposal is not applicable. Disposal is achieved via passive atmospheric reentry. Calculating the area-to-mass ratio for the worst-case (smallest Area-to-Mass) post- mission disposal among the CubeSats finds Shields-1 in its stowed configuration as the worst case. The area-to-mass is calculated for is as follows: !"#$ &(' )*"# (,- ) ,- = )*"# − 45 − !#// ( ) !#// (01) 01 Equation 3: Area to Mass 0.0417;< ;< = 0.0060 6.94?@ ?@ Shields-1 has the smallest Area-to-Mass ratio and as a result will have the longest orbital lifetime. The assessment of the spacecraft illustrates they are compliant with Requirements 4.6-1 through 4.6-5. DAS 2.1.1 Orbital Lifetime Calculations: DAS inputs are: 500 km maximum apogee 500 km maximum perigee altitudes with an inclination of 85 degrees at deployment no earlier than March 1, 2018. An area to mass ratio of 0.0060 m2/kg for the Shields-1 CubeSat was imputed. DAS 2.1.1 yields a 5.9 years orbit lifetime for Shields-1 in its stowed state. This meets requirement 4.6-1. For the complete list of CubeSat orbital lifetimes reference Table 4: CubeSat Orbital Lifetime & Collision Probability. Assessment results show compliance.

Section 7: Assessment of Spacecraft Reentry Hazards A detailed assessment of the components to be flown on ELaNa-19 was performed. The assessment used DAS 2.1.1, 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 posses the same negligible risk as stainless steel components. See Table 5 through Table 7. Table 5: ELaNa-19 High Melting Temperature Material Analysis (1/3) CubeSat High Temp Component Material Mass (g) Demise Alt (km) KE (J) ANDESITE Node Deployment Springs Steel AISI 304 0.002 76.4 0 ANDESITE Antennae Steel AISI 410 0.001 0 0 ANDESITE 6-32 Screws Stainless Steel (generic) 0.000 77.5 0 ANDESITE 2-56 Screws Stainless Steel (generic) 0.000 77.4 0 ANDESITE Hinges Stainless Steel (generic) 0.006 0 1 CeREs Tungsten Tube Tungsten 0.202 0 150 CeREs Detector Silicon 0.008 0 0 CeREs Closeout Plate 1 Tungsten 0.018 0 8 CHOMPTT StenSat UHF Antennae Stainless Steel (generic) 0.001 0 0 CHOMPTT Lithium UHF Antennae Stainless Steel (generic) 0.001 0 0 CHOMPTT Backplane Holder - 11 mm Steel AISI 304 0.002 0 0 CHOMPTT Backplane Holder - 13 mm Steel AISI 304 0.002 0 0 CHOMPTT Reaction Wheel Assembly Stainless Steel (generic) 0.096 68.6 0 40

Table 6: ELaNa-19 High Melting Temperature Material Analysis (2/3) CubeSat High Temp Component Material Mass (g) Demise Alt (km) KE (J) CHOMPTT Batteries Stainless Steel (generic) 0.045 69 0 CHOMPTT Battery Holder Plates 2a&2b* Steel AISI 304 0.058 0 6 CHOMPTT Lithium Radio Stainless Steel (generic) 0.026 0 6 CHOMPTT Retoreflector Array Stainless Steel (generic) 0.018 0 4 CubeSail CubeSail Antenna Stainless Steel (generic) 4.400 74.7 0 CubeSail Fasteners Stainless Steel (generic) 100.000 77.7 0 CubeSail Low-head Socket Cap Screw Stainless Steel (generic) 0.680 77 0 CubeSail Wave Spring Steel AISI 304 0.045 77.9 0 CubeSail SRU Nut Plate Stainless Steel (generic) 7.530 75.3 0 CubeSail Wave Spring 2 Steel AISI 304 0.045 77.8 0 CubeSail Motor Pin Steel A-286 0.091 77.6 0 CubeSail Socket Cap Screw Stainless Steel (generic) 0.454 77.3 0 CubeSail Socket Cap Screw 2 Stainless Steel (generic) 0.771 77.1 0 CubeSail Bobbin Motor Bearing Stainless Steel (generic) 1.000 76.7 0 CubeSail Drive Pin Steel A-286 0.272 77.2 0 CubeSail Socket Cap Screw 3 Stainless Steel (generic) 0.635 77.3 0 ISX Historesis Material Stainless Steel (generic) 0.0015 77 0 ISX Screw - Representative Stainless Steel (generic) 0.00045 76.9 0 ISX Structural Rods Stainless Steel (generic) 0.001 77.4 0 ISX ISIS screws Stainless Steel (generic) 0.00025 77.1 0 ISX ISIS washers Stainless Steel (generic) 0.00005 0 0 ISX GAMMA Antenna washers Stainless Steel (generic) 0.00005 0 0 ISX GAMMA Antenna screws Stainless Steel (generic) 0.0006 76.2 0 ISX GAMMA Antenna nuts Stainless Steel (generic) 0.00001 0 0 ISX solar panel screw Stainless Steel (generic) 0.00054 76.6 0 ISX solar panel nut Stainless Steel (generic) 0.000241 0 0 ISX Solar panel clip Stainless Steel (generic) 0.0005 0 0 ISX 15mm spacers Stainless Steel (generic) 0.002 75 0 ISX 25mm spacers Stainless Steel (generic) 0.005 73.5 0 Rsat Motors Stainless Steel (generic) 0.01933 73.3 0 Rsat ADCS Stainless Steel (generic) 0.01 0 3 Rsat Fasteners Stainless Steel (generic) 0.00005 77.6 0 Shields-1 Shield1 Tantalum 0.2 0 69 Shields-1 Shield2 Titanium (6 Al-4 V) 0.072364523 0 14 Shields-1 Shield3 Tantalum 0.1 0 27 Shields-1 Shield4 Titanium (6 Al-4 V) 0.00001 0 0 Shields-1 Shield5 Tantalum 0.00001 0 0 Shields-1 Shield6 Titanium (6 Al-4 V) 0.0001 0 0 Shields-1 Shield7 Titanium (6 Al-4 V) 0.0001 0 0 Battery Holder Plates 2a&2b*Has been updated with corrected “per unit mass” of 0.058kg resulting in 6J of energy for surviving component 41

Table 7: ELaNa-19 Summary of Surviving High Temperature Material Components (3/3) CubeSat High Temp Component Material Mass (g) Demise Alt (km) KE (J) Shields-1 Shield8 Titanium (6 Al-4 V) 0.0001 0 0 Shields-1 Charge Dissipation Film electrodes Steel AISI 304 0.01 73.8 0 Shields-1 Charge Dissipation Film spring Stainless Steel (generic) 0.0025 76.1 0 Shields-1 RTDs (Est Dims) Stainless Steel (generic) 0.001 77.5 0 Shields-1 Fasterners2 Stainless Steel (generic) 0.0001 77.7 0 Shields-1 Fasteners3 Stainless Steel (generic) 0.00005 77.7 0 Shields-1 Fasteners4 Stainless Steel (generic) 0.0005171 0 0 Shields-1 Solar Panel Screws Steel AISI 410 0.00008 77.6 0 Shields-1 Solar Panel Washers Steel AISI 410 0.0001 0 0 Shields-1 Remove Before Flight Pin Stainless Steel (generic) 0.02 73.7 0 Shields-1 Sep Switch Stainless Steel (generic) 0.02 73.7 0 Shields-1 ADCS Components (Hysteresis Rods) Stainless Steel (generic) 0.001 77.5 0 STF-1 Ferrite Bead Stainless Steel (generic) 0.00001 77.3 0 STF-1 Geiger Tube Stainless Steel (generic) 0.05 67 0 STF-1 Fasteners5 Stainless Steel (generic) 0.00001 77.9 0 TOMSat Reaction Wheels Stainless Steel (generic) 0.22501 63.9 0 TOMSat Single Torque Rod Stainless Steel (generic) 0.01844 74.8 0 TOMSat 18267 Titanium (generic) 0.01669 0 2 TOMSat 18265 Titanium (generic) 0.01092 0 1 TOMSat 18264 Titanium (generic) 0.01232 0 1 TOMSat 18268 Titanium (generic) 0.00404 0 0 TOMSat 18266 Titanium (generic) 0.01028 0 2 TOMSat 18263 Titanium (generic) 0.00128 0 0 TOMSat 18270 Titanium (generic) 0.00074 0 0 TOMSat Laser Aluminum 6061-T6 0.35285 72.8 0 SHFT-1 Internal Fasteners Stainless Steel (generic) 0.0005 77 0 SHFT-1 External Fasteners Stainless Steel (generic) 0.0005 77 0 ALBus Threaded Rod Stainless Steel (generic) .00068 78 0 ALBus Baseplate Aluminum 7075-T6 0.0008 78 0 ALBus Springs Titanium (generic) 0.0069 78 0 ALBus Gravity mass Stainless Steel (generic) 0.0009 78 0 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 DaVinci Reaction Wheel Daughter Board Stainless Steel (generic) 0.1 0 14 The majority of high temperature components demise upon reentry. And all CubeSats comply with the 1:10,000 probability of Human Casualty Requirement 4.7-1. A breakdown of the determined probabilities follows on Table 7. 42

Table 8: Requirement 4.7-1 Compliance by CubeSat CubeSat Risk Risk < 1:10,000 ANDESITE 1:0 Compliant CeREs 1:210,600 Compliant CHOMPTT 1:0 Compliant CubeSail 1:0 Compliant ISX 1:0 Compliant NMTsat 1:0 Compliant Rsat 1:0 Compliant Shields-1 1:32,400 Compliant STF-1 1:0 Compliant TOMSat 1:0 Compliant SHFT-1 1:0 Compliant ALBus 1:0 Compliant DaVinci 1:0 Compliant *Requirement 4.7-1 Probability of Human Casualty < 1:10,000 If a component survives to the ground but has less than 15 Joules of kinetic energy it is not included in the Debris Casualty Area that inputs into the Probability of Human Casualty calculation. Which is why CubeSats that have surviving components like ANDESITE, CubeSail, DaVinci, ISX, NMTsat, CHOMPTT, Rsat, STF-1 TOMSat EAGLESCOUT, TOMSat R3, SHFT-1, and ALBus have a 1:0 probability as none of their components have more than 15J of energy. The breakdown of CubeSat’s with greater than 15J of energy components is as follows: CeREs has 1 and Shields-1 has 3. These two CubeSats are well within the NASA requirements for uncontrolled reentry. All CubeSats launching under the ELaNa-19 mission are shown to be in compliance with Requirement 4.7-1 of NASA-STD-8719.14A. See the Appendix for a complete accounting of the survivability of all CubeSat components. 43

Section 8: Assessment for Tether Missions In the ELaNa-19 mission, CubeSail’s deployable sail made of a mylar film qualifies as a momentum tether although a ribbon would be a more accurate description of its dimensions (0.0004 cm x 7.9cm x 25,317 cm). The tether mission plan can be referenced in the CubeSail specific mission plan located in Section 2. (See Appendix O for the CONOPs) Following the Methods to Assess Compliance for Tethered Systems (section 4.8.4), the DAS analysis determined the CubeSail design to be COMPLIANT with both Requirement 4.5-1 and 4.5-2 dealing with meeting the requirements limiting the generation or orbital debris from on-orbit collisions. The probability of collision on orbit for the un-deployed system, fully deployed system, and ½ the system in the event of a tether severing event was calculated to be << 0.001. CubeSail is also compliant with Requirements 4.6-1 to 4.6-4 (Postmission Disposal), given the low 350km x 350km, this orbit will have CubeSail passively deorbit in 5.5 years if the system does not deploy, <<0.1 years if the system does deploy, and <<0.1 year if the tether breaks into two equal parts as calculated via DAS 2.1.1 All three scenarios are compliant with the Requirement 4.6-1 to 4.6-4. Figure 23: Tether Assessment of CubeSail ELaNa-19 CubeSat, CubeSail satisfies Section 8’s requirement 4.8-1. 44

Section 9-14 ODAR sections 9 through 14 for the launch vehicle are not covered here. If you have any questions, please contact the undersigned at 321-867-2958. /original signed by/ Justin Treptow Flight Design Analyst NASA/KSC/VA-H1 cc: VA-H/Mr. Carney VA-H1/Mr. Beaver VA-H1/Mr. Haddox VA-G2/Mr. Atkinson VA-G2/Mr. Marin SA-D2/Mr. Frattin SA-D2/Mr. Hale SA-D2/Mr. Henry Analex-3/Mr. Davis Analex-22/Ms. Ramos 45

Appendix Index: Appendix A. ELaNa-19 Component List by CubeSat: ANDESITE Appendix B. ELaNa-19 Component List by CubeSat: CeREs Appendix C. ELaNa-19 Component List by CubeSat: CHOMPTT Appendix D. ELaNa-19 Component List by CubeSat: CubeSail Appendix E. ELaNa-19 Component List by CubeSat: DaVinci Appendix F. ELaNa-19 Component List by CubeSat: ISX Appendix G. ELaNa-19 Component List by CubeSat: NMTSat Appendix H. ELaNa-19 Component List by CubeSat: RSat Appendix I. ELaNa-19 Component List by CubeSat: Shields-1 Appendix J. ELaNa-19 Component List by CubeSat: STF-1 Appendix K. ELaNa-19 Component List by CubeSat: TOMSat EAGLESCOUT Appendix L. ELaNa-19 Component List by CubeSat: TOMSat R3: Appendix M. ELaNa-19 Component List by CubeSat: SHFT-1 Appendix N. ELaNa-19 Component List by CubeSat: ALBus Appendix O. CubeSail CONOPS Rev8 46

Appendix A. ELaNa-19 Component List by CubeSat: ANDESITE Diameter/ Row Individual Length Height High Melting CUBESAT Name Qty Material Body Type Width Survivability Number Mass (g) (mm) (mm) Temp Temp (mm) ANDESITE 1 6U Anodized Baseplate 1 Aluminum 7075 Flate Plate 1346 239 361 6.35 No - Demise ANDESITE 2 Sensor Node Structure 8 Alumnium 6061 Box 133 97.81 190 15.5 No - Demise ANDESITE 3 Top Plate 1 Aluminum 6061 Box 364 227.8 361 3.18 No - Demise ANDESITE 4 CubeSat Structure - 2U L Brackets 2 Aluminum 6061 Box 60 19.05 223.23 3.18 No - Demise ANDESITE 5 CubeSat Structure - 1U L Brackets 4 Aluminum 6061 Box 36 19.05 93.65 3.18 No - Demise ANDESITE 6 CubeSat Structure - 1U Cladding 2 Aluminum 6061 Box 38 227.8 100 2.29 No - Demise ANDESITE 7 CubeSat Structure - 2U Cladding 2 Aluminum 6061 Box 110 148.6 100 2.29 No - Demise ANDESITE 8 Top Solar Panel 1 Fiberglass Cylinder 150 227.8 361 No - Demise ANDESITE 9 Wing Solar Panel 2 Fiberglass Box 98 354.86 86 3.18 No - Demise ANDESITE 10 Node Deployment Mechanism 1 Aluminum 6061 Flat Plate 1549 210 151.33 15 No - Demise ANDESITE 11 Node Deployment Peg Guides 4 Aluminum 6061 Box 82 27.6 100 15 No - Demise ANDESITE 12 Node Deployment Springs 8 Steel 302 Cylinder 4.4 4.7752 19.05 Yes 1538 See Tables 4-6 ANDESITE 13 Antennae 9 Steel 410 Blade 0.8 12.7 165.1 1 Yes 1532 See Tables 4-6 ANDESITE 14 Sensor Node Solar Panels 16 Fiberglass PCB 67.3 175 93.73 2 No - Demise ANDESITE 15 Mule Battery 1 Battery Box 260.4 95 90 39.82 No - Demise ANDESITE 16 Node Batteries 8 Battery Box 184.4 59.5 157 9.8 No - Demise ANDESITE 17 EPS 1 Fiberglass (PCB) Board 174 96 90 1.5 No - Demise ANDESITE 18 ADCS Components (eg. Magnets) 1 Fiberglass (PCB) Board 94.2 96 90 1.5 No - Demise ANDESITE 19 Comm Board 1 Fiberglass (PCB) Board 125 96 90 1.5 No - Demise ANDESITE 20 C&DH Board 1 Fiberglass (PCB) Board 142 96 90 1.5 No - Demise ANDESITE 21 Magnetometer Orthogonal Holder 1 Macor Holder 5 5 5 5 No - Demise ANDESITE 22 Magnetorquers 1 Copper Board/Coils 95.9 96 90 1.5 No - Demise ANDESITE 23 6-32 Screws 90 Stainless Steel 316 Screws 0.5 3.5052 6.35 Yes 1400 See Tables 4-6 ANDESITE 24 2-56 Screws 150 Stainless Steel 316 Screws 0.3 2.1844 6.35 Yes 1400 See Tables 4-6 ANDESITE 25 Bumpers 4 Nylon Blocks 2 25.4 50.8 2.54 No - Demise ANDESITE 26 Hinges 4 Stainless Steel 316 Hinge 12 25.4 50.8 0.889 Yes See Tables 4-6

Appendix B. ELaNa-19 Component List by CubeSat: CeREs Diameter/ Row Individual Length Height High Melting CUBESAT Name Qty Material Body Type Width Survivability Number Mass (g) (mm) (mm) Temp Temp (mm) Ceres 1 Cubesat Structure 1 Aluminium 6061-T6 Box 700 100 100 340 No - Demise Ceres 2 Payload Structure 1 Aluminium 6061-T6 Box 250 74 52 94 No - Demise Ceres 3 Tungsten Tube 1 Tungsten Cylinder 202 67 40 Yes 3422 See Tables 4-6 Ceres 4 XB1 1 Aluminum Box 1800 100 100 135 No - Demise Ceres 5 solar array 2 FR4+Aluminum Flat Plate 194 65 82 327 No - Demise Ceres 6 Detector 8 Silicon Cylinder 8 39 39 Yes 1410 See Tables 4-6 Ceres 7 Closeout Plate 1 2 Tungsten Flat Plate 25 50 14 2 Yes 3422 See Tables 4-6 Ceres 8 Aluminum Closeout Plate Holder 1 Aluminum Box 20 26 67 17.2 No - Demise Ceres 9 Detector Holder 16 FR4 Flat Plate 5 52 52 No - Demise Ceres 10 Payload Card 4 FR4+Copper Flat Plate 100 88 92 18 No - Demise Ceres 11 backplane 1 FR4+Copper Flat Plate 21 7.5 25.4 11.3 No - Demise Ceres 12 HVPS 2 Urethane? Box 20 33 40.6 12.1 No - Demise Ceres 13 GPS antenna 1 Aluminum 6061-T6 Flat Plate 50 53 18 No - Demise Ceres 14 ISIS antenna 4 Aluminum 6061-T6 Flat Plate 100 98 98 5.7 No - Demise Ceres 15 CSP 1 FR4+Copper Flat Plate 44 100 100 14.6 No - Demise Ceres 16 Cabling 6 copper alloy cylinder 8 2 6 No - Demise 48

Appendix C. ELaNa-19 Component List by CubeSat: CHOMPTT (1/2) Diameter/ Row Individual Length Height High Melting CUBESAT Name Qty Material Body Type Width Survivability Number Mass (g) (mm) (mm) Temp Temp (mm) CHOMPTT 1 3U CubeSat Chassis 1 Aluminum 5052 Box 317 100 100 339.89 No - Demise CHOMPTT 2 StenSat UHF Antennae 1 Stainless Steel (generic) Box 1.43 12.2 186.5 0.1 Yes 1510 See Tables 4-6 CHOMPTT 3 Lithium UHF Antennae 1 Stainless Steel (generic) Box 1.43 12.2 195.6 0.1 Yes 1510 See Tables 4-6 CHOMPTT 4 RBF Switch 1 Polycarbonate (aka Lexan) Box 1.15 12.27 19.84 6.39 No - Demise CHOMPTT 5 Rail Switches 1 Polycarbonate (aka Lexan) Box 1 13 15 10 No - Demise CHOMPTT 6 GPS Patch Antennae 1 Fiberglass Flat Plate 9.2 34.94 89.5 - No - Demise CHOMPTT 7 Sun Sensors 5 Aluminum 6061 Box 4 27.4 14 5.9 No - Demise CHOMPTT 8 1U TASC Solar Panel 5 Aluminum (generic) Flat Plate 108.18 98.6 98.99 - No - Demise CHOMPTT 9 1U GOMspace Solar Panel 4 Aluminum (generic) Flat Plate 57 98 82.6 - No - Demise CHOMPTT 10 1U GOMspace Solar Panel 4 Aluminum (generic) Flat Plate 26 98 82.6 - No - Demise CHOMPTT EDSN/NODeS-derived Spacecraft Bus - - - CHOMPTT 11 Backplane PCB 1 Fiberglass Flat Plate 29.759 56.94 140.96 - No - Demise CHOMPTT 12 Backplane Holder - 11 mm 1 Steel AISI 304 Box 1.52 11 67 0.9 Yes 1538 See Tables 4-6 CHOMPTT 13 Backplane Holder - 13 mm 1 Steel AISI 304 Box 1.99 16 67 0.9 Yes 538 See Tables 4-6 CHOMPTT 14 Midplane 1 Aluminum 6061-T6 Cylinder 3.14 16.9 21.1 - No - Demise CHOMPTT 15 Router PCB 1 Fiberglass Flat Plate 44.74 60.63 89.74 - No - Demise CHOMPTT 16 ACS PCB 1 Fiberglass Flat Plate 36.94 94.09 95.46 22.77 No - Demise CHOMPTT 17 Reaction Wheel Assembly 1 Stainless Steel (generic) Box 96.43 26 66 26 Yes 1400 See Tables 4-6 CHOMPTT 18 Phone PCB 1 Fiberglass Box 51.86 94.09 109.77 30.6 No - Demise CHOMPTT 19 EPS PCB 1 Fiberglass Box 46.57 94.09 95.46 37.53 No - Demise 49

ELaNa-19 Component List by CubeSat: CHOMPTT (2/2) Diameter/ Row Individual Length Height High Melting CUBESAT Name Qty Material Body Type Width Survivability Number Mass (g) (mm) (mm) Temp Temp (mm) CHOMPTT 20 Lithium Grounding Hat Assembly 1 Aluminum 6061-T6 Box 1.84 18.13 52.64 5.8 No - Demise CHOMPTT 21 StenSat Grounding Hat Assembly 1 Aluminum 6061-T6 Box 1.32 17 43 5 No - Demise CHOMPTT 22 Batteries 4 Stainless Steel (generic) Cylinder 45.45 18.3 64.9 - Yes 1400 See Tables 4-6 CHOMPTT 23 Battery Holder 1 Polycarbonate (aka Lexan) Box 27.99 78.73 82.6 15.7 No - Demise CHOMPTT 24 Battery Holder Plates 2a&2b 2 Steel AISI 304 Flat Plate 58.5 94.09 95.46 - Yes 1450 See Tables 4-6 CHOMPTT 25 StenSat Radio Assembly 1 Fiberglass Box 28.87 44.45 78.74 18.53 No - Demise CHOMPTT 26 GPS PCB 1 Fiberglass Flat Plate 48.14 94.09 95.5 - No - Demise CHOMPTT 27 GPS Housing & Heat Sink 1 Aluminum 6061-T6 Flat Plate 32.9 87.01 92.55 - No - Demise CHOMPTT 28 GPS Reciever 1 Fiberglass Box 18.3 45.72 71.12 10.19 No - Demise CHOMPTT 29 Lithium Radio PCB 1 Fiberglass Flat Plate 28.72 94.909 95.46 - No - Demise CHOMPTT 30 Lithium Radio 1 Stainless Steel (generic) Box 25.7 32 62 10.079 Yes 1450 See Tables 4-6 CHOMPTT 31 Adapter Plate - Aluminum 6061 Flat Plate 40.15 97 97 - No - Demise CHOMPTT OPTI Payload - - - CHOMPTT 32 Payload Structure 1 Aluminum 6061 Box 564.83 96.4 97 94 No - Demise CHOMPTT 33 Supervisor PCB 1 Fiberglass Box 30.6 86.28 56.12 - No - Demise CHOMPTT 34 Channel PCB 2 Fiberglass Flat Plate 30 86.15 86.01 - No - Demise CHOMPTT 35 High Voltage Shield 2 Aluminum 6061, Cesium Flat Plate 45.79 84.75 61.75 11.5 No - Demise CHOMPTT 36 CSAC (Chipscale Atomic Clock) 2 Aluminum 6061 Box 35 35.57 40.65 11.43 No - Demise CHOMPTT 37 Beacon Diode PCB 1 Fiberglass Box 35 12 30.13 - No - Demise CHOMPTT 38 Retoreflector Array Fused Silica (Glass) Box 17.98 52 30 7 Yes 1600 See Tables 4-6 CHOMPTT 39 Fasteners - - - - - - - No - Demise CHOMPTT 40 Cabling - - - - - - - No - Demise CHOMPTT 41 Large Aperature Plate (-Y) 1 Aluminum 6061 Flat Plate 37 99.78 99.75 - No - Demise 50

Appendix D. ELaNa-19 Component List by CubeSat: CubeSail (1/3) Diameter/ Row Individual Length Height High Meltin CUBESAT Name Qty Material Body Type Width Survivability Number Mass (g) (mm) (mm) Temp g Temp (mm) CubeSail 1 Rail 8 Aluminum 6061 Rail 26.8 17 17 155.75 No - Demise CubeSail 2 Bottom Plate 2 Aluminum 6061 Plate 71.97 100 100 25.5 No - Demise CubeSail 3 Antennae 8 Stainless Steel Strip 4.4 6.7 22 0.4 Yes 1450 See Tables 4-6 CubeSail 4 Radiation Shielding 6 Aluminum 6061 Plate 35.6 80 161.75 1.016 No - Demise Radiation Shielding with Access CubeSail 5 2 Aluminum 6061 Plate 35.2 80 161.75 1.016 No - Demise Port CubeSail 6 Solar Cell 22 Solar Cell Panel 3.2 40 70 0.4 No - Demise CubeSail 7 Flex Cable 8 Kapton and PCB Components Flat Cable 5 54 18.34 169.32 No - Demise CubeSail 8 Magnetometer 8 Circuit Board Board 3.7 40 30 3.9 No - Demise CubeSail 9 Daughter Card 2 Circuit Board Plate 10.1 60 30 2.41 No - Demise CubeSail 10 Power Board 2 Circuit Board Board 56.5 94 90 1.5 No - Demise CubeSail 11 C&DH Board (was CPU) 2 Circuit Board Board 40 90 90 5.6002 No - Demise Aluminum 6061 and Circuit CubeSail 12 Lithium Radio 2 Plate 50 60.4 30.4 9 No - Demise Board CubeSail 13 Radio Carry Board 2 Circuit Board Board 17.3 70 70 1.6 No - Demise CubeSail 14 Payload Board 2 Circuit Board Board 30.3 12 90 90 No - Demise CubeSail 15 Connector Adjustment Board 2 Circuit Board Board 3 5 32 20 No - Demise CubeSail 16 Torque Coil 10 Circuit Board Board 27.7 90 76.2 3.5 No - Demise CubeSail 17 Middle Plate 2 Aluminum 6061 Plate 66.98 96.83 96.83 13.5 No - Demise Lithium Ion Batteries, Circuit 4 cylinders, mounted CubeSail 18 Battery Pack 2 227.2 87 85 22.5 No - Demise Board on board CubeSail 19 Battery Holder 2 Aluminum 6061 Board 40 86 86.5 22.8 No - Demise CubeSail 20 Fasteners 1 Stainless Steel Small 100 Yes 1450 See Tables 4-6 51

ELaNa-19 Component List by CubeSat: CubeSail (2/3) Diameter/ Row Body Individual Length Height High Melting CUBESAT Name Qty Material Width Survivability Number Type Mass (g) (mm) (mm) Temp Temp (mm) CubeSail 21 Cabling 1 Copper alloy, teflon insulation Wires 150 No - Demise CubeSail 22 Bobbin 2 Al 6061 Cylinder 93.5760296 49.022 84.00034 0 No - Demise CubeSail 23 Motor Mount Plate, Drive Shaft 2 Al 6061 Cylinder 5.3070264 25.4 6.985 0 No - Demise CubeSail 24 Motor Mount Plate, Ribbon Cable 2 Al 6061 Cylinder 6.2142104 25.4 6.985 0 No - Demise CubeSail 25 Motor Support Rod 6 Al 6061 Rod 2.26796 4.7625 50.8 0 No - Demise CubeSail 26 Drive Wheel 2 Al 6061 Cylinder 7.257472 26.9494 8.30834 0 No - Demise CubeSail 27 Shim Rings 4 Al 6061 Ring 0.4989512 26.9494 1.5748 0 No - Demise CubeSail 28 A-Frame, Motor Mount 2 Al 6061 Plate 19.4590968 57.00014 13.4839964 49.9999 No - Demise CubeSail 29 A-Frame, Support 2 Al 6061 Plate 22.8156776 57.00014 13.4919974 49.9999 No - Demise CubeSail 30 Support Rod 4 Al 6061 Rod 36.28736 4.7625 78.3844 0 No - Demise CubeSail 31 Film 2 Aluminized Mylar Sheet 85 79 253170 0.004 No - Demise CubeSail 32 Low-head Socket Cap Screw 8 18-8 stainless steel Screw 0.680388 5.7404 8.1788 0 Yes 1450 See Tables 4-6 CubeSail 33 Slit Rod 2 Al 6061 - T6 Rod 2.9937072 6.35 79 0 No - Demise CubeSail 34 Standoff Feet 4 Brass Screw 0.1360776 3.7084 1.4732 0 No - Demise CubeSail 35 (Motor) Payload Plate, Male 1 Al 6061 Plate 54.43104 16.4999924 99.9998 99.9998 No - Demise CubeSail 36 Camera Mount Dog 1 Al 6061 Block 8.618248 29.972 10.8204 19.9898 No - Demise CubeSail 37 Camera Mount Base 1 Al 6061 Block 8.2553744 19.9898 29.972 7.33298 No - Demise CubeSail 38 Motor Mount Plate 1 Al 6061 Plate 1.9504456 21.2015578 13.9338304 2.54 No - Demise CubeSail 39 Motor Support Rod 4 Al 2024 Rod 1.4061352 3.96875 47.54118 0 No - Demise CubeSail 40 SRU Leadscrew 1 Brass Screw 3.628736 6.1849 15.986506 0 No - Demise 52

ELaNa-19 Component List by CubeSat: CubeSail (3/3) Row Diameter/ High CUBESA Body Individual Length Height Meltin Numbe Name Qty Material Width Tem Survivability T Type Mass (g) (mm) (mm) g Temp r (mm) p CubeSail 41 Compression Spring 2 Zinc-coated Music Wire Spring 0.226796 7.9193136 18.1991 0 No - Demise CubeSail 42 Motor 2 Brass Cylinder 75.1 15.93 61.54 0 No - Demise See Tables 4- CubeSail 43 Wave Spring 2 302 Stainless Steel Ring 0.0453592 4.6736 0.5842 0 Yes 1450 6 CubeSail 44 Slit Rod 2 Al 6061 - T6 Rod 2.9937072 6.35 79 0 No - Demise CubeSail 45 Payload Plate, Female 1 Al 6061 Plate 49.89512 19.2499996 99.9998 99.9998 No - Demise CubeSail 46 Camera Mount Dog 1 Al 6061 Block 8.618248 29.972 10.8204 19.9898 Demise CubeSail 47 Camera Mount Base 1 Al 6061 Block 8.2553744 19.9898 29.972 7.33298 No - Demise See Tables 4- CubeSail 48 SRU Nut Plate 1 Stainless Steel Plate 7.5296272 26.4922 12.7 3.175 Yes 1430 6 CubeSail 49 Motor 1 Brass Cylinder 75.1 15.93 61.54 0 No - Demise See Tables 4- CubeSail 50 Wave Spring 2 302 Stainless Steel Ring 0.0453592 4.6736 0.5842 0 Yes 1450 6 See Tables 4- CubeSail 51 Motor Pin 1 Steel Cylinder 0.0907184 1.6764 6.1341 Yes 1450 6 See Tables 4- CubeSail 52 Socket Cap Screw 12 18-8 stainless steel Screw 0.453592 5.4102 7.8486 0 Yes 1450 6 13.71676 See Tables 4- CubeSail 53 Socket Cap Screw 6 18-8 stainless steel Screw 0.7711064 4.4958 0 Yes 1450 2 6 CubeSail 54 SRU Frame Screws 8 Brass Screw 0.2721552 3.429 9.271 0 No - Demise See Tables 4- CubeSail 55 Bobbin Motor Bearing 6 Stainless Steel Ring 1 3 3 0 Yes 1450 6 See Tables 4- CubeSail 56 Drive Pin 2 Steel Cylinder 0.2721552 3.175 4.7625 0 Yes 1450 6 CubeSail 57 LED mount board 4 Circuit Board Plate 0.5 1.524 36.83 18.415 No - Demise CubeSail 58 3.2x2.4mm LED 6 LED Block 0 3.1496 2.4384 2.413 No - Demise See Tables 4- CubeSail 59 Socket Cap Screw 12 18-8 Stainless Steel Screw 0.6350288 5.4102 12.6111 0 Yes 1450 6 CubeSail 60 Slotted Screw 8 Nylon Screw 0.0907184 5.5626 8.0772 0 No - Demise 21.4900 CubeSail 61 Camera 2 Circuit Board Block 13.5 20.0000108 28.30068 No - Demise 002 53

Appendix E. ELaNa-19 Component List by CubeSat: DaVinci Diameter/ Row Individual Length Height High Melting CUBESAT Name Qty Material Body Type Width Survivability Number Mass (g) (mm) (mm) Temp Temp (mm) DaVinci 1 DaVinci Cubesat 1 Aluminium 6082 Box - - - - No - Demise DaVinci 2 CubeSat Structure 1 Aluminium 6082 Box 396 100 100 340.5 No - Demise DaVinci 3 Patch Antenna 1 Ceramic Disc 69 48.124 48.124 9.652 No - Demise DaVinci 4 Deployable VHF/UHF Antenna 1 Nitinol Thin strips 12 450 170 No - Demise DaVinci 5 Deployable Solar Panels 2 Copper, Fibreglass, Kapton Rectangle 332 1.6 200 300 No - Demise DaVinci 6 Solar Panels 2 Copper, Fibreglass, Kapton Rectangle 142 1.6 100 300 No - Demise DaVinci 7 Duplex Comms Payload 1 PCB PCB 226 63.73 118.7 26.99 No - Demise DaVinci 8 VUTRX Comms 1 PCB PCB 96 90.18 95.89 13 No - Demise DaVinci 9 Imaging Payload 1 PCB/Glass PCB 43 24.4 25 34.1 No - Demise DaVinci 10 Antenna Deployment Module 1 Aluminium PCB 87 98 98 10.51 No - Demise DaVinci 11 On Board Computer 1 PCB PCB 73 90.17 95.89 5.51 No - Demise DaVinci 12 Payload Interface Module 1 PCB PCB 70 90.17 95.89 23.29 No - Demise DaVinci 13 Battery 1 lithium ion polymer PCB 331 90.17 95.89 27.35 No - Demise DaVinci 14 ADCS Mother board 1 PCB PCB 86 90.17 95.89 9.06 No - Demise DaVinci 15 Reaction Wheel Daughter Board 1 Stainless Steel (120g of total) PCB/Box 239 90.17 95.89 44.49 Yes 1450 See Tables 4-6 DaVinci 16 Harnesses 20 Copper Cylinder/wire 22.5 - - - No - Demise DaVinci 17 Spacers 1 Aluminium 6082 Cylinder 16.4 - - - No - Demise DaVinci 18 Engraved Plate 1 Aluminium 6082 Rectangle 28 - - - No - Demise DaVinci 19 EPS 1 PCB PCB 178 - - - No - Demise DaVinci 20 Spacing Headers 1 - - 16 - - - No - Demise 54

Appendix F. ELaNa-19 Component List by CubeSat: ISX (1/2) Diameter/ Row Individual Length Height High Melting CUBESAT Name Qty Material Body Type Width Survivability Number Mass (g) (mm) (mm) Temp Temp (mm) ISX 1 ISX 3U CubeSat 1 Various Box 3699.3 100 100 340.5 No - Demise ISX 2 CubeSat Structure 1 Aluminum 6061 Box 456 100 100 340.5 No - Demise ISX 3 +Z Panel 1 PCB Box 30 100 100 2.5 No - Demise ISX 4 -Z Panel 1 PCB Box 30 100 100 2.5 No - Demise ISX 5 Radio Daughter Board 1 PCB Box 15 36 83 2.5 No - Demise ISX 6 GPS Daughter Board 1 PCB Box 15 39 83 2.5 No - Demise ISX 7 GPS Patch 1 Ceramic Box 11.4 25.1 25.1 5.2 No - Demise ISX 8 C-Band Patch 1 Ceramic Box 2.1 12 12 4.3 No - Demise ISX 9 Antenna Routes 3 Delrin Box 5 65 65 3.4 No - Demise ISX 10 Antenna 6 Nitonol Wire Box 2 0.31 165 0.51 No - Demise ISX 11 System Board 1 PCB Box 60 100 83 3 No - Demise ISX 12 Payload Interface and Battery Board 1 PCB Box 50 83 83 3 No - Demise ISX 13 Side Panel 4 PCB Box 120 83 320 2.5 No - Demise ISX 14 Solar Cell 20 Eglass Box 2.3 70 40 0.5 No - Demise ISX 15 Solar Angle Sensor Board 5 PCB Box 5 20 30 2.5 No - Demise ISX 16 Solar Angle Sensor Apperture 5 Aluminum Box 3 19 21 5 No - Demise ISX 17 Battery Bracket 1 Aluminum 6061 Box 168 76 82 67 No - Demise ISX 18 Heat Shrink 2 RNF-100 Polyolefin Heat Shrink Tube 2 63.5 25.4 0.5 No - Demise ISX 19 Batteries 9 Lithion Ion Cylinder 45 18.4 65.1 N/A No - Demise ISX 20 Dummy Cell 1 Delrin Cylinder 10 19 66 N/A No - Demise 55

ELaNa-19 Component List by CubeSat: ISX (2/2) Diameter/ Row Individual Length Height High Melting CUBESAT Name Qty Material Body Type Width Survivability Number Mass (g) (mm) (mm) Temp Temp (mm) ISX 21 Magnets 4 NdFeB Cylinder 5 14.3 3.2 N/A Yes 1300 See Tables 4-6 ISX 22 Historesis Material 4 HyMu80 Cylinder 2.6 2.3 50 N/A Yes 1454 See Tables 4-6 ISX 23 Magnetorquer Route 3 Delrin Box 5 78 58 4 No - Demise ISX 24 Magnetorquer Wire 3 Copper Cylinder 9 3 260 N/A No - Demise ISX 25 Screw - Representative 120 Stainless Steel 316 Cylinder 0.87 2.8 10 N/A Yes 1510 See Tables 4-6 ISX 26 Processor Housing 1 Aluminum 6061 Box 725 94.5 98.5 60 No - Demise ISX 27 Processor Board 1 1 PCB Box 87 75 89 3 No - Demise ISX 28 Processor Board 2 1 PCB Box 42 75 89 3 No - Demise ISX 29 Processor Board 3 1 PCB Box 50 75 89 3 No - Demise ISX 30 RF Front End Housing 1 Aluminum 6061 Box 225 94.5 98.5 30 No - Demise ISX 31 RF Front End Board 1 1 PCB Box 39 75 89 3 No - Demise ISX 32 RF Front End Board 2 1 PCB Box 40 75 89 3 No - Demise ISX 33 RF Front End Board 3 1 PCB Box 32 75 89 3 No - Demise ISX 34 Cband Housing 1 Aluminum 6061 Box 130 94.5 98.5 20 No - Demise ISX 35 Cband Board 1 PCB Box 44 75 89 3 No - Demise ISX 36 Payload Heat Shrink 1 Polyolefin Tube 5 20 100 0.5 No - Demise ISX 37 Payload Dialectric 1 PTFE Box 10 10 10 10 No - Demise ISX 38 SMB Connectors 4 Brass Box 5 17 6.5 14 No - Demise ISX 39 Cabling 3 Copper Ribbon 40 25.4 340 0.5 No - Demise ISX 40 Staking Compound 1 3M Scotch Weld 2216 Rectangular 50 N/A N/A N/A No - Demise ISX 41 Kapton Tape 1 Kapton Tape Tape 0 Various Various 0.05 No - Demise ISX 42 Sep/Actuating Switches 2 Plastic (PBT) Rectangular 2 6 8 7 No - Demise ISX 43 Payload Cable Bundles 1 Plastic (PBT) Cylinder 20 10 50 N/A No - Demise ISX 44 Conformal Coating 1 Arathane 5750 Coating 30 N/A N/A N/A No - Demise 56

Appendix G. ELaNa-19 Component List by CubeSat: NMTSat (1/2) Row Diameter/ Lengt Heigh CUBESA Individua High Melting Numbe Name Qty Material Body Type Width h t Survivability T l Mass (g) Temp Temp r (mm) (mm) (mm) NMTsat 1 3U CubeSat structure 1 Aluminum 6061 Box 396.893 99.87 99.87 340.53 No - Demise NMTsat 2 Solar panels 4 FR-4, GaAs cells Rectangualr Plate 96.65 81.73 324.5 1.575 No - Demise NMTsat 3 ISIS Antenna 1 Aluminum 6061 Box 85.162 98 98 5.7 No - Demise NMTsat 4 copper plate (plasma probe) 1 101 Copper Circular Plate 32.62 60.96 3.175 No - Demise NMTsat 5 LPP 1 FR-4 PC/104 29.6 90.297 95.885 15 No - Demise NMTsat 6 GAMMA Antenna 1 Aluminum 6061 box 15 38.1 32.055 15.24 No - Demise NMTsat 7 PEEK column 4 PEEK, copper threads Cylinder 4.884 12.7 28.575 No - Demise NMTsat 8 Solar panel clip 4 18-8 Stainless Steel box 1.364 15 15 0.3 Yes 1450 See Tables 4-6 NMTsat 9 GAMMA Antenna screws 2 18-8 Stainless Steel screw 0.6 4 9.7 Yes 1450 See Tables 4-6 NMTsat 10 solar panel screw 8 18-8 stainless steel screw 0.54 6 7.8 Yes 1450 See Tables 4-6 NMTsat 11 ISIS screws 4 18-8 Stainless Steel screws 0.25 4 7.8 Yes 1450 See Tables 4-6 NMTsat 12 solar panel nut 8 18-8 Stainless Steel nut 0.241 5.5 1.8 Yes 1450 See Tables 4-6 NMTsat 13 GAMMA Antenna nuts 2 18-8 Stainless Steel Nut 0.2 3 1 Yes 1450 See Tables 4-6 NMTsat 14 PEEK Screws 8 PEEK screw 0.16 6.756 9.525 No - Demise NMTsat 15 ISIS washers 4 18-8 Stainless Steel Washer 0.05 5 0.711 Yes 1450 See Tables 4-6 NMTsat 16 GAMMA Antenna washers 2 18-8 Stainless Steel washer 0.05 4.089 0.711 Yes 1450 See Tables 4-6 NMTsat 17 GAMMA 1 FR-4 PC/104 stack 227.5 90.297 95.885 10 No - Demise NMTsat 18 Power Board 1 FR-4 PC/104 199.58 90.297 95.885 25 No - Demise NMTsat 19 Pumpkin Flight board 1 FR-4 PC/104 89.67 90.297 95.885 15 No - Demise NMTsat 20 HE-100 Radio 1 FR-4 PC/104 74.185 90.297 95.885 15 No - Demise NMTsat 21 CPU with BeagleBone black 1 FR-4 PC/104 69.28 90.297 95.885 30 No - Demise 57

ELaNa-19 Component List by CubeSat: NMTSat (2/2) Row Individual Diameter/ Length Height High Melting CUBESAT Name Qty Material Body Type Survivability Number Mass (g) Width (mm) (mm) (mm) Temp Temp See Tables 4- NMTsat 22 Structural Rods 4 18-8 Stainless Steel Rods 49.94 3 98 Yes 1450 6 NMTsat 23 ACS 1 FR-4, Hymu 80/Permalloy PC/104 30 90.297 95.885 15 No - Demise NMTsat 24 PCM 1 FR-4 PC/104 29.6 90.297 95.885 15 No - Demise NMTsat 25 MAG 2 FR-4 PC/104 29.6 90.297 95.885 15 No - Demise NMTsat 26 Buffer 1 FR-4 PC/104 29.6 90.297 95.885 15 No - Demise NMTsat 27 RF cables with SSMCX 2 Copper alloy, PVC sheath cable 13.608 No - Demise See Tables 4- NMTsat 28 25mm spacers 16 18-8 Stainless Steel hex cylinder 11.34 6 25 Yes 1450 6 NMTsat 29 Mid plane Standoffs 4 Aluminum 6061 Box 10 99.87 99.87 7 No - Demise NMTsat 30 Other Cables Copper alloy, PVC sheath cable 10 No - Demise Copper alloy with gold NMTsat 31 Stacking Bus Conector 4 Box 6.34 79 12.7 10 No - Demise plating See Tables 4- NMTsat 32 15mm spacers 36 18-8 Stainless Steel hex cylinder 4.536 6 15 Yes 1450 6 NMTsat 33 ELROI circuit board 1 FR-4 PC/104 29.6 90.297 95.885 10 No - Demise Rectangular NMTsat 34 ELROI tube 1 Aluminum 27 25 100 25 No - Demise cylinder 58

NMTsat 35 ELROI lenses 2 Borosilicate glass flat cylinder 1 25 2 25 No - Demise 59

Appendix H. ELaNa-19 Component List by CubeSat: RSat Diameter/ Row Individual Length Height High Melting CUBESAT Name Qty Material Body Type Width Survivability Number Mass (g) (mm) (mm) Temp Temp (mm) Rsat 1 RSat CubeSat 1 Aluminium 6061 A-Frame 4000 113 113 340.5 No - Demise Rsat 2 CubeSat Structure 1 Aluminium 6061 A-Frame 750 100 100 340.5 No - Demise Rsat 3 Arms 2 CRP Windform XT Hollow-core 292 15 15 600 No - Demise Rsat 4 Motors 16 Stainless Steel Cylinder 19.33 12 39 N/A Yes 1450 See Tables 4-6 Rsat 5 Solar Panels 6 Fiberglass Flat pannel 100 83 340.5 1.5 No - Demise Rsat 6 Motor Control Board 32 Fiberglass Flat pannel 15 15 30 6 No - Demise Rsat 7 Batteries 6 Lithium-Ion Cylinder 91 18.3 64.8 N/A No - Demise Rsat 8 ADCS 2 HyMu 80 / Neodymium Cylinder 100 25.4 5 N/A Yes 1454 See Tables 4-6 Rsat 9 Comm Board 1 Fiberglass / Aluminium Box 350 82.5 82.5 17 No - Demise Rsat 10 Battery Frame 2 ABS Frame 30 50 65 30 No - Demise Rsat 11 C&DH Board 1 PCB Flat pannel 100 96 327.5 6 No - Demise Rsat 12 Fasteners ~150 Stainless Steel M2 Screws 1 2 Variable N/A Yes 1510 See Tables 4-6 Rsat 13 Sep Switches 2 Plastic Limit switch 10 10 10 10 No - Demise Rsat 14 Cabling - Copper alloy - - - - - No - Demise 60

Appendix I. ELaNa-19 Component List by CubeSat: Shields-1 (1/2) Diameter/ Row Individual Length Height High Melting CUBESAT Name Qty Material Body Type Width Survivability Number Mass (g) (mm) (mm) Temp Temp (mm) Shields-1 1 Shields-1 3 U CubeSat 1 - Box 6935.35 10 10 34.05 No - Demise Shields-1 2 Mid Structure-Atomic Z Grade Vault 1 - Box - - - - No See Tables 4-6 Shields-1 2.1 Shield -1 4 Aluminum 6061 Sheet 56.0099 95.403 135.9 1.6 No - Demise Shields-1 2.2 Shield 0 4 Ti-6-4 Sheet 113.7832 95.403 135.9 1.981 No 1650 See Tables 4-6 Shields-1 2.3 Shield 1 4 Tantalum Sheet 219.8909792 95.403 135.9 1.016 Yes 2980 See Tables 4-6 Shields-1 2.4 Shield 2 2 Aluminum 6061 Sheet 35.62155203 90.806 90.806 1.6 No - Demise Shields-1 2.5 Shield 3 2 Ti-6-4 Sheet 72.36452329 90.806 90.806 1.981 Yes 1650 See Tables 4-6 Shields-1 2.6 Shield 4 2 Tantalum Sheet 139.8475746 90.806 90.806 1.016 Yes 2980 See Tables 4-6 Shields-1 2.7 Shield 5 2 Aluminum 6061 Sheet 3.420275484 31.75 - 1.6 No - Demise Shields-1 2.8 Shield 6 2 Ti-6-4 Sheet 8.794904361 31.75 - 1.981 Yes 1650 See Tables 4-6 Shields-1 2.9 Shield 7 2 Tantalum Sheet 13.4277482 31.75 - 1.016 Yes 2980 See Tables 4-6 Shields-1 3 Bottom Structure-Research Payload 1 Aluminum 6061 Box 2305.392421 100 142 26.1 No - Demise Shields-1 3.1 Al-Ti Z grade Sample - - - - - - No - Demise Shields-1 3.2 - 1 Aluminum 6061 Sheet 15.00298702 66.497 - 1.6 No - Demise Shields-1 3.3 - 1 Ti-6-4 Sheet 30.4776999 66.497 - 1.981 Yes 1650 See Tables 4-6 Shields-1 3.4 Al-Ti-Ta Z grade Sample (3 g/cm2) - - - - - - No - Demise Shields-1 3.5 - 1 Aluminum 6061 Sheet 15.00298702 66.497 - 1.6 No - Demise Shields-1 3.6 - 1 Ti-6-4 Sheet 30.4776999 66.497 - 1.981 Yes 1650 See Tables 4-6 Shields-1 3.7 - 1 Ta Sheet 14.7225828 66.497 - 0.254 No - Demise Shields-1 3.8 Al-Ti-Ta Z grade Sample (3 g/cm2) - - - - - - - No - Demise Shields-1 3.9 - 1 Aluminum 6061 Sheet 15.00298702 66.497 - 1.6 No - Demise Shields-1 3.10 - 1 Ti-6-4 Sheet 30.4776999 66.497 - 1.981 Yes 1650 See Tables 4-6 Shields-1 3.11 - 1 Ta Sheet 58.8903312 66.497 - 1.016 No - Demise Shields-1 4 Top Structure-Antenna Housing 1 eg. Aluminum 6061 Box 356 100 46.7 100 No - Demise 61

ELaNa-19 Component List by CubeSat: Shields-1 (2/2) Diameter/ Row Individual Length Height High Melting CUBESAT Name Qty Material Body Type Width Survivability Number Mass (g) (mm) (mm) Temp Temp (mm) Shields-1 5 Battery Board 1 Lithium-Ion, PCB Board 310 87 87 1.6 No - Demise Shields-1 6 Antenna 1 Al 6061, PCB box 89 100 100 6.5 No - Demise Shields-1 7 FCPU and Comm Board 1 Al, PCB Board 92 87 87 1.6 No - Demise Shields-1 8 Research Payload Board 2 PCB Board 90 87 87 1.6 No - Demise Shields-1 9 EPS Board 1 PCB - 87.8 87 87 1.6 No - Demise Shields-1 9.1 Voltage Booster 1 Kovar, PCB box 75.7 30 50 10 No - Demise Shields-1 9.2 Voltage Booster Heat Sink 1 Aluminum frame 32.39 30 50 10 No - Demise Shields-1 10 Charge Dissipation Film electrodes 4 SS 305 disk 35.73 25.4 2.921 Yes 1538 See Tables 4-6 Shields-1 10.1 Charge Dissipation Film spring 1 stainless steel spring 5 6.3 12.7 - Yes 1650 See Tables 4-6 Shields-1 11 Charge Dissipation Film housing 1 Ultem Cylinder 32.8 38.1 25.4 - No - Demise Shields-1 11.1 Antenna Rf Connector 1 Copper/Gold Cable 5.01 - - - No - Demise Shields-1 11.2 Omnetics antenna Cabling 9 pin 1 Copper/Gold - 4.75 - - - No - Demise Shields-1 12 Omnetics Research Payload Cabling 3 Copper - 25 - - - No - Demise Shields-1 13 RTDs 10 Stainless Steel, Al, Cu - 1.89 - - - Yes 1650 See Tables 4-6 Shields-1 14 Microdosimeters 8 Kovar, PCB - 20 35.6 25.4 1.016 No - Demise Shields-1 15 Solar Panels 4 Triple Junction GaAs Board 112.33 83.2 317 2.108 No - Demise Shields-1 16 Fasteners 76 A86 stainless Screw 0.5171 2.845 4.7752 - Yes 1510 See Tables 4-6 Shields-1 17 Fasteners 66 A86 stainless Screw 0.5171 2.184 3.048 - Yes 1510 See Tables 4-6 Shields-1 18 Fasteners 8 A86 stainless Screw 0.5171 8 6.35 - Yes 1510 See Tables 4-6 Shields-1 19 Solar Panel Screws 24 SS 4130 Screws 0.25 1.5875 6.35 - Yes 1510 See Tables 4-6 Shields-1 19 Solar Panel Washers 24 SS 4130 Washers 1.00 3.175 1.5875 - Yes 1510 See Tables 4-6 Shields-1 20 Charge Dissipation Film 2 Acrylic - 0.03 25.4 - 0.0508 No - Demise Shields-1 21 Remove Before Flight Pin 1 Stainless Steel, Al switch 20 25.4 12.5 12.5 Yes 1510 See Tables 4-6 Shields-1 22 Sep Switch 1 PCB stainless steel switch 20 25.4 12.5 12.5 Yes 1510 See Tables 4-6 Shields-1 23 ADCS Components (eg. Magnets) 1 AlNiCo Rod 11 6.4 - 35.6 No - Demise Shields-1 24 ADCS Components (Hysteresis Rods) 3 Hymu80 Rod 13 1.588 - 70 Yes 1454 See Tables 4-6 62

Appendix J. ELaNa-19 Component List by CubeSat: STF-1 Diameter/ Row Mass (g) Length Height High Melting CUBESAT Name Qty Material Body Type Width Survivability Number (Ind) (mm) (mm) Temp Temp (mm) STF-1 1 STF-1 3U CubeSat 1 Box No - Demise STF-1 2 CubeSat Structure 1 Aluminum 6082 Box 513 100 100 340.5 No - Demise STF-1 3 UHF Antenna 1 PCB, Aluminum Box 114 102 102 7.13 No - Demise inc. w/ row STF-1 3 UHF Element 2 NiTi-Alloy Box 0.19 15.4 3.1 No - Demise 3 STF-1 4 1U Solar Panel 1 PCB Box 43 98 98 1.57 No - Demise STF-1 5 3U Solar Panel 4 PCB Box 150.5 82.6 337 1.57 No - Demise STF-1 6 Sep Switches 2 Aluminum Thin Wall Cylinder 2.35 est 5.05 11.8 No - Demise STF-1 7 GPS Antenna 1 Composite Radome/Aluminum -T6 Box 88 52.78 52.78 17.53 No - Demise inc. w/ row STF-1 8 LP Element 2 NiTi-Alloy Box 0.19 588.96 3.1 No - Demise 3 STF-1 9 Radio 1 PCB/ Aluminum Box 87 69 69 13.5 No - Demise STF-1 10 Battery 2 PCB/Lithium Polymer Box 338 90.17 95.89 26.7 No - Demise STF-1 11 EPS 1 PCB Box 178 90.17 95.89 15.4 No - Demise STF-1 12 Special Services Board 1 PCB Box 250 est 90.17 95.89 18.09 No - Demise STF-1 13 C&DH Board 1 PCB Box 89 88.88 91.98 23.25 No - Demise STF-1 14 Fasteners Stainless Steel Solid Cylinder 120 est 3.048 - Yes 1510 See Tables 4-6 STF-1 15 Cabling Copper alloy/ Teflon - 80 est - - - No - Demise STF-1 16 Connectors Tin/Gold/ABS - 96 est - - - No - Demise STF-1 17 CSEE Experiment Board 1 PCB Box 122 90.17 95.89 22.19 No - Demise STF-1 17 Ferrite Bead 1 Ferrite Box 0.03 2 1.2 0.9 Yes 1539 See Tables 4-6 STF-1 17 LED Chip Carrier 3 Al2O3 (Ceramic) Box <1.0 10.17 10.17 1.27 No - Demise STF-1 18 Physics Experiment Board 1 PCB Box 191 90.17 95.89 19 No - Demise inc. w/ row STF-1 18 Geiger Tube 2 Stainless Steel/Mica/Neon/Argon Thin Wall Cylinder 15 43 - Yes 1539 See Tables 4-6 15 STF-1 19 IMU Experiment Board 1 PCB Box 47 90.17 95.89 2.6 No - Demise STF-1 20 Camera 1 PCB Box 8 24 34 3 No - Demise inc. w/ row STF-1 20 Camera Lens 1 ABS/Glass Solid Cylinder 13.1 14.75 No - Demise 17 STF-1 21 Debug Port 1 Aluminum/Silicon/Copper Box 44 10.5 33.6 7.5 63

Appendix K. ELaNa-19 Component List by CubeSat: TOMSat EAGLESCOUT Diameter Heigh Row Qt Individual Length High Melting CUBESAT Name Material Body Type / Width t Survivability Number y Mass (g) (mm) Temp Temp (mm) (mm) TOMSat EAGLEScout 1 Full Body Only 1 6061-T6 Box 644 103.494 110.9 340.5 No - Demise TOMSat EAGLEScout 2 Frame Part 1 (2001) 1 6061-T6 Box 298 103.494 110.9 130 No - Demise TOMSat EAGLEScout 3 Frame Part 2 (4001) 1 6061-T6 Box 346 103.494 110.9 209.23 No - Demise TOMSat EAGLEScout 4 Bus Electronics 1 FR4 Box 627 85.046 84.882 97.05 No - Demise TOMSat EAGLEScout 5 Reaction Wheels 1 Stainless Box 225 52.832 71.102 39.192 Yes 1450 See Tables 4-6 TOMSat 6061-T6 (65%), glass (25%), FR4 6 Star Tracker 2 Box 55 26.67 25.4 41.829 No - Demise EAGLEScout (10%) TOMSat EAGLEScout 7 Single Torque Rod 9 HyMu 80 Cylinder 18 8 78.74 - Yes 1300 See Tables 4-6 TOMSat EAGLEScout 8 Zenith Lid Assembly 1 6061-T6 Box 141 103.494 110.9 16.74 No - Demise TOMSat EAGLEScout 9 Antenna 2 Ceramic (95%) with copper foil (5%) Plate 16 39.878 38.099 3.277 No - Demise TOMSat EAGLEScout 10 Wing Assembly 2 6061-T6 Plate 148 2.677 313.5 73.66 No - Demise TOMSat EAGLEScout 11 Nadir Lid Assembly 1 6061-T6 Box 100 103.494 110.9 7.977 No - Demise TOMSat EAGLEScout 12 Antenna 1 Ceramic (95%) with copper foil (5%) Plate 16 39.878 38.099 3.277 No - Demise TOMSat EAGLEScout 13 Uplink Receiver 1 6061-T6 (75%), glass (25%) Cylinder 28 31 31.601 - No - Demise TOMSat 6061-T6 (45%), glass (45%), FR4 14 Payload Assembly 1 Box 1311 82.444 164.58 56.238 No - Demise EAGLEScout (10%) TOMSat EAGLEScout 15 18267 1 Titanium Cylinder 17 32 37.275 - Yes 1650 See Tables 4-6 TOMSat EAGLEScout 16 18265 1 Titanium Cylinder 11 32 16.506 - Yes 1650 See Tables 4-6 TOMSat EAGLEScout 17 18264 1 Titanium Cylinder 12 32 25.999 - Yes 1650 See Tables 4-6 TOMSat EAGLEScout 18 18268 1 Titanium Cylinder 4 39 2.5 - Yes 1650 See Tables 4-6 TOMSat EAGLEScout 19 18266 1 Titanium Cylinder 10 32 5.081 - Yes 1650 See Tables 4-6 TOMSat EAGLEScout 20 18263 1 Titanium Cylinder 1 32 1.649 - Yes 1650 See Tables 4-6 TOMSat EAGLEScout 21 18270 1 Titanium Cylinder 1 32 1.601 - Yes 1650 See Tables 4-6 TOMSat EAGLEScout 22 Laser 1 6061-T6 (90%), stainless steel (10%) Box 353 82.245 120.65 20.192 Yes ~1650 See Tables 4-6 TOMSat EAGLEScout 23 STIM 210 IMU 1 6061-T6 Box 116 48.26 64.77 25.4 No - Demise 64

Appendix L. ELaNa-19 Component List by CubeSat: TOMSat R3 Row Diameter/ Individual Length Height High Melting CUBESAT Numbe Name Qty Material Body Type Width Survivability Mass (g) (mm) (mm) Temp Temp r (mm) TOMSat 1 Full Body Only 1 6061-T6 Box 644 103.494 110.9 340.5 No - Demise R3 TOMSat 2 Frame Part 1 (2001) 1 6061-T6 Box 298 103.494 110.9 130 No - Demise R3 TOMSat 3 Frame Part 2 (4001) 1 6061-T6 Box 346 103.494 110.9 209.23 No - Demise R3 TOMSat 4 Bus Electronics 1 FR4 Box 627 85.046 84.882 97.05 No - Demise R3 TOMSat 5 Reaction Wheels 1 Stainless Box 225 52.832 71.102 39.192 Yes 1450 See Tables 4-6 R3 TOMSat 6061-T6 (65%), glass (25%), FR4 6 Star Tracker 2 Box 55 26.67 25.4 41.829 No - Demise R3 (10%) TOMSat 7 Single Torque Rod 9 HyMu 80 Cylinder 18 8 78.74 - Yes 1300 See Tables 4-6 R3 TOMSat 8 Zenith Lid Assembly 1 6061-T6 Box 141 103.494 110.9 16.74 No - Demise R3 TOMSat 9 Antenna 2 Ceramic (95%) with copper foil (5%) Plate 16 39.878 38.099 3.277 No - Demise R3 TOMSat 10 Wing Assembly 2 6061-T6 Plate 148 2.677 313.5 73.66 No - Demise R3 TOMSat 11 Nadir Lid Assembly 1 6061-T6 Box 100 103.494 110.9 7.977 No - Demise R3 TOMSat 12 Antenna 1 Ceramic (95%) with copper foil (5%) Plate 16 39.878 38.099 3.277 No - Demise R3 TOMSat 13 Uplink Receiver 1 6061-T6 (75%), glass (25%) Cylinder 28 31 31.601 - No - Demise R3 TOMSat 6061-T6 (45%), glass (45%), FR4 14 Payload Assembly 1 Box 1311 82.444 164.58 56.238 No - Demise R3 (10%) TOMSat 15 18267 1 Titanium Cylinder - Hollow 17 32 37.275 - Yes 1650 See Tables 4-6 R3 TOMSat 16 18265 1 Titanium Cylinder - Hollow 11 32 16.506 - Yes 1650 See Tables 4-6 R3 TOMSat 17 18264 1 Titanium Cylinder - Hollow 12 32 25.999 - Yes 1650 See Tables 4-6 R3 TOMSat 18 18268 1 Titanium Cylinder - Hollow 4 39 2.5 - Yes 1650 See Tables 4-6 R3 TOMSat 19 18266 1 Titanium Cylinder - Hollow 10 32 5.081 - Yes 1650 See Tables 4-6 R3 TOMSat 20 18263 1 Titanium Cylinder - Hollow 1 32 1.649 - Yes 1650 See Tables 4-6 R3 65

TOMSat 21 18270 1 Titanium Cylinder - Hollow 1 32 1.601 - Yes 1650 See Tables 4-6 R3 TOMSat 22 Laser 1 6061-T6 (90%), stainless steel (10%) Box 353 82.245 120.65 20.192 Yes ~1650 See Tables 4-6 R3 TOMSat 23 STIM 210 IMU 1 6061-T6 Box 116 48.26 64.77 25.4 No - Demise R3 Appendix M. ELaNa-19 Component List by CubeSat: SHFT-1 Row Body Individual Diameter/ Length Height High Melting CUBESAT Name Qty Material Survivability Number Type Mass (g) Width (mm) (mm) (mm) Temp Temp SHFT-1 1 3U CubeSat 1 Box 5100 113.1 365.8 112.48 No - Demise SHFT-1 2 CubeSat Structure 1 Al 7075-T651 Box 378.7 100 270.7 100 No - Demise SHFT-1 3 Antenna - deployed 4 Steel, Ultem, Al 6061 Boom 458.1 19.05 6000 0.28 No - Demise SHFT-1 4 Solar Panels - deployed 2 FR4, glass, Al 6061 Flat Plate 305 138.38 326.49 57.25 No - Demise SHFT-1 5 ADCS 1 Al 6061 Box 895 100 100 50 No - Demise SHFT-1 6 UHF/GPS Antenna System - deployed 1 Al 6061, brass, RO3006 005 R3 Box 260.3 274 274 115.42 No - Demise SHFT-1 7 S-Band Antenna 1 AD350A, RO450F, RO4003C Box 75 83.82 83.82 5.08 No - Demise SHFT-1 8 Rails 2 Al 7075-T651 Flat Plate 39.9 13.5 366 2.95 No - Demise SHFT-1 9 IXC/GPS Board 1 Polyimide Box 107.2 95.88 90.17 15.75 No - Demise SHFT-1 10 SBC Board 1 Polyimide Flat Plate 88.5 95.88 90.17 10.9 No - Demise SHFT-1 11 EPS Boards with Spacers 1 Polyimide, Al 6061 Box 218.6 95.88 90.17 24.94 No - Demise SHFT-1 12 Battery Assembly 1 Polyimide, Al 6061, 2200SF gap pad, Li Ion Box 298.6 95.88 90.17 27.35 No - Demise SHFT-1 13 Radio 1 OFHC Copper, Al 6061, Polyimide Box 576 96.65 96.65 30.91 No - Demise SHFT-1 14 Payload Boards 1 Polyimide, Al 7075 Box 1093.9 116 96.65 76 No - Demise SHFT-1 15 Internal Fasteners 85 18-8 SSTL, 316 SSTL, Alloy Steel cylinder 1 3 (head 5mm) 10 Yes 1400 See Table 4-6 SHFT-1 16 External Fasteners 134 18-8 SSTL, 316 SSTL cylinder 1 3 (head 5mm) 10 Yes 1400 See Table 4-6 SHFT-1 17 External Covers 6 Al 6061 flat plate 3.4 1.60 20 40 No - Demise SHFT-1 18 Internal Cabling Copper Alloy wires 50 0.5 150 No - Demise 66

Appendix N. ELaNa-19 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 16 No - Demise 4.3.1 Heat Sink 1 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 67

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 68

Appendix O. CubeSail CONOPS Rev8 <see the following page> 69

CubeSail CONOPS Revision 7 April 3, 2018 PRE-DEPLOYMENT OPERATIONS OVERVIEW As stowed aboard the launch vehicle, the two sections of CubeSail are rigidly coupled by the separation release unit (SRU), and flexibly coupled by the solar sail film. Following a successful launch and orbit insertion of the satellite into near sun-synchronous orbit, communication with mission control will be initiated to verify satellite functionality. Next, a detumbling maneuver utilizing the magnetic torquers will commence. After detumbling, the CubeSail spacecraft will be monitored regularly until its orbit has decayed to an altitude of 350 km. This decay is anticipated to take approximately 2 years during which its instrumentation, communications, and ADCS will be tested extensively in its un-deployed state. INITIAL DEPLOYMENT OPERATIONS OVERVIEW Once the orbital altitude has decayed to 350 km or lower, a command is given for CubeSail to orient such that its sail will be perpendicular to Earth’s surface in the long dimension, and edge-on to the ram direction, and face-on to the sun direction after deployment. Once the satellite is stable in this attitude and diagnostic data has been reviewed, the ground station will command initiation of the programmed solar sail deployment sequence, with the scheduled time for initiation specified in the command. The ground station at the University of Illinois campus is the only one that will be used to support this mission. At the scheduled time, the sail deployment initiates and takes place from beginning to end as a programmed sequence, and does not depend on real-time ground control. Each satellite section has a unique sequence of actions which must be executed during deployment. By incorporating appropriate delays in the sequence, sensitivity to clock synchronization has been reduced. On the ground communication pass prior to the intended deployment, both satellite buses will receive clock updates. Following are the main steps in the sequence: 1. The SRU motor spins a leadscrew, to unscrew and rigidly decouple the two sections from each other. The compression springs, mounted on the payload plate, will force the two sections apart. 2. As the sections separate, the slack in the film is reduced. Once the leadscrew has fully cleared its threaded hole, the film is taught and the separation springs remain partially compressed. After an interval, oscillations induced by leadscrew clearing are damped by the springs. 3. The film bobbin motors are activated to pull the sections together using the film, thus compressing the separation springs. The force required by the bobbin motors to compress the separation springs is sensed by the circuit and converted to a rotational bobbin motor film deployment speed. 4. The bobbin motors are then activated and begin deploying film. This deploy velocity matches the separation velocity imparted by the compression springs (5 cm/s), allowing the sections to separate freely as the sail deploys. Cameras on each section of the satellite will capture images of the deployment. 5. As the film nears full deployment, the bobbin motors slow down incrementally to mitigate snapping back when the film becomes taught. 6. Following complete film deployment, the attitude of each of the two CubeSail sections, will be controlled to hold the sail such that its edge is ram-facing (and consequently, the sail will be Page 1 of 3

CubeSail CONOPS Revision 7 April 3, 2018 approximately facing the Sun). The gravity gradient will hold the sail perpendicular to Earth’s surface. This ends the programmed sail deployment sequence. 7. Mission control is notified of sail deploy completion at the next opportunity. During the ensuing phase, data downloads, including health data and images, may be commanded by mission operations. The deployment sequence has been tested extensively on the ground. Dozens of trials were performed on a four degree of freedom simulator using the flight payload hardware. The sequence was also validated during a micro-gravity parabolic flight experiment. All flight software undergoes a peer review process. Development occurs on a coding branch, and is only merged into the flight branch after review by another team member. Below is the timeline for the CubeSail deployment sequence described above. “T” is the pre-scheduled start time, set by a ground command. T = scheduled Event deployment start time T + 0 min Programmed deployment sequence begins: The SRU motor is activated and decouples the two sections from each other. The compression springs force the satellite apart. T + 3 min Programmed deployment sequence: The film bobbin motors pull the sections together and compress the separation springs. T + 4 min Programmed deployment sequence: The film bobbin motors begin deploying film at 5 cm/s. A camera on each bus captures photos of the sail during this time. T + 44 min Programmed deployment sequence: Deployment sequence: As the film reaches full deployment the film bobbin motors slow down. T + 164 min Programmed deployment sequence ends: The film is fully deployed. Utilizing their magnetic torquers the satellite sections continue to orient themselves such that the film’s edge is ram facing. MISSION CONCEPT OF OPERATIONS CubeSail’s orbit will be at 85 degrees inclination, which is a near-polar orbit. With the sail edge in the ram direction, the flat face of the sail will approximately face the sun for the entire orbit. However, CubeSail will not raise orbit under any circumstances – even with the full face of the sail facing the sun, the drag forces from the atmosphere will overpower any forces from solar pressure, and the satellite will continue to deorbit. Page 2 of 3

CubeSail CONOPS Revision 7 April 3, 2018 After approximately 1 week of operation in the sail edge ram-facing configuration, the CubeSail sections will be commanded by mission operations to be reoriented by 90° utilizing the magnetic torquers. This will hold the sail surface ram-facing (and therefore edge-on to the Sun). The ensuing drag from the increased ram facing surface area, will cause CubeSail to deorbit in less than 0.1 years, as described in the ODAR. CubeSail’s mission success will be determined by successful (1) sail deployment, (2) attitude control of the two individual sections of CubeSail, and (3) deorbit. CONJUNCTION PREDICTION AND COLLISION AVOIDANCE CubeSail is registered on Space-Track with 18 SPCS. 18 SPCS screens every satellite at least every 24 hours for potential conjunctions. CubeSail will notify 18 SPCS when sail deployment is scheduled to commence, when sail attitude is scheduled to be modified from edge ram facing to sail face ram facing, and any other configuration changes that may occur. Should a conjunction be predicted, CubeSail may be commanded to change the sail orientation, thus changing its drag profile and significantly changing its rate of velocity change. Upon prediction of a potential conjunction between CubeSail and another object, 18 SPCS will send, and the CubeSail team will receive, emergency notifications in accordance with 18 SPCS’s practices. Should such a notification occur, the CubeSail team will coordinate with the mission operators of the other spacecraft which is at-risk, if it is a spacecraft. To contribute to conjunction risk mitigation, the following options are available to CubeSail and may be coordinated with the other object’s operator: 1) If the sail is in a high-drag configuration, it can be turned to a low-drag configuration, reducing the rate of descent, therefore entirely changing CubeSail’s forward orbit and avoiding the conjunction opportunity, given sufficient time 2) If the sail is in a low-drag configuration, it can be turned to a high-drag configuration, increasing the rate of descent, therefore entirely changing CubeSail’s forward orbit and avoiding the conjunction opportunity, given sufficient time By adjusting the drag of CubeSail, the effect of the atmosphere will either increase or decrease, which inturn speeds up or slows down the descent. With the low-drag “edge-on” configuration, CubeSail will maintain its current orbit like a regular satellite; however, while in the “face-on” high drag configuration, it will see a slow descent through the atmosphere. Page 3 of 3


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