ODAR

0042-EX-CN-2016 Text Documents

California Polytechnic State University

2016-09-08ELS_181758

Rev 1 8/23/2016 Orbital Debris Assessment for the IRVINE01 CubeSat per NASA-STD 8719.14A 1

IRVINE01 Orbital Debris Assessment Report (ODAR) 2

IRVINE01 Orbital Debris Assessment Report (ODAR) 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. 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 D. UL Standard for Safety for Lithium Batteries, UL 1642. UL Standard. 4th ed. Northbrook, IL, Underwriters Laboratories, 2007 E. Kwas, Robert. Thermal Analysis of ELaNa-4 CubeSat Batteries, ELVL-2012-0043254; Nov 2012 F. Range Safety User Requirements Manual Volume 3- Launch Vehicles, Payloads, and Ground Support Systems Requirements, AFSCM 91-710 V3. G. UL Standard for Safety for Household and Commercial Batteries, UL 2054. UL Standard. 2nd ed. Northbrook, IL, Underwriters Laboratories, 2005 H. HQ OSMA Policy Memo/Email to 8719.14: CubeSat Battery Non-Passivation, Suzanne Aleman to Justin Treptow, 10, March 2014 3

IRVINE01 Orbital Debris Assessment Report (ODAR) 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 Compliant 4.6-1(a) Compliant Worst case lifetime 4.5 years 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 IRVINE01 mission 4

IRVINE01 Orbital Debris Assessment Report (ODAR) ODAR Table of Contents Section 1 (Program Management and Mission Overview)............................................................6 Section 2 (Spacecraft Description).................................................................................................8 Section 3 (Assessment of Spacecraft Debris Released during Normal Operations)…………......9 Section 4 (Assessment of Spacecraft Intentional Breakups and Potential for Explosions)...........10 Section 5 (Assessment of Spacecraft Potential for On-Orbit Collisions): ………………………11 Section 6 (Assessment of Spacecraft Post-mission Disposal Plans and Procedures)....................12 Section 7 (Assessment of Spacecraft Reentry Hazards)................................................................14 Section 8 (Assessment for Tether Missions).................................................................................20 5

IRVINE01 Orbital Debris Assessment Report (ODAR) ODAR Section 1: Program Management and Mission Overview Project Manager: Tinh Tran Foreign Government or Space Agency Participation: The Ecuadorian Space Agency (EXA) will provide many of the necessary parts for the CubeSat including the batteries and the solar panels. Russia will control the launch vehicle, a Depnr vehicle, that will be launched from Yasny, Russia. Schedule of Upcoming Mission Milestones: Mission kickoff date: March 1, 2016 Design review date: April 29, 2016 Delivery date: November 11, 2016 Tentative Launch Date: March 1, 2017 Mission Overview: IRVINE01 will be dispensed from an ISIPOD 3U CubeSat dispenser into an estimated orbit of 714 km Apogee and 598 km Perigee with an inclination of 97.74 degrees. The mission is expected to remain in orbit for 1659 days or approximately 4.5 years without use of our thrusters to adjust our orbit. During this time, our payload will take pictures of celestial objects, not including the Earth, as well as collect other data using our sun sensors, GPS, and other necessary equipment. ODAR Summary: No debris released in normal operations; no credible scenario for breakups; the collision probability with other objects is compliant with NASA standards; and the estimated nominal decay lifetime due to atmospheric drag is under 25 years following operations. Launch Vehicle and Launch Site: Dnepr, Yasny, Russia Proposed Launch Date: March 1, 2017 Mission Duration: Normal mission operations will take place until contact is lost, or some other mission detrimental factor causes a failure of essential systems. The natural decay time of the CubeSat is 1659 days 6

IRVINE01 Orbital Debris Assessment Report (ODAR) assuming we do not use our thrusters. Upon use of our thrusters, we will make the proper adjustments to our orbit listing. Launch and deployment profile, including all parking, transfer, and operational orbits with apogee, perigee, and inclination: The Dnepr launch vehicle will be dispensing various payloads into a nearly circular 600 km sun- synchronous orbit. IRVINE01 will decay from an orbit defined as follows assuming no orbit adjustments with our thrusters: Apogee: 714 km Perigee: 598 km Orbital Inclination: 97.74 degrees IRVINE01 does include thrusters and ergo has the ability to actively change its orbit. Any orbital changes will be coordinated with the JSpOC. 7

IRVINE01 Orbital Debris Assessment Report (ODAR) ODAR Section 2: Spacecraft Description Physical description of the spacecraft: IRVINE01 conforms to the 1U CubeSat specification, with a launch mass of 1.2 kg. Basic physical dimensions are 100mm x 100mm x 106mm, with two solar panels with 170mm x 85mm x 2mm extended dimensions. The IRVINE01 solar panel structure is comprised of two 100mm x 100mm plates that are extended. The solar arrays are spring-loaded and burn-wire deployed. Power storage is provided by Lithium-Ion cells. The batteries will be recharged by solar cells mounted on the body of the satellite and on the two deployable solar panels. IRVINE01 attitude is approximately determined using the magnetic field vector, measured by onboard magnetometers. The IRVINE01’s attitude will be controlled by a 3-axis magnetorquer controller. Total satellite mass at launch, including all propellants and fluids: ~1.2 kg. Dry mass of satellites at launch, excluding solid rocket motor propellants: ~1.2 kg Description of all propulsion systems (cold gas, monopropellant, bipropellant, electric, nuclear): Electric Identification, including mass and pressure, of all fluids (liquids and gases) planned to be on board and a description of the fluid loading plan or strategies, excluding fluids in sealed heat pipes: Unpressurized ionic liquid Fluids in Pressurized Batteries: None 8

IRVINE01 Orbital Debris Assessment Report (ODAR) ODAR Section 3: Assessment of Spacecraft Debris Released during Normal Operations Identification of any object (>1 mm) expected to be released from the spacecraft any time after launch, including object dimensions, mass, and material: There are no intentional releases. Rationale/necessity for release of each object: N/A. Time of release of each object, relative to launch time: N/A. Release velocity of each object with respect to spacecraft: N/A. Expected orbital parameters (apogee, perigee, and inclination) of each object after release: N/A. Calculated orbital lifetime of each object, including time spent in Low Earth Orbit (LEO): N/A. Assessment of spacecraft compliance with Requirements 4.3-1 and 4.3-2 (per DAS v2.0.1) 4.3-1, Mission Related Debris Passing Through LEO: NOT APPLICCABLE 4.3-2, Mission Related Debris Passing Near GEO: NOT APPLICCABLE 9

IRVINE01 Orbital Debris Assessment Report (ODAR) ODAR Section 4: Assessment of Spacecraft Intentional Breakups and Potential for Explosion There are NO plans for designed spacecraft breakups, explosions, or intentional collisions on the IRVINE01 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 maximum possible lifetime of 4.5 years the IRVINE01 CubeSat is compliant. 10

IRVINE01 Orbital Debris Assessment Report (ODAR) ODAR Section 5: Assessment of Spacecraft Potential for On-Orbit Collisions Assessment of spacecraft compliance with Requirements 4.5-1 and 4.5-2 (per DAS v2.0.1, and calculation methods provided in NASA-STD-8719.14, section 4.5.4): Requirement 4.5-1: Limiting debris generated by collisions with large objects when operating in Earth orbit: For each spacecraft and launch vehicle orbital stage in or passing through LEO, the program or project shall demonstrate that, during the orbital lifetime of each spacecraft and orbital stage, the probability of accidental collision with space objects larger than 10 cm in diameter is less than 0.001 (Requirement 56506). Large Object Impact and Debris Generation Probability: (DAS 2.0.2) IRVINE01; Collision Probability: 0.00000; COMPLIANT. The above analysis results are a product of the DAS 2.0.2 software. We then assume hard spheres of diameter 1 m for IRVINE01 Requirement 4.5-2: Limiting debris generated by collisions with small objects when operating in Earth or lunar orbit: For each spacecraft, the program or project shall demonstrate that, during the mission of the spacecraft, the probability of accidental collision with orbital debris and meteoroids sufficient to prevent compliance with the applicable post-mission disposal requirements is less than 0.01 (Requirement 56507). Small Object Impact and Debris Generation Probability: IRVINE01; Collision Probability: 0.00000 COMPLIANT. Identification of all systems or components required to accomplish any post-mission disposal operation, including passivation and maneuvering: No post-mission disposal procedures are necessary, since the satellite’s orbit will naturally decay within 4.5 years. 11

IRVINE01 Orbital Debris Assessment Report (ODAR) ODAR Section 6: Assessment of Spacecraft Post-mission Disposal Plans and Procedure 6.1: Description of Spacecraft Disposal Option Selected: IRVINE01 will de-orbit naturally by atmospheric re-entry within 4.5 years. All components will burn up during re-entry. 6.2: Plan for Any Spacecraft Maneuvers Required to Accomplish Post-Mission Disposal: No maneuvers are required. 6.3: Calculation of Area-to-Mass Ratio After Post-Mission Disposal, if the Controlled Re- entry Option is Not Selected: Spacecraft Mass: 1.2 kg Cross-Sectional Area: 141cm2 6.4: Assessment of Spacecraft Compliance with Requirements 4.6-1 Through 4.6-5 (per DAS v. 2.0.1 and NASA-STD-8719.14 Section): Requirement 4.6-1: Disposal for Space Structures Passing Through LEO: A spacecraft or orbital stage with a perigee altitude below 2000 km shall be disposed of by one of three methods (Requirement 56557): a. Atmospheric Re-Entry Option: ○ Leave the space structure in an orbit in which natural forces will lead to atmospheric reentry within 25 years after the completion of mission by no more than 30 years after launch. ○ Maneuver the space structure into a controlled de-orbit trajectory as soon as practical after completion of mission.\ b. Storage Orbit Option: ○ Maneuver the space structure into an orbit with perigee altitude greater than 2000 km and apogee less than GEO - 500 km. c. Direct Retrieval: ○ Retrieve the space structure and remove it from orbit within 10 years after completion of mission. Analysis: The IRVINE01 satellite re-entry is COMPLIANT using method “I”. 12

IRVINE01 Orbital Debris Assessment Report (ODAR) Requirement 4.6-2: Disposal for Space Structures Near GEO: Analysis: Not Applicable. Requirement 4.6-3: Disposal for Space Structures Between LEO and GEO: Analysis: Not Applicable. Requirement 4.6-4: Reliability of Post-Mission Disposal Operations: Analysis: The maximum drag configuration is the aerodynamically stable state, meaning that even under massive subsystem failure we would eventually assume this orientation. 13

IRVINE01 Orbital Debris Assessment Report (ODAR) ODAR Section 7: Assessment of Spacecraft Reentry Hazards Assessment of spacecraft compliance with Requirement 4.7-1: Requirement 4.7-1: Limit the risk of human casualty: The potential for human casualty is assumed for any object with an impacting kinetic energy in excess of 15 joules: a) For uncontrolled reentry, the risk of human casualty from surviving debris shall not exceed 0.0001 (1:10,000) (Requirement 56626). Summary Analysis Results: DAS v2.0.1 reports that IRVINE01 is compliant with the requirement. There will be no risk of human casualty during reentry because it will completely burn up in the atmosphere. =============== End of Requirement 4.3-1 =============== 06 19 2012; 16:57:52PM Processing Requirement 4.3-2: Return Status : Passed =============== End of Requirement 4.3-2 =============== 06 19 2012; 16:57:57PM Requirement 4.4-3: Compliant =============== End of Requirement 4.4-3 =============== 06 19 2012; 16:58:03PM Processing Requirement 4.5-1: Return Status : Passed ============== Run Data ============== **INPUT** Space Structure Name = IRVINE01 Space Structure Type = Payload Perigee Altitude = 400.000000 (km) Apogee Altitude = 650.000000 (km) Inclination = 97.790000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass Ratio = 0.036538 (m^2/kg) Start Year = 2017.4166667 (yr) 14

IRVINE01 Orbital Debris Assessment Report (ODAR) Initial Mass = 1.2 (kg) Final Mass = 0.9 (kg) Duration = 3.000000 (yr) Station-Kept = True Abandoned = False PMD Perigee Altitude = N/A PMD Apogee Altitude = N/A PMD Inclination = N/A PMD RAAN = 0.000000 (deg) PMD Argument of Perigee = N/A PMD Mean Anomaly = N/A **OUTPUT** Collision Probability = 0.000011 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range Status = Pass ============== =============== End of Requirement 4.5-1 =============== 06 19 2012; 16:58:10PM Requirement 4.5-2: Compliant 06 19 2012; 16:58:23PM Processing Requirement 4.6 Return Status : Passed ============== Project Data ============== **INPUT** Space Structure Name = IRVINE01 Space Structure Type = Payload Perigee Altitude = 400.000000 (km) Apogee Altitude = 650.000000 (km) Inclination = 97.790000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass Ratio = 0.036538 (m^2/kg) Start Year = 2017.4166667 (yr) 15

IRVINE01 Orbital Debris Assessment Report (ODAR) Initial Mass = 1 (kg) Final Mass = 0.9 (kg) Duration = 3.000000 (yr) Station-Kept = True Abandoned = False PMD Perigee Altitude = N/A PMD Apogee Altitude = N/A PMD Inclination = N/A PMD RAAN = 0.000000 (deg) PMD Argument of Perigee = N/A PMD Mean Anomaly = N/A **OUTPUT** Suggested Perigee Altitude = 595.700000 (km) Suggested Apogee Altitude = 799.000000 (km) Returned Error Message = Passes LEO reentry orbit criteria. Released Year = 2029 (yr) Requirement = 61 Compliance Status = Pass ============== =============== End of Requirement 4.6 =============== 06 19 2012; 16:59:04PM *********Processing Requirement 4.7-1 Return Status : Passed ***********INPUT**** Item Number = 1 name = IRVINE01 quantity = 1 parent = 0 type = Box Aero Mass = 1.200000 Thermal Mass = 1.200000 Diameter/Width = 0.100000 Length = 0.106000 Height = 0.100000 16

IRVINE01 Orbital Debris Assessment Report (ODAR) name = Camera quantity = 1 parent = 1 materialID = 5 type = Box Aero Mass = 0.370000 Thermal Mass = 0.370000 Diameter/Width = 0.060000 Length = 0.080000 Height = 0.060000 quantity = 8 parent = 1 materialID = 46 type = Cylinder Aero Mass = 0.026000 Thermal Mass = 0.026000 Diameter/Width = 0.014000 Length = 0.065000 name = Structure quantity = 1 parent = 1 materialID = 5 type = Box Aero Mass = 1.280000 Thermal Mass = 1.280000 Diameter/Width = 0.100000 Length = 0.340000 Height = 0.100000 name = Solar Arrays quantity = 8 parent = 1 materialID = 24 type = Flat Plate Aero Mass = 0.050000 Thermal Mass = 0.050000 Diameter/Width = 0.080000 Length = 0.300000 17

IRVINE01 Orbital Debris Assessment Report (ODAR) name = Avionics quantity = 1 parent = 1 materialID = 23 type = Box Aero Mass = 0.200000 Thermal Mass = 0.200000 Diameter/Width = 0.100000 Length = 0.100000 Height = 0.100000 name = Optical Tube quantity = 1 parent = 1 materialID = 72 type = Cylinder Aero Mass = 2.080000 Thermal Mass = 2.080000 Diameter/Width = 0.091000 Length = 0.200000 name = +/- X Structure Walls quantity = 2 parent = 1 materialID = 5 type = Flat Plate Aero Mass = 0.200000 Thermal Mass = 0.200000 Diameter/Width = 0.100000 Length = 0.300000 **************OUTPUT**** Item Number = 1 name = IRVINE0-1 Demise Altitude = 77.999691 Debris Casualty Area= 0.000000 Impact Kinetic Energy = 0.000000 18

IRVINE01 Orbital Debris Assessment Report (ODAR) ************************************* name = Camera Demise Altitude = 72.690324 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Batteries Demise Altitude = 74.279746 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Structure Demise Altitude = 73.855996 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 *********************** ************** name = Solar Arrays Demise Altitude = 77.857871 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.0000 ************************************* name = Avionics Demise Altitude = 76.855277 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Optical Tube Demise Altitude = 0.000000 Debris Casualty Area = 0.540089 Impact Kinetic Energy = 2419.714355 ************************************* name =+/-X Structure Walls 19

IRVINE01 Orbital Debris Assessment Report (ODAR) Demise Altitude = 76.366027 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* =============== End of Requirement 4.7-1 =============== Requirements 4.7-1b, and 4.7-1c below are non-applicable requirements because IRVINE01 does not use controlled reentry. 4.7-1, b) NOT APPLICABLE. For controlled re-entry, the selected trajectory shall ensure that no surviving debris impact with a kinetic energy greater than 15 joules is closer than 370 km from foreign land masses, or is within 50 km from the continental U.S., territories of the U.S., and the permanent ice pack of Antarctica (Requirement 56627). 4.7-1, c) NOT APPLICABLE. For controlled re-entries, the product of the probability of failure of the re-entry burn (from Requirement 4.6-4.b) and the risk of human casualty assuming uncontrolled re-entry shall not exceed 0.0001 (1:10,000) (Requirement 56628)) ODAR Section 8: Assessment for Tether Missions Not applicable. There are no tethers in the IRVINE01 mission. 20


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