ODAR revision

0020-EX-CN-2016 Text Documents

California Polytechnic State University

2016-09-01ELS_181528

September 1, 2016 Orbital Debris Assessment for DAVE on the JPSS-1 / ELaNa-XIV Mission per NASA-STD 8719.14A Sensitive But Unclassified (SBU)

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. Preliminary Mission Analysis For The Delta II 7920-10 / JPSS-1 Spacecraft Mission, ULA-TP-15-096, July 21, 2015. 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. UL Standard for Safety for Household and Commercial Batteries, UL 2054. UL Standard. 2nd ed. Northbrook, IL, Underwriters Laboratories, 2005 The intent of this report is to satisfy the orbital debris requirements listed in ref. (a) for the DAVE CubeSat, part of the ELaNa-XIV auxiliary mission launching in conjunction with the JPSS-1 primary payload. 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. Sensitive But Unclassified (SBU) 2

The following table summarizes the compliance status of the DAVE CubeSat, part of the ELaNa-XIV auxiliary payload mission flown on JPSS-1. The CubeSat is 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 13.8 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 DAVE mission Sensitive But Unclassified (SBU) 3

Section 1: Program Management and Mission Overview The ELaNa-XIV 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: DAVE: Dr. Jordi Puig-Suari <jpuigsua@calpoly.edu> Dr. John Bellardo <bellardo@calpoly.edu> Justin Foley <jfoley@calpoly.edu> Sensitive But Unclassified (SBU) 4

Program'Milestone'Schedule' Task% Date% CubeSat%Selection% August%5,%2016% CubeSat%Build,%Test,%and%Integration% September%1,%2016% MRR% October%4,%2016% CubeSat%Integration%into%PEPODs% November%7,%2016% CubeSat%Delivery%to%VAFB% January%9,%2017% Launch% January%2017% Figure 1: Program Milestone Schedule The ELaNa-XIV mission will be launched as an auxiliary payload on the JPSS-1 mission on a Delta II 7920-10 launch vehicle from Space Launch Complex 2 West (SLC-2W) at Vandenberg Air Force Base (VAFB). ELaNa-XIV, will deploy 5 pico-satellites (or CubeSats). The CubeSat slotted position is identified in Table 2: ELaNa-XIV CubeSats. The ELaNa-XIV manifest includes: Buccaneer, EagleSat, DAVE, MiRaTA and, RadFXSat. The current launch date is January 20, 2017. The (5) CubeSats will be ejected from a P-POD carrier attached to the launch vehicle, placing the CubeSats in an orbit approximately 440 km X 811 km at inclination of 97.7 deg (ref. (c)). The CubeSat standard form 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. Sensitive But Unclassified (SBU) 5

Section 2: Spacecraft Description There are five CubeSats flying to comprise ELaNa-XIV. The CubeSats will be deployed out of 3 PPODs, as shown in Table 2: ELaNa-XIV CubeSats below. Table 2: ELaNa-2 CubeSats PPOD CubeSat CubeSat CubeSat CubeSat size Slot Quantity Names Masses (kg) 1U (10 cm X 10 cm X 10 cm) EagleSat 1.1 P-POD #1 3 1U (10 cm X 10 cm X 10 cm) DAVE 1.40 1U (10 cm X 10 cm X 10 cm) RadFXSat 1.32 P-POD #2 1 3U (10 cm X 10 cm X 32.5 cm) Buccaneer 3.98 P-POD #3 1 3U (10 cm X 10 cm X 32.5 cm) MiRaTA 4.19 The following subsections contain description of DAVE. ! ! Sensitive But Unclassified (SBU) 6

DAVE CubeSat Description, Cal Poly – 1U The Damping and Vibration Experiment (DAVE) CubeSat implements a payload to evaluate a mechanical damping technology in microgravity. This technology, called particle damping, exploits the dynamics of multiple constrained particles to dissipate vibration energy. Terrestrial applications demonstrate particle damping performance to be largely unaffected by extreme environments yet simple and cheap to implement. This feature set makes particle damping an attractive technology for applications in spacecraft, where dampers are needed to steady sensitive instrumentation and inhibit destructive structural resonant modes. In orbit, DAVE provides a low cost and low risk platform to characterize unknown particle damper microgravity behavior and provide flight heritage for particle damper technology. The completion of these objectives overcomes barriers currently inhibiting the employment of particle dampers in space. DAVE is equipped with one OmniVision imager. The primary purpose of the imager is verifying the rotation rates of the spacecraft prior to performing experiments. The secondary mission is acquiring Earth imagery to support public outreach activities. After deployment from the P-POD, the satellite will power on. Approximately 15 minutes later, antenna deployment will occur. 115 minutes after antenna deployment, the beacon will be activated and the satellite will be available to acquire with the ground station. A full parameter sweep vibration experiment will begin automatically within a few hours of launch. Results will be downloaded over subsequent passes. Additional experiments can be commanded from the ground as necessary to improve confidence in the results. The structure is made entirely of 6061-T6 Aluminum. The antenna is made of NiTi and Delrin. The ceramic piezo electric beam actuators are lead zirconate titanate. The tips of the booms contain tungsten particles. The satellite contains mostly standard commercial off the shelf materials, electrical components, PCBs, and solar cells. There are no pressure vessels, hazardous materials, or exotic materials. The cavities containing the tungsten particles are not freely vented. There are 2x UL listed 3.7V 2600mAh Lithium-Ion 18650 batteries connected in parallel. The UL listing number is MH48285. There is battery protection circuitry and over-charge protection. Sensitive But Unclassified (SBU) 7

Figure 2: 1U CubeSat Specification Figure 3: 3U CubeSat Specification Sensitive But Unclassified (SBU) 8

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 DAVE CubeSat mission therefore this section is not applicable. Sensitive But Unclassified (SBU) 9

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 DAVE 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 low earth orbit environment is negligible (ref (h)). The CubeSat batteries still meet Req. 56450 (4.4-2) by virtue of the HQ OSMA policy regarding CubeSat battery disconnect stating; “CubeSats as a satellite class need not disconnect their batteries if flown in LEO with orbital lifetimes less than 25 years.” (ref. (h)) Assessment of spacecraft compliance with Requirements 4.4-1 through 4.4-4 shows that with a maximum lifetime of 8.4 years the DAVE CubeSat is compliant. Sensitive But Unclassified (SBU) 10

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 five CubeSats, is that of the Buccaneer CubeSat (10 X 10 X 32.5 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 Buccaneer CubeSat has an orbit at deployment of 440 km perigee altitude by 811 km apogee altitude, with an inclination of 97.7 degrees. With an area to mass (3.98 kg) ratio of 0.046 m2/kg, DAS yields 5.2 years for orbit lifetime for its deployed state. Even with the variation in CubeSat design and orbital lifetime ELaNa-XIV CubeSats see an average of 0.00000 probability of collision. Buccaneer, with the largest cross sectional area will see the highest probability of collision of 0.00000. Table 3 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. Sensitive But Unclassified (SBU) 11

Table 3: CubeSat Orbital Lifetime & Collision Probability CubeSat( DAVE( Buccaneer( EagleSat( MiRaTA( RadFXSat( ! Mass((kg)( 1.4! 3.98! 1.1! 4.19! 1.32! ! ! ! ! ! ! ! ! Mean(C/S(Area( 0.0155! 0.38! 0.016! 0.0364! 0.015! (m^2)( AreaDto(Mass( 0.011! 0.009! 0.014! 0.0089! 0.011! Stowed( (m^2/kg)( Orbital(Lifetime( 8.4! 8.5! 7.4! 13.8! 8.5! (yrs)( Probability(of(collision( 0.00000! 0.00000! 0.00000! 0.00000! 0.00000! (10^X)( ! ! ! ! ! ( ! Mean(C/S(Area( 0.0155! 0.183! 0.021! 0.0385! 0.0153! (m^2)( AreaDto(Mass( Deployed( 0.011! 0.046! 0.019! 0.0092! 0.012! (m^2/kg)( Orbital(Lifetime( 8.4! 5.2! 6.6! 12.5! 8.3! (yrs)( Probability(of(collision( 0.00000! 0.00000! 0.00000! 0.00000! 0.00000! (10^X)(

The probability of any ELaNa-XIV 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-XIV 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-XIV spacecraft will naturally decay from orbit within 25 years after end of the mission, satisfying requirement 4.6-1a detailing the spacecraft disposal option. Planning for spacecraft maneuvers to accomplish post-mission disposal is not applicable. Disposal is achieved via passive atmospheric reentry. Calculating the area-to-mass ratio for the worst-case, longest orbital lifetime (smallest Area-to-Mass) post-mission disposal among the CubeSats finds MiRaTA in its stowed configuration as the longest lived. The area-to-mass is calculated for is as follows: !"#$! ! ! !"#$!(!! ) !! = !"#$ − !" − !"##!( ) !"##!(!") !" Equation 3: Area to Mass 0.0374!!! !! = !0.0089 4.19!!" !" MiRaTA has the smallest Area-to-Mass ratio and as a result will have the longest orbital lifetime (worst cast time to deorbit). 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: 440 km maximum perigee 811 km maximum apogee altitudes with an inclination of 97.7 degrees at deployment in January 20 of 2017. An area to mass ratio of 0.0089 m2/kg for the MiRaTA CubeSat was imputed. DAS 2.0.2 (using a solar flux file dated 10/14/2015) yields a 13.8-year orbit lifetime for MiRaTA in its stowed state. This meets requirement 4.6-1. For the complete list of CubeSat orbital lifetimes reference Table 3: CubeSat Orbital Lifetime & Collision Probability. Assessment results show compliance. Sensitive But Unclassified (SBU)

Section 7: Assessment of Spacecraft Reentry Hazards A detailed assessment of the components to be flown on ELaNa-XIV was performed. The assessment used DAS 2.0.2, 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: Survivability Analysis CubeSat( High(Temp(Component( Material( Mass((g)( Demise(Alt((km)( KE((J)( DAVE% PZT%Actuator% Ceramic% 3.5% 0% 0% DAVE% Damping%powder*% Tungsten% 20% 0% 0% *Tungsten powder, total 20 grams, modeled as 200 x 0.1 gram spheres.% A significant number of the high temperature components demise upon reentry. The components that DAS conservatively identifies as reaching the ground have less than 15 joules of kinetic energy. No high temperature 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. Components, reported by DAS to have a demise altitude of 0 km and kinetic energy of 0J, can be assumed to have energy less than one joule as DAS does not supply decimal result. Through the method described above, Table 4, and the full component lists in the Appendix all CubeSats launching under the ELaNa-XIV mission are conservatively shown to be in compliance with Requirement 4.7-1 of NASA- STD-8719.14A. Sensitive But Unclassified (SBU) 14

Section 8: Assessment for Tether Missions DAVE will not be deploying any tethers. DAVE satisfies Section 8’s requirement 4.8-1. Sensitive But Unclassified (SBU) 15

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 805-756-5074. /original signed by/ Justin Foley CubeSat Systems Engineer Cal Poly CubeSat Program, San Luis Obispo Sensitive But Unclassified (SBU) 16

Appendix Index: Appendix A. DAVE Component List Sensitive But Unclassified (SBU) 17

Appendix A. DAVE Component List External/Internal Diameter/ Row Mass Length Low Melting Name (Major/Minor Qty Material Body Type Width Height (mm) Comment Number (g) (mm) Melting Temp Components) (mm) 1 DAVE 1 Various Box 100 100 113.5 Y Demises 2 CubeSat Structure External - Major 1 Aluminum 6061 Box 535 100 100 113.5 Y Demises 3 Antenna Route External - Major 1 Delrin Square 7 65 65 3.5 Y Demises 4 Antenna Wire External - Major 2 Nickel Titanium (NiTi) Rectangular 2.638 2.2 80 12 Y Demises 5 Solar Cells External - Major 10 Eglass Rectangular 2.2512 0.5 68 40 Y Demises 6 Side Panels External - Major 5 FR4 Multilayer PCB Rectangular 35 1.5 83 72 Y Demises 7 Z-Panels External - Major 1 FR4 Multilayer PCB Square 45 1.5 100 100 Y Demises 8 Cavity Caps Internal - Major 3 316 Stainless Steel Box 10.5 20 13 13 Y Demises Ceramic Lead Zirconate Survives with <1J 9 Piezoelectric Internal - Major 3 Box 3.5 2.54 44.45 12.7 N 1350 °C Titanate of energy Actuators Tungsten Survives with <1J 10 Internal - Major 1 Tungsten Powder 20 N/A N/A N/A N 3422 °C Crystalline Powder of energy SMA Actuators 11 Internal - Major 4 Nickel Titanium (NiTi) Wire 0.5 0.05 100 N/A Y Demises Boards SMA Actuators 12 Internal - Major 4 FR4 Multilayer PCB Rectangular 22 1.524 68.707 24.257 Y Demises wire 13 Torque Shaft Internal - Major 1 Aluminum 6061 Cylindrical 3 4 62 Y Demises 14 Locking springs Internal - Major 3 302 Stainless Cylindrical 3 Y Demises Sep/Actuating 15 External - Minor 5 Plastic (PBT) Rectangular 2 6 8 7 Y Demises Switches 16 Batteries Internal - Major 2 Lithium Ion Cylindrical 90.7 26.3 65.8 N/A Y Demises 17 Payload Board Internal - Major 2 FR4 Multilayer PCB Board 33 1.5 83 83 Y Demises 18 Sensor Board Internal - Major 3 FR4 Multilayer PCB Board 5 1.5 32 32 Y Demises 19 Comm Board Internal - Major 1 FR4 Multilayer PCB Board 12 1.5 83 36 Y Demises 20 Breakout Board Internal - Major 1 FR4 Multilayer PCB Board 12 1.5 83 36 Y Demises 21 C&DH Board Internal - Major 1 FR4 Multilayer PCB Board 30 1.5 83 83 Y Demises 22 Fasteners Internal - Minor 1 18-8 Stainless Screw 35 2.2 Various N/A Y Demises Internal/External - 23 Staking Compound 1 3M Scotch Weld 2216 Rectangular 15 N/A N/A N/A Y Demises Minor RNF-100 Polyolefin 24 Heat Shrink Internal - Minor 1 Tube 0 N/A N/A N/A Y Demises Heat Shrink Internal/External - 25 Kapton Tape 1 Kapton Tape Tape 0 Various Various 0.05 Y Demises Minor Sensitive But Unclassified (SBU)


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Document Modified: 8620-04-26 00:00:00
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