ODAR

0476-EX-PL-2015 Text Documents

The University of Texas at Austin

2015-07-28ELS_165207

ELVL-2015-0044079 (DRAFT) July 13, 2015 Orbital Debris Assessment for The CubeSats on the STP-2 /ELaNa-XV Mission per NASA-STD 8719.14A

Signature Page _______________________________ Justin Treptow, Analyst, NASA KSC VA-H1 ________________________________ Scott Higginbotham, Mission Manager, NASA KSC VA-C _________________________________ Jason Crusan, Program Executive, NASA HQ SOMD _________________________________ Suzanne Aleman, NASA HQ OSMA MMOD Program Executive Signatures Required for Final Version of ODAR _________________________________ Terrence W. Wilcutt, NASA Chief, Safety and Mission Assurance _________________________________ William Gerstenmaier, NASA AA, Human Exploration and Operations Mission Directorate. 2

National Aeronautics and Space Administration John F. Kennedy Space Center, Florida Kennedy Space Center, FL 32899 ELVL-2015-0044079 Reply to Attn of: VA-H1 July 13, 2015 TO: Scott Higginbotham, LSP Mission Manager, NASA/KSC/VA-C FROM: Justin Treptow, NASA/KSC/VA-H1 SUBJECT: Orbital Debris Assessment Report (ODAR) for the ELaNa-XV Mission (DRAFT) 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. Higginbotham, Scott. “RE: Please confirm the mission launching ELaNa-15” 6 July 2015. E-mail. 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 Version: DRAFT – Technical information in this DRAFT is subject to change. Please see official release for finalized components and analysis. The intent of this report is to satisfy the orbital debris requirements listed in ref. (a) for the ELaNa-XV auxiliary mission launching in conjunction with the STP-2 primary payload. It serves as the final submittal in support of the spacecraft Safety and Mission Success Review (SMSR). Sections 1 through 8 of ref. (b) are addressed in this document; sections 9 through 14 fall under the requirements levied on the primary mission and are not presented here. 3

The following table summarizes the compliance status of the ELaNa-XV auxiliary payload mission flown on STP-2. The 3 CubeSats comprising the ELaNa-XV 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 Minimal risk to orbital environment, mitigated by orbital lifetime. 4.4-2 Compliant Minimal risk to orbital environment, mitigated by orbital lifetime. 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 4.0 yrs 4.6-1(b) Not applicable 4.6-1(c) Not applicable 4.6-2 Not applicable 4.6-3 Not applicable 4.6-4 Not applicable Passive disposal 4.6-5 Compliant 4.7-1 Compliant Non-credible risk of human casualty 4.8-1 Compliant No planned tether release under ELaNa-XV mission 4

Section 1: Program Management and Mission Overview The ELaNa-XV mission is sponsored by the Space Operations Mission Directorate at NASA Headquarters. The Program Executive is Jason Crusan. Responsible program/project manager and senior scientific and management personnel are as follows: ARMADILLO: Dr. E. Glenn Lightsey, Principle Investigator; Cody Colley, Project Manager LEO: Jordi Puig-Suari, Principal Investigator, Alex Wargo, Project Manager StangSat: Tracey Beatovich Principal Investigator, Brian Robusto, Project Manager 5

Program Milestone Schedule Task Date CubeSat Selection October 2014 MRR May 2016 Pre-Ship Review June 2016 CubeSat Delivery to KAFB July 2016 Launch September 2016 Figure 1: Program Milestone Schedule The ELaNa-XV mission will be launched as an auxiliary payload on the STP-2 mission on a (Falcon 9 Heavy) launch vehicle from KSC, FL. The ELaNa-XV, will deploy 3 pico-satellites (or CubeSats). The CubeSat slotted position is identified in Table 2: ELaNa-XV CubeSats. The ELaNa-XV manifest includes: ARMADILLO, LEO, StangSat. The current launch date is in (Sept 15, 2016). The (3) CubeSats will be ejected from a PPOD carrier attached to the launch vehicle, placing the CubeSats in an orbit approximately 300 X 860 km at inclination of 28.5 deg (ref. (c)). Each CubeSat ranges in sizes from a 10 cm cube to 10 cm x 10cm x 30 cm, with masses from about 1 kg to 4 kg total. The CubeSats have been designed and universities and government agencies and each have their own mission goals. 6

Section 2: Spacecraft Description There are three CubeSats flying on the ELaNa-XV. The CubeSats will be deployed out of 2 PPODs, as shown in Table 2: ELaNa-XV CubeSats below. Table 2: ELaNa-XV CubeSats CubeSat CubeSat CubeSat PPOD Slot CubeSat size Quantity Names Masses (kg) A 3U (10 cm X 10 cm X 30 cm) ARMADILLO [4.15] B 3 2U (10 cm X 10 cm X 20 cm) LEO [1.9] C 1U (10 cm X 10 cm X 10 cm) StangSat [0.77] The following subsections contain descriptions of these 3 CubeSats. 7

ARMADILLO – UNIVERSITY OF TEXAS – 3U Figure 2: ARMADILLO Expanded View (Not Showing Solar Panels) ARMADILLO will demonstrate the GPS Radio Occultation technique using a custom dual frequency GPS receiver and characterize the sub-millimeter space debris environment within the deployment orbit using a dedicated debris detector. For this mission, the Texas Spacecraft Laboratory will utilize a software defined ground station to communicate with the spacecraft and downlink science data. The spacecraft uses the He-100 radio manufactured by Astronautical Development, LLC at uplink and downlink baud rates of 9600 and 19200 bps respectively. Upon deployment, the spacecraft will wait for a [TBD] period specified by the Launch Provider, then deploy its antennas and begin start up activities. These include detumble and transmission of the spacecraft’s health beacon. After an initial checkout the spacecraft operators will schedule a daily occultation observation—in which the spacecraft’s GPS antenna is pointed in the anti-velocity vector—and extended periods of observation with a debris detector pointed into the velocity vector. In conjunction with AMES Research Center, the spacecraft will also be occasionally pointed to a [TBD] ground station for laser ranging experiments using a corner cube reflector. The primary mission will last at least 6 months, with extended operations continuing as long as the spacecraft is capable of doing so. 8

The primary CubeSat structure is made of 6061-T6 aluminum. It contains all standard commercial off the shelf (COTS) materials, electrical components, PCBs and solar cells. There are no pressure vessels, hazardous or exotic materials. The electrical power storage system consists of common lithium-ion 18650 cell batteries with over-charge/current protection circuitry. They are the GOMSpace, ApS NanoPower BP4 battery pack. 9

LEO – Cal Poly – 2U Figure 3: LEO Expanded View LEO will record vibrational and thermal measurements with two accelerometers and a thermocouple and also record vibrational data taken by a second CubeSat that will be transferred through WiFi during launch. Upon deployment from the P-POD, LEO will turn off its WiFi module and take pictures of the StangSat CubeSat as they separate. 45 minutes after deployment the antenna will be deployed and the UHF beacon will be activated. For the first few passes the ground station operators will attempt communications to perform checkouts of the spacecraft. Data from the requested EOI (events of interest) will then be able to be downlinked. The CubeSat structure is made of Aluminum 6061-T6. It contains all standard commercial off the shelf (COTS) materials, electrical components, PCBs and solar cells. There are no pressure vessels, hazardous or exotic materials. The electrical power storage system consists of common lithium-ion batteries with over- charge/current protection circuitry. 10

StangSat – Merritt Island High School - 1U Figure 4: StangSat Expanded View StangSat will record vibrational and shock measurements with two accelerometers located on the Top Plate shown above. This dynamic data will also be transmitted to our sister satellite LEO inside the PPOD over WiFi during launch. Upon deployment from the P-POD, StangSat will be utilized as a ground reflective object while also bleeding down batteries to an acceptable level for reentry. StangSat has no capability to and will not transmit to the ground with our low power WiFi transmission. No additional transmission capability exists on StangSat. The CubeSat structure is made of Aluminum 6061-T6. The side and bottom plate contains all standard commercial off the shelf (COTS) materials, electrical components and “PCB clips” provided by Pumpkin (www.cubesatkit.com). The top plate which houses the accelerometers and signal board was custom machined and also made of Aluminum 6061-T6. StangSat contains no pressure vessels, hazardous or exotic materials. The electrical power storage system consists of Clyde Space procured lithium polymer batteries with over-charge/current protection circuitry included on the EPS module. 11

Figure 5: 1U CubeSat Specification Figure 6: 3U CubeSat Specification 12

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-XV CubeSat mission therefore this section is not applicable. 13

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-XV mission. The probability of battery explosion is very low, and, due to the very small mass of the satellites and their short orbital lifetimes the effect of an explosion on the far-term LEO environment is negligible (ref (h)). The CubeSats batteries still meet Req. 56450 (4.4-2) by virtue of the HQ OSMA policy regarding CubeSat battery disconnect stating; “CubeSats as a satellite class need not disconnect their batteries if flown in LEO with orbital lifetimes less than 25 years.” (ref. (h)) Assessment of spacecraft compliance with Requirements 4.4-1 through 4.4-4 shows that with a lifetime of 1.3 years maximum the ELaNa-XV CubeSat is compliant. 14

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 three CubeSats is that of the ARMADILLO CubeSat (10 X 10 X 30 cm): !"#$%&'!!"#$ !∗ !∗! +!∗ !∗! !"#$!!"# = ! = ! ! Equation 1: Mean Cross Sectional Area for Convex Objects !!"# + !! + !! !"#$!!"# = ! ! Equation 2: Mean Cross Sectional Area for Complex Objects All CubeSats evaluated for this ODAR are stowed in a convex configuration, indicating there are no elements of the CubeSats obscuring another element of the same CubeSats from view. Thus, mean CSA for all stowed CubeSats was calculated using Equation 1. This configuration renders the longest orbital life times for all CubeSats. Once a CubeSat has been ejected from the P-POD and deployables have been extended Equation 2 is utilized to determine the mean CSA. Amax is identified as the view that yields the maximum cross-sectional area. A1 and A2 are the two cross-sectional areas orthogonal to Amax. Refer to Appendix A for dimensions used in these calculations The ARMADILLO CubeSat has an orbit at deployment of 300 km perigee altitude by 860 km apogee altitude, with an inclination of 28.5 degrees. With an area to mass (4.15 kg) ratio of 0.009 m2/kg, DAS yields 4.0 years for orbit lifetime for its stowed state. Even with the variation in CubeSat design and orbital lifetime ELaNa-XV CubeSats see an average of 0.00000 probability of collision. ARMADILLO, with the largest cross sectional area will see the highest 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. 15

Table 3: CubeSat Orbital Lifetime & Collision Probability CubeSat ARMADILLO LEO StangSat Mass (kg) [4.15] [0.762] [0.77] Mean C/S Area (m^2) 0.039 0.025 0.017 Area-to Mass (m^2/kg) 0.009 0.033 0.023 Stowed Orbital Lifetime (yrs) 4.0 2.8 1.3 Probability of collision 0.00000 0.00000 0.00000 (10^X) Mean C/S Area (m^2) 0.039 0.025 0.017 Deployed Area-to Mass (m^2/kg) 0.009 0.033 0.023 Orbital Lifetime (yrs) 4.0 2.8 1.3 Probability of collision 0.00000 0.00000 0.00000 (10^X)

The probability of any ELaNa-XV 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-XV 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-XV 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 StangSat in its stowed configuration as the worst case. The area-to-mass is calculated for is as follows: !"#$! ! ! !"#$!(!! ) !! = !"#$ − !" − !"##!( ) !"##!(!") !" Equation 3: Area to Mass 0.0174!!! !! = !0.023 !0.77!" !" Equation 4: Area to Mass Calculation of StangSat (Deployed) StangSat has the smallest Area-to-Mass ratio and as a result will have the longest orbital lifetime. The assessment of the spacecraft illustrates they are compliant with Requirements 4.6-1 through 4.6-5. DAS 2.0.2 Orbital Lifetime Calculations: DAS inputs are: 300 km maximum perigee 860 km maximum apogee altitudes with an inclination of 28.5 degrees at deployment in September of 2016. An area to mass ratio of 0.009 m2/kg for the ARMADILLO CubeSat was imputed. DAS 2.0.2 yields a 4.0 year orbit lifetime for ARMADILLO in its stowed state. This meets requirement 4.6-1. For the complete list of CubeSat orbital lifetimes reference. Assessment results show compliance.

Section 7: Assessment of Spacecraft Reentry Hazards A detailed assessment of the components to be flown on ELaNa-XV was performed. The assessment used DAS 2.0, a conservative tool used by the NASA Orbital Debris Office to verify Requirement 4.7-1. The analysis is intended to provide a bounding analysis for characterizing the survivability of a CubeSat’s component during re-entry. For example, when DAS shows a component surviving reentry it is not taking into account the material ablating away or charring due to oxidative heating. Both physical effects are experienced upon reentry and will decrease the mass and size of the real-life components as the reenter the atmosphere, reducing the risk they pose still further. The following steps are used to identify and evaluate a components potential reentry risk relative to the 4.7-1 requirement of having less than 15 J of kinetic energy and a 1:10,000 probability of a human casualty in the event the survive reentry. 1. Low melting temperature (less than 1000 °C) components are identified as materials that would never survive reentry and pose no risk to human casualty. This is confirmed through DAS analysis that showed materials with melting temperatures equal to or below that of copper (1080!°C) will always demise upon reentry for any size component up to the dimensions of a 1U CubeSat. 2. The remaining high temperature materials are shown to pose negligible risk to human casualty through a bounding DAS analysis of the highest temperature components, stainless steel (1500°C). If a component is of similar dimensions and has a melting temperature between 1000 °C and 1500°C, it can be expected to posses the same negligible risk as stainless steel components. See Table 4. Table 4: ELaNa-VX Stainless Steel DAS Analysis High Temp Length / Width Height Demise CubeSat Material Mass (g) KE (J) Components Diameter (mm) (mm) (mm) Alt (km) Stainless ARMADILLO Fasteners 15 3.05 2.54 1.67 71.1 - Steel Reaction Wheel – Stainless ARMADILLO 200 50 15 - 63.4 - Wheel Steel Steel LEO Antennae [20] 163 0.24 0.48 0 0.0 410 StangSat Spacers Steel 3 7 3 - 74.8 - The majority of stainless steel components demise upon reentry. The components that DAS conservatively identifies as reaching the ground have 1 or less joules of kinetic energy, far below the requirement of 15 joules. No stainless steel component will pose a risk to human casualty as defined by the Range Commander’s Council. In fact, any injury incurred or inflicted by an object with such low energy would be negligible and wouldn’t require the individual to seek medical attention. Through the method described above, Table 4: ELaNa-VX Stainless Steel DAS Analysis, and the full component lists in the Appendix all CubeSats launching under the ELaNa- XV mission are conservatively shown to be in compliance with Requirement 4.7-1 of 18

NASA-STD-8719.14A. Section 8: Assessment for Tether Missions ELaNa-XV CubeSats will not be deploying any tethers. ELaNa-XV CubeSats satisfy Section 8’s requirement 4.8-1. 19

Section 9-14 ODAR sections 9 through 14 for the launch vehicle are addressed in ref. (g), and 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. Poffenberger SA-D2/Mr. Frattin SA-D2/Mr. Hale SA-D2/Mr. Henry Analex-3/Mr. Davis Analex-22/Ms. Ramos 20

Appendix Index: Appendix A. ELaNa-XV Component List by CubeSat: ARMADILLO Appendix B. ELaNa-XV Component List by CubeSat: StangSat Appendix C. ELaNa-XV Component List by CubeSat: LEO *Note for this DRAFT version of the ODAR a number of component items dimensions and materials have been left empty [TBD] and will be updated upon final release of this document 21

Appendix A. ELaNa-XV Component List by CubeSat: ARMADILLO External/Internal Mass (g) Diameter/ Length Height High Melting Name (Major/Minor Qty Material Body Type Survivability (total) Width (mm) (mm) (mm) Temp Temp Components) ARMADILLO 3U CubeSat 1 Aluminum 6061- shelled box (2.5 CubeSat Structure External - Major 1 1170 113.5 113.5 340.5 No - Demise T6511 mm thick) Aluminum, FR4 PCB, Antennae System External - Major 4 box 86 98 98 5.8 No - Demise flex PCB Germanium, glass, Solar Panels (long) External - Major 4 sheet 512 83 340.5 2.4 No - Demise FR4 PCB, copper Germanium, glass, Solar Panels (short) External - Major 5 sheet 63 98 98 1.6 No - Demise FR4 PCB, copper Thermoplastic acetal, Separation Switches External - Minor 5 copper, steel, silver box 42.5 20 12 6.5 No - Demise plated bronze Sun Sensors External - Major 2 Aluminum, copper box 66.5 32 34 20 No - Demise Lithium-ion, FR4 Batteries Internal - Major 4 box 240 94 88 20 No - Demise PCB, aluminum FR4 PCB, copper, EPS Board Internal - Major 1 various electronic box 90 94 88 15 No - Demise components Copper wire, magnetic Magnetic Torque Rods Internal - Major 3 cylinder 81.5 10 70 - No - Demise alloy rod Aluminum, Nitronic, Reaction Wheels Internal - Major 3 Acetal, Samarium box 369 50 50 29.5 No - Demise Cobalt, Stainless Steel Demise at Reaction Wheel - Wheel Internal - Major 3 Stainless Steel cylinder 300 50 15 - Yes 1500 63.4 km Altitude FR4 PCB, copper, Magnetometer Internal - Major 1 various electronic box 23.5 75 30.5 13 No - Demise components

External/Internal Mass (g) Diameter/ Length Height High Melting Name (Major/Minor Qty Material Body Type Survivability (total) Width (mm) (mm) (mm) Temp Temp Components) FR4 PCB, copper, Gyroscopes Internal - Major 3 various electronic box 7.5 25 25 6.5 No - Demise components FR4 PCB, copper, UHF/VHF Radio Internal - Major 1 aluminum, various box 68 94 88 13 No - Demise electronic components FR4 PCB, copper, phyCORE-LPC3250 Internal - Major 2 various electronic box 30 70 58 8.5 No - Demise components FR4 PCB, copper, Kesler Interface Board Internal - Major 1 various electronic box 60 94 88 15 No - Demise components FR4 PCB, copper, Horton Interface Board Internal - Major various electronic box 10 65 57 12 No - Demise components FR4 PCB, copper, Kraken Interface Board Internal - Major 1 various electronic box 60 94 88 15 No - Demise components FR4 PCB, copper, Hudson Interface Board Internal - Minor 1 various electronic box 10 65 57 12 No - Demise components Piezo Dust Detector - Single Internal - Major 1 [TDB] [TDB] [TDB] [TDB] [TDB] No - Demise Detector Demise at Fasteners Internal - Minor Many Stainless steel [TDB] 150 [TDB] [TDB] [TDB] Yes 1500 71.1km Atltitude Cabling Internal - Minor Many Copper alloy [TDB] 150 [TDB] [TDB] [TDB] No - Demise FR4 PCB, copper, PDD SDU Internal - Major 1 box 21.35 30 30 21 No - Demise aluminium FR4 PCB, copper, PDD MDU Internal - Major 1 box 170.6 100 100 21 No - Demise aluminium PDD DCU Internal - Major 1 FR4 PCB, copper box 86.4 81.3 50.8 36 No - Demise rectangular Camera Both-Major 1 158.4 38 38 74 No - Demise prism 23

External/Internal Mass (g) Diameter/ Length Height High Melting Name (Major/Minor Qty Material Body Type Survivability (total) Width (mm) (mm) (mm) Temp Temp Components) FR4 PCB, copper, FOTON Internal - Major 1 various electronic box 350 96 82.67 35.56 No - Demise components 6061-T6 ALUMINUM ALLOY BASE, COMPOSITE RADOME, IMPACT, GPS Antenna External - Major 1 ABRASION, UV, box 74 50.8 50.8 13.54 No - Demise SOLVENT, SKYDROL RESISTANCE, AND FIRE RETARDANT Retroreflector Exterior - Minor 1 - [TDB] [TDB] [TDB] [TDB] [TDB] No - Demise Retroreflector bracket Exterior - Minor 1 - [TDB] [TDB] [TDB] [TDB] [TDB] No - Demise 24

Appendix B. ELaNa-XV Component List by CubeSat: LEO External/Internal Melting Diameter/ Length Height High Name (Major/Minor Qty Material Body Type Mass (g) Temp Survivability Width (mm) (mm) (mm) Temp Components) (C) LEO - 1 - - 1900 - - - - - - CubeSat Structure External - Major 1 Aluminum 6061 Box 500 100.2 100.2 200 No - Demise Survives to Antennae External - Major 1 Steel 410 [TBD] [TBD] 163 0.24 0.48 Yes ground with < 1J of energy Solar Panels External - Major 18 Fiberglass [TBD] [TBD] [TBD] [TBD] [TBD] No - Demise Sep Switches External - Minor 1 [TBD] [TBD] [TBD] [TBD] [TBD] [TBD] - - Demise Batteries Internal - Major 2 [TBD] [TBD] 91.6 [TBD] [TBD] [TBD] - - Demise Battery Mount Internal - Major 1 Aluminum 6061 [TBD] 28.22 [TBD] [TBD] [TBD] No - Demise Telemetry Interface Board [TBD] [TBD] [TBD] [TBD] 50 [TBD] [TBD] [TBD] - - Demise Comm Board [TBD] [TBD] [TBD] [TBD] [TBD] [TBD] [TBD] [TBD] - - Demise Linux Board [TBD] [TBD] [TBD] [TBD] 22.5 [TBD] [TBD] [TBD] - - Demise C Board [TBD] [TBD] [TBD] [TBD] 22.5 [TBD] [TBD] [TBD] - - Demise Z Sensor Board [TBD] [TBD] [TBD] [TBD] [TBD] [TBD] [TBD] [TBD] - - Demise Sensor Mounting Block Internal - Major 1 Aluminum 6061 [TBD] 47.75 [TBD] [TBD] [TBD] No - Demise Fasteners Internal - Minor [TBD] [TBD] [TBD] [TBD] [TBD] [TBD] [TBD] - - Demise Cabling Internal - Minor [TBD] Copper alloy [TBD] [TBD] [TBD] [TBD] [TBD] No - Demise 25

Appendix C. ELaNa-XV Component List by CubeSat: StangSat External/Internal Body Mass Diameter/ Length Height High Melting Name (Major/Minor Qty Material Survivability Type (g) Width (mm) (mm) (mm) Temp Temp Components) StangSat - 1 - - 770 - - - - - Demise Pumpkin External Skelet External - Major 1 Aluminum T6-6061 218 105.15 105.3 113.6 No - Demise Structure on FR4, Steel, Nylon, Copper, Glass- Motherboard Internal - Major 1 Filled Polyester, Phosphor Bronze, - 79 96.12 92.21 13.16 No - Demise Gold Plating FR4, Aluminum, Silicon, Glass- PPM w/ Fasteners Internal - Major 1 Filled Polyester, Phosphor Bronze, - 21 54.6 89.5 1.6 No - Demise Gold Plating FR4, Aluminum, Silicon, Li- Battery w/EPS board Internal - Major 1 Polymer, Glass-Filled Polyester, - 233 90 95 22 No - Demise Phosphor Bronze, Gold Plating FR4, Aluminum, Silicon, Nylon, Gold-Plated Brass, Glass-Filled Telemetry Board Internal - Major 1 - 84 96 90.4 35 No - Demise Polyester, Phosphor Bronze, Gold Plating FR4, Aluminum, Silicon, Nylon, Signal Board Internal - Major 1 - 40 99.14 99.15 1.61 No - Demise Gold-Plated Brass Wi-Fi Transmitter Internal - Minor 1 FR4, Steel - 15 [TDB] [TDB] [TDB] No - Demise Demise at 74.8 Mounting Rod / Spacers Internal - Minor 4 Steel, Aluminum - 31 7 - 3 Yes 1500 km Altitude Accellerometer (100G) Internal - Minor 1 Aluminum, Epoxy, Steel, Copper - 22 25.4 21.6 10.8 No - Demise Accellerometer 2 (25G) Internal - Minor 1 Aluminum, Epoxy, Steel, Copper - 22 25.4 21.6 10.8 No - Demise Copper, Vinyl, Beryllium Copper, Cabling Internal - Minor 1 - 5 [TDB] [TDB] [TDB] No - Demise Gold-Plating 26


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