Orbital Debris Assessment Report

0456-EX-PL-2015 Text Documents

California State University, Northridge

2015-10-06ELS_167896

ELVL-2015-xxxxxxx (DRAFT) September 29, 2015 Orbital Debris Assessment for CSUNSat1 Mission per NASA-STD 8719.14A 1

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-xxxxxx Reply to Attn of: VA-H1 September 29, 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 [TBD] Mission (DRAFT) FEERENCES: 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. Email, “FW: ISS Orbital Parameters” Scott Higginbotham to Justin Treptow, March 7, 2014 D. Kwas, Robert. Thermal Analysis of ELaNa-4 CubeSat Batteries, ELVL-2012- 0043254; Nov 2012 E. Range Safety User Requirements Manual Volume 3- Launch Vehicles, Payloads, and Ground Support Systems Requirements, AFSCM 91-710 V3. F. 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 [TBD] mission. Sections 1 through 8 of ref. (b) are addressed in this document; sections 9 through 14 are not applicable and are not presented here. 3

The following table summarizes the compliance status of the ELaNa [TBD] auxiliary payload mission flown on the [TBD] CRS launch, inside the [Orbital Sciences Cygnus or Falcon 9] vehicle. The ELaNa [TBD] 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 1.1 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 4

Section 1: Program Management and Mission Overview The ELaNa [TBD] mission is sponsored by the Space Operations Mission Directorate at NASA Headquarters and is made of the CSUNSat1 CubeSat. The Program Executive is Jason Crusan. Responsible program/project manager and senior scientific and management personnel are as follows: CSUNSat1: Sharlene Katz, Ph.D, Principle Investigator; Program Milestone Schedule Task Date CubeSat Selection [TBD] CubeSat Delivery to NanoRacks [TBD] CubeSat Integration into NanoRacks [TBD] CubeSat Dispenser (NRCSD) Launch Late 2016 Figure 1: Program Milestone Schedule The ELaNa [TBD] mission will be launched as a payload of the [Cygnus / Dragon] resupply vehicle on the [CRS] mission on an [Atlas V / Falcon 9] launch vehicle from CCAFS, Fl. The CubeSat slotted position is identified in Table 2: ELaNa [TBD] CubeSat and in the Appendix. The current launch date is in late 2016. CSUNSat1 will be deployed from a NRCSD dispenser from the ISS, placing the CubeSats in an orbit approximately 400 X 400 km at inclination of 51.6 deg (ref. (c)). CSUNSat1 is in a 2U form factor of 10 cm x 10cm x 22.7 cm, with mass of 2.16kg. Section 2: Spacecraft Description The primary CubeSat will be deployed out of an individual dispenser, as shown in Table 2: ELaNa [TBD] CubeSat below. Table 2: ELaNa [TBD] CubeSat Dispenser CubeSat CubeSat CubeSat CubeSat size Slot Quantity Names Masses (kg) A 1 2U (10 cm X 10 cm X 22.7 cm) CSUNSat1 2.16 5

CSUNSat1 CubeSat Description CSUNSat1 – California State University Northridge (CSUN) / Jet Propulsion Laboratory(JPL) – 2U Figure 2: CSUNSat1 Xray View CSUNSat1 is a 2U CubeSat jointly developed by California State University Northridge (CSUN) and the Jet Propulsion Laboratory (JPL). The objective of the CSUNSat1 mission is to space test a new low-temperature capable, Li-ion battery/supercapacitor hybrid power system. This innovation would reduce the mass and volume of power systems and eliminate the need for wasteful battery heaters and thereby increase the amount of energy and power available at for low-temperatures science and engineering operations encountered in deep space missions. 30 minutes after release from the deployer, CSUNSat1 will power up and execute an initialization process that includes charging the spacecraft battery and deploying the antenna. After initialization the follow mission phases will be executed.  Spacecraft Checkout: A set of tests to verify spacecraft performance and charge the spacecraft battery  Payload Checkout: A single charge/discharge cycle of the payload battery  Primary Experiments: A series of ground station controlled designed to characterize the battery, supercapacitors, and hybrid system at several temperatures  Extended Mission: Based on the successful performance of the primary experiments, the satellite will switch from the spacecraft to the payload battery as the primary source of stored energy for the remainder of the mission. The primary CSUNSat1 structure is made of 5052-H32 Aluminum. The radio and beacon use an ISIS Deployable Antenna System (Double UHF Dipole) made from Aluminum 6082, Polycarbonate, and Nitinol. The solar panel substrates are made of Aluminum 6061 with XTJ cells mounted on them. The remaining components contain all 6

standard commercial off the shelf (COTS) materials, electrical components, and PCBs. CSUNSat1 has no propulsion and no attitude control. There are no pressure vessels, hazardous or exotic materials. The spacecraft’s electrical power storage system consists of Panasonic NCR18650 Lithium batteries. The payload experiment battery is a A123 Systems/Navitas 26650 Li- ion Cell (Manufacturer Serial # TXN10293). Figure 3: 2U CubeSat Specification 7

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. 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 [TBD] 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 [TBD] mission. No passivation of components is planned at the End of Mission for the CubeSats on this 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 (f)). 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. (f)) Assessment of spacecraft compliance with Requirements 4.4-1 through 4.4-4 shows that with a lifetime of 1.1 years maximum the CSUNSat1 is compliant. 8

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. ∑ 𝑺𝒖𝒓𝒇𝒂𝒄𝒆 𝑨𝒓𝒆𝒂 [𝟐 ∗ (𝒘 ∗ 𝒍) + 𝟒 ∗ (𝒘 ∗ 𝒉)] 𝑴𝒆𝒂𝒏 𝑪𝑺𝑨 = = 𝟒 𝟒 Equation 1: Mean Cross Sectional Area for Convex Objects (𝑨𝒎𝒂𝒙 + 𝑨𝟏 + 𝑨𝟏 ) 𝑴𝒆𝒂𝒏 𝑪𝑺𝑨 = 𝟐 Equation 2: Mean Cross Sectional Area for Complex Objects CSUNSat1 is evaluated for this ODAR, 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 CSUNSat1 orbit at deployment is 400 km perigee altitude by 400 km apogee altitude, with an inclination of 51.6 degrees. With an area to mass (2.16 kg) ratio of 0.0128 m2/kg, DAS yields 1.1 years for orbit lifetime for its stowed state, which in turn is used to obtain the collision probability. CSUNSat1 sees less than 0x10^-5 probability of collision. Table 4 below provides complete results. 9

Table 3: CubeSat Orbital Lifetime & Collision Probability CSUNSat1 Mass (kg) 2.16 Mean C/S Area (m^2) 0.0277 Stowed Area-to Mass (m^2/kg) 0.0128 Orbital Lifetime (yrs) 1.1 Probability of collision (1:X) 0.00000 Deployed Mean C/S Area (m^2) 0.0289 Area-to Mass (m^2/kg) 0.0134 Orbital Lifetime (yrs) 1.0 Probability of collision (1:X) 0.00000 10

Figure 4: Orbit Collision vs. Altitude (CSUNSat1 Stowed) 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. The probability of the CSUNSat1 spacecraft collision with debris and meteoroids greater than 10 cm in diameter and capable of preventing post-mission disposal has been calculated to be less than 0x10^-5 probability of collision, for any configuration. This satisfies the 0.001 maximum probability requirement 4.5-1. Since the CubeSat 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 CSUNSat1 to be compliant. Requirement 4.5-2 is not applicable to this mission. 11

Section 6: Assessment of Spacecraft Postmission Disposal Plans and Procedures The CSUNSat1 spacecraft will naturally decay from orbit within 1.0 years after being deployed, 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 of CSUNSat1, in its stowed configuration as the worst case. The area- to-mass is calculated for is as follows: 𝑴𝒆𝒂𝒏 𝑪⁄𝑺 𝑨𝒓𝒆𝒂 (𝒎𝟐 ) 𝒎𝟐 = 𝑨𝒓𝒆𝒂 − 𝒕𝒐 − 𝑴𝒂𝒔𝒔 ( ) 𝑴𝒂𝒔𝒔 (𝒌𝒈) 𝒌𝒈 Equation 3: Area to Mass 0.0227 𝑚2 𝑚2 = 0.0128 2.16 𝑘𝑔 𝑘𝑔 CSUNSat1 results in the worst case orbital lifetime of 1.1 years. 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: 400 km maximum perigee 400 km maximum apogee altitudes with an inclination of 51.6 degrees at deployment from the ISS sometime after September of 2016. The area to mass ratio of 0.0128 m2/kg was imputed for the CSUNSat1. DAS 2.0.2 yields a 1.1 years of orbit lifetime of CSUNSat1 in its stowed / non-deployed state. This meets requirement 4.6-1. For the complete list of CubeSat orbital lifetimes reference Table 3: CubeSat Orbital Lifetime & Collision Probability. Assessment results show compliance. 12

Section 7: Assessment of Spacecraft Reentry Hazards A detailed assessment of the components to be flown on ELaNa [TBD] 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, where the risk to human casualty shall not exceed 1:10,000. There is not enough energy to cause a human casualty if the surviving reentry component has less than 15J. 1. Low melting temperature (less than 1000 °C) components are identified as materials that would not 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 [TBD] High Temperature DAS Analysis Total Debris KickSat-2 High Temp Length / Width Height CubeSat Mass (g) Casualty Area KE (J) Probability Components Diameter (mm) (mm) (mm) (m^2) ISIS Deployable CSUNSAT1 10 1.5 120 5 0.39 0 1:0 Antenna Elements LiFePO4 Battery CSUNSAT1 (contains Stainless 63 33 - 65 0.42 0 1:0 Steel) The majority of components demise upon reentry. The components that survive re-entry show 0 J of energy on impact. From the Debris Casualty Area and the deployment orbit, the probability of human casualty is calculated by DAS results in a 0 probability, satisfying the requirement (1/10,000). Through the method described above, Table 4: ELaNa [TBD] High Temperature DAS Analysis, and the full component lists in the Appendix the KickSat-2 mission components are conservatively shown to be in compliance with Requirement 4.7-1 of NASA-STD-8719.14A. 13

Section 8: Assessment for Tether Missions ELaNa [TBD] will not be deploying any tethers. ELaNa [TBD] satisfy, Section 8’s requirement 4.8-1. 14

Section 9-14 ODAR sections 9 through 14 for the launch vehicle 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-C/Mr. Higginbotham VA-G2/Mr. Poffenberger SA-D2/Mr. Hale SA-D2/Mr. Hidalgo SA-D2/Mr. Hibshman AIS-22/Ms. Nighswonger 15

Appendix Index: Appendix A. ELaNa [TBD] Component List 16

Appendix A. ELaNa [TBD] Component List External/Intern Diameter/ Row Mass Length Height CubeSat Name al (Major/Minor QTY Material Body Type Width Melting Temp (°C) Comment Number (g) (mm) (mm) Components) (mm) CSUNSat1( Entire CSUNSat1 - - - Assembly 2160 100 100 227 - - Assembly) Aluminum 5052-H32, CSUNSat1 1 CubeSat Structure External - Major 1 Box 254 100 100 227 Low Melting Temp Demise Stainless Steel ISIS UHF Antenna CSUNSat1 2 External - Major 1 Aluminum 6061 Box 100 98 98 7 Low Melting Temp Demise (undeployed) ISIS Deployable CSUNSat1 3 External - Major 4 NiTi Alloy Strip metal 10 1.5 120 5 1981 See Table 4 Antenna Elements CSUNSat1 4 Solar Panels External - Major 4 Aluminum 6061 Panel 100 1.6 82 224 Low Melting Temp Demise Hot Shunt Regulator CSUNSat1 5 External - Major 1 FR4/ Sn solder/Cu Board 37 96 92 5 Low Melting Temp Demise Board CSUNSat1 6 Processor Board Internal - Major 1 FR4/ Sn solder/Cu Board 93 96 92 5 Low Melting Temp Demise Cold Shunt Regulator CSUNSat1 7 Internal - Major 1 FR4/ Sn solder/Cu Board 49 96 92 5 Low Melting Temp Demise Board CSUNSat1 8 Battery Control Board Internal - Major 1 FR4/ Sn solder/Cu Board 104 96 92 5 Low Melting Temp Demise Panasonic CSUNSat1 Internal - Minor 1 Li-ion Cylinder 46 19 65 Low Melting Temp Demise NCR18650B Battery Power Processing Unit CSUNSat1 9 Internal - Major 1 FR4/ Sn solder/Cu Board 77 96 92 5 Low Melting Temp Demise 1 Power Processing Unit CSUNSat1 10 Internal - Major 1 FR4/ Sn solder/Cu Board 49 96 92 5 Low Melting Temp Demise 2 CSUNSat1 11 Radio Beacon Board Internal - Major 1 FR4/ Sn solder/Cu Board 79 96 92 5 Low Melting Temp Demise CSUNSat1 12 RF Multiplexer Board Internal - Major 1 FR4/ Sn solder/Cu Board 106 96 92 5 Low Melting Temp Demise CSUNSat1 13 Pigtail Board Internal - Major 1 FR4/ Sn solder/Cu Board 50 96 92 5 Low Melting Temp Demise CSUNSat1 14 Payload Board Internal - Major 1 FR4/ Sn solder/Cu Board 50 96 92 5 Low Melting Temp Demise CSUNSat1 Battery Internal - Major 1 LiFePO4/Stainless steel Cylinder 75 26 65 1500 See Table 4 CSUNSat1 Supercapacitors Internal - Major 2 1100 Aluminum Cylinder 63 33 65 Low Melting Temp Demise Battery/Capacitor CSUNSat1 Internal - Major 1 Aluminum Box 315 10 10 5 Low Melting Temp Demise Clamp CSUNSat1 15 Standoffs, nuts, screws Internal - Minor mulitiple Aluminum/ Copper various 48 various various various Low Melting Temp Demise 17


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Document Modified: 2015-10-01 17:00:59
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