ODAR

1288-EX-ST-2015 Text Documents

Cornell University

2016-01-07ELS_171109

ELVL-2015-0044145 September 28, 2015 Orbital Debris Assessment for KickSat-2 Mission per NASA-STD 8719.14A 1

Signature Page Loe Ts Justin/Areptow, Analyst, NASA KSC VA—H1 Actbay Scott Higginbotham, Miséfon 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.

National Aeronautics and Space Administration John F. Kennedy Space Center, Florida Kennedy Space Center, FL 32899 ELVL-2015-0044145 Reply to Attn of: VA-H1 September 28, 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 KickSat-2 Mission 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 G. Email, “RE: KickSat-2” Jer-Chyi Liou to Scott Higginbotham, August 3, 2015 The intent of this report is to satisfy the orbital debris requirements listed in ref. (a) for the KickSat-2 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 KickSat-2 auxiliary payload mission flown on the OA-6, inside the Orbital Sciences Cygnus vehicle. The KickSat-2 CubeSat is fully compliant with all applicable requirements. Table 1: Orbital Debris Requirement Compliance Matrix Requirement Compliance Assessment Comments 4.3-1a Compliant Sprites will have lifetime of 2-6 days 4.3-1b Compliant Object-time product is < 2.5 years 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 0.8 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 4

Section 1: Program Management and Mission Overview The KickSat-2 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: KickSat-2: Zack Manchester, Principle Investigator; Program Milestone Schedule Task Date CubeSat Selection 6/22/2015 CubeSat Delivery to NanoRacks 12/8/15 CubeSat Integration into NanoRacks 12/9/15 CubeSat Dispenser (NRCSD) Launch 3/10/16 Figure 1: Program Milestone Schedule The KickSat-2 mission will be launched as a payload of the Cygnus resupply vehicle on the OA-6 mission on an Atlas V launch vehicle from CCAFS, Fl. The CubeSat slotted position is identified in Table 2: KickSat CubeSats and in the Appendix. The current launch date is in 3/10/2016. KickSat-2 will be deployed from a NRCSD dispenser from the ISS, placing the CubeSats in an orbit approximately 410 X 400 km at inclination of 51.6 deg (ref. (c)). KickSat-2 is in a 3U form factor of 10 cm x 10cm x 30 cm, with mass of 2.256kg. Section 2: Spacecraft Description The primary CubeSat will be deployed out of an individual dispenser, as shown in Table 2: KickSat CubeSats below. Table 2: KickSat CubeSats Dispenser CubeSat CubeSat CubeSat CubeSat size Slot Quantity Names Masses (kg) A 1 3U (10 cm X 10 cm X 30 cm) KickSat-2 2.256 5

KickSat-2 CubeSat Description Cornell University – 3U Figure 2: KickSat-2 Expanded View KickSat-2 is a technology demonstration mission for the Sprite centimeter-scale “ChipSat” developed at Cornell University. The Sprite is a 3.5-by-3.5 centimeter printed circuit board spacecraft that is capable of collecting and processing sensor measurements and communicating directly with ground stations. KickSat-2 is designed to deploy 100 Sprites in low-Earth orbit. The primary mission objective is to demonstrate the Sprite’s CDMA communication architecture. Upon deployment from the PPOD, KickSat-2 will power up and start a countdown timer. After 45 minutes, a dipole antenna will be deployed and a UHF beacon will be activated. An onboard GPS receiver will be used to perform orbit determination. Once the spacecraft’s orbital altitude has decayed to 325 km, Sprite deployment will be triggered by a command from Cornell’s ground station. The primary CubeSat structure is made of 5052-H32 aluminum. The majority of its internal components are made of 6061 aluminum, ABS plastic, and FR4 printed circuit boards. There are few steel components (fasteners, deployment spring). 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. The lithium batteries carry the UL-listing number MH19896. 6

Figure 3: 3U 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. 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. KickSat-2 will be releasing 100 “Sprites” as part of its primary mission to provide a technology demonstration for the use of CDMA communications across multiple vehicles to one ground station. After being deployed from the ISS, KickSat-2 will wait 45 minutes before deploying its primary antenna and activating its radio beacon. The spacecraft will then calculate its orbital position and velocity and set its real-time clock using the onboard GPS receiver. It is expected that contact will be established with either Cornell’s ground station or partner ground stations within the spacecraft’s first few orbits. After performing checkout operations, the spacecraft will be put into a power-safe mode with its radio beacon transmitting at regular intervals. Orbital elements will be propagated by the flight computer and updated using the onboard GPS receiver once per day. KickSat’s orbit will be allowed to decay until an altitude of 325 km is reached. Simulations, performed by the project, indicate that this will take several months given the current altitude of the ISS. Once the target altitude of 325 km has been reached, the Sprites will be deployed. The Sprite deployer contains 100 Sprites stacked 2-by-2 in four columns. Each Sprite is housed in an individual slot and constrained by a carbon fiber rod that runs the length of each column and passes through a hole in the corner of the Sprites. The nitinol wire antennas on the Sprites are coiled in such a way that they act as springs, pushing the Sprites out of their slots. When the carbon fiber rod is removed, the Sprites’ antennas will push them from the deployer housing with an estimated ΔV of 5-10 cm/sec. The Sprites are expected to have an orbital lifetime of approximately 5 days before reentry under typical atmospheric conditions. Bounding test cases with extremely high and extremely low atmospheric density give a range of orbital lifetimes between approximately 2 and 14 days (Figure 4). DAS simulations reflect this sprite orbital lifetime. 8

Figure 4: KickSat-2 Provided Sprite Orbital Lifetime The short orbital lifetime of the Sprites satisfies the Requirements 4.3-1. Total object- time of the 100 sprites (worst-case 6 day orbit lifetime) and KickSat-2 deployed structure (0.7 years) is summed to be 2.34 years, which satisfies the Requirement 4.3-2. The release of the Sprite’s from KickSat-2 has been pre-coordinated with the NASA Orbital Debris Planning Office. J.C. Liou replied to a question by Scott Higginbotham (ELaNa Mission Manager) on August 3, 2015: “For KickSat-2, releasing 100 Sprites from 325 km altitude has no long-term negative impact to the environment. The ODPO is fine with the plan.” (ref (g)) . 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 KickSat-2 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 0.8 years maximum the KickSat-2 is compliant. 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. ∑ π‘ͺπ‘ͺ𝑺𝑺𝑺𝑺𝑺𝑺𝑴𝑴𝑺𝑺𝑴𝑴 π‘ͺπ‘ͺ𝑺𝑺𝑴𝑴𝑴𝑴 [𝟐𝟐 ∗ (π’˜π’˜ ∗ 𝒍𝒍) + πŸ’πŸ’ ∗ (π’˜π’˜ ∗ 𝒉𝒉)] 𝑴𝑴𝑴𝑴𝑴𝑴𝑴𝑴 π‘ͺπ‘ͺπ‘ͺπ‘ͺπ‘ͺπ‘ͺ = = πŸ’πŸ’ πŸ’πŸ’ Equation 1: Mean Cross Sectional Area for Convex Objects (π‘ͺπ‘ͺπ’Žπ’Žπ‘΄π‘΄π’Žπ’Ž + π‘ͺπ‘ͺ𝟏𝟏 + π‘ͺπ‘ͺ𝟏𝟏 ) 𝑴𝑴𝑴𝑴𝑴𝑴𝑴𝑴 π‘ͺπ‘ͺπ‘ͺπ‘ͺπ‘ͺπ‘ͺ = 𝟐𝟐 Equation 2: Mean Cross Sectional Area for Complex Objects KickSat-2 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 KickSat-2 orbit at deployment is 400 km perigee altitude by 4106 km apogee altitude, with an inclination of 51.6 degrees. With an area to mass (2.256 kg) ratio of 0.0.0166 m2/kg, DAS yields 0.8 years for orbit lifetime for its stowed state, which in turn is used to obtain the collision probability. KickSat-2 sees less than 0x10^-5 probability of collision. Table 4 below provides complete results, a Sprite has been included for comparison. 11

Table 3: CubeSat Orbital Lifetime & Collision Probability KickSat-2 Sprite* Mass (kg) 2.2562 0.0051 Mean C/S Area (m^2) 0.0375 n/a Stowed Area-to Mass (m^2/kg) 0.0166 n/a Orbital Lifetime (yrs) 0.8 n/a Probability of collision (1:X) 0.00000 n/a Mean C/S Area (m^2) 0.0409 0.00067375 Deployed Area-to Mass (m^2/kg) 0.0181 0.132107843 Orbital Lifetime (yrs) 0.7 ~2-4 days Probability of collision (1:X) 0.00000 0.00000 * Sprite is being deployed from KickSat-2 at 325km circular orbit 12

Figure 5: Orbit Collision vs. Altitude (KickSat-2 Failure to Deploy) 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 KickSat-2 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 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 KickSat-2 to be compliant. Requirement 4.5-2 is not applicable to this mission. 13

Section 6: Assessment of Spacecraft Postmission Disposal Plans and Procedures The KickSat-2 spacecraft will naturally decay from orbit within 0.8 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 KickSat-2, in its stowed configuration as the worst case. The area-to- mass is calculated for is as follows: 𝑴𝑴𝑴𝑴𝑴𝑴𝑴𝑴 π‘ͺπ‘ͺοΏ½π‘ͺπ‘ͺ π‘ͺπ‘ͺ𝑺𝑺𝑴𝑴𝑴𝑴 (π’Žπ’ŽπŸπŸ ) π’Žπ’ŽπŸπŸ = π‘ͺπ‘ͺ𝑺𝑺𝑴𝑴𝑴𝑴 − 𝒕𝒕𝒕𝒕 − 𝑴𝑴𝑴𝑴𝑴𝑴𝑴𝑴 ( ) 𝑴𝑴𝑴𝑴𝑴𝑴𝑴𝑴 (π’Œπ’Œπ’Œπ’Œ) π’Œπ’Œπ’Œπ’Œ Equation 3: Area to Mass 0.0375 π‘šπ‘š2 π‘šπ‘š2 = 0.0166 2.26 π‘˜π‘˜π‘˜π‘˜ π‘˜π‘˜π‘˜π‘˜ KickSat-2 results in the worst case orbital lifetime of 0.8 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 410 km maximum apogee altitudes with an inclination of 51.6 degrees at deployment from the ISS after March of 2016. The area to mass ratio of 0.0166 m2/kg was imputed for the KickSat-2. DAS 2.0.2 yields a 0.8 years of orbit lifetime of KickSat-2 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. 14

Section 7: Assessment of Spacecraft Reentry Hazards A detailed assessment of the components to be flown on KickSat-2 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: KickSat-2 High Temperature DAS Analysis Length / KickSat-2 High Width Height Demise Alt CubeSat Mass (g) Diameter KE (J) Probability Temp Components (mm) (mm) (km) (mm) KickSat-2 Threaded Rods 14 3 3 320 76 0 0 KickSat-2 Sprite Deployer Spring 22.9 63 63 199 0 0.51 0 KickSat-2 Antenna 2.1 12.7 170 0.15 0 0.84 0 KickSat-2 Fasteners 3 - - - 74.8 0 0 The majority of high temperature components demise upon reentry. The components that survive re-entry show < 1J 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: KickSat-2 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. 15

Section 8: Assessment for Tether Missions KickSat-2 will not be deploying any tethers. KickSat-2 satisfy, Section 8’s requirement 4.8-1. 16

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 17

Appendix Index: Appendix A. KickSat-2 Component List 18

Appendix A. KickSat-2 Component List External/Internal Body Diameter/ Length Height Low Melting Temp Name (Major/Minor QTY Material Mass (g) Comment Type Width (mm) (mm) (mm) Temperature (°C) Components) CubeSat Name KickSat - - - - - - - - - Demise on reentry Aluminum CubeSat Structure External - Major 1 Box 477.3 100 100 340.5 yes - Demise on reentry 5052-H32 Demise on reentry, see Threded Rods Internal - Major 4 Steel Cylinder 14 3 3 320 no 1500 Table 4 Sprite Deployer Housing Internal - Major 1 ABS Plastic Box 206.5 96 96 201 yes - Demise on reentry Sprite Deployer Pusher Internal - Major 1 ABS Plastic Box 59 102 102 15 yes - Demise on reentry Survives reentry with Sprite Deployer Spring Internal - Major 1 Steel Cylinder 22.9 63 63 199 no 1500 0J, see Table 4 Flat Sprite ChipSat Internal - Major 100 FR4 PCB 5.1 35 35 1.75 yes - Demise on reentry Plate Flat Survives reentry with Antenna External - Major 2 Steel 2.1 12.7 170 0.15 no 1500 Plate 0J, see Table 4 GPS Antenna External - Minor 2 Aluminum Box 18.2 27 27 9.3 yes - Demise on reentry RF Divider Internal - Minor 1 Aluminum Box 114 50.5 50.5 19.1 yes - Demise on reentry Gallium Flat Solar Cells External - Major 100 0.26 31.8 12.9 0.15 yes - Demise on reentry Arsenide Plate Magnetorquer/Solar Panel Flat External - Major 6 FR4 PCB 33.9 104.8 82.6 2.5 yes - Demise on reentry Boards Plate Batteries Internal - Major 8 Lithium Ion Cylinder 46.3 19.1 19.1 61.9 yes - Demise on reentry Flat Flight Computer/Radio Board Internal - Major 1 FR4 PCB 46.6 80 80 2.5 yes - Demise on reentry Plate GPS Board Internal - Major 1 FR4 PCB Box 31.6 52.9 52.9 12.8 yes - Demise on reentry 6061 Flat Battery Mount Internal - Major 1 37.9 88.5 93.25 0.65 yes - Demise on reentry Aluminum Plate Stainless Demise on reentry, see Fasteners Internal - Minor 18 Cylinder 3 no 1450 Steel Table 4 Copper Cabling Internal - Minor - 18.7 - - - yes - Demise on reentry Alloy Loctite 222 Threadlocker Internal - Minor 1 Acrylic - - - - - yes - Demise on reentry 19


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