ODAR rev2

0042-EX-CN-2016 Text Documents

California Polytechnic State University

2016-11-01ELS_183999

Rev  2   10/28/2016                   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 6 months   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).....................10     Section 4 (Assessment of Spacecraft Intentional Breakups and Potential for Explosions)...........11     Section 5 (Assessment of Spacecraft Potential for On-Orbit Collisions): ....................................12     Section 6 (Assessment of Spacecraft Post-mission Disposal Plans and Procedures)....................13     Section 7 (Assessment of Spacecraft Reentry Hazards)................................................................15     Section 8 (Assessment for Tether Missions).................................................................................19                                           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. India will control the launch vehicle, which will be launched from Sriharikota, India.   Schedule of Upcoming Mission Milestones:   Mission kickoff date: March 1, 2016   Design review date: April 29, 2016   Delivery date: April 1, 2016   Tentative Launch Date: June 1, 2017   Mission Overview:   IRVINE01 will be dispensed from a PPOD 3U CubeSat dispenser into an estimated orbit of 500 km Apogee and 600 km Perigee with an inclination of 97 degrees. The mission is expected to remain in orbit for approximately 6 months. During this time, our payload will take pictures of celestial objects, such as the Moon and Venus, 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.   6  

  IRVINE01   Orbital  Debris  Assessment  Report  (ODAR)     Launch Vehicle and Launch Site:   PSLV, Sriharikota, India   Proposed Launch Date:   June 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 6 months.   Launch and deployment profile, including all parking, transfer, and operational orbits with apogee, perigee, and inclination:   The launch vehicle will be dispensing various payloads into a nearly circular 500 km sun- synchronous orbit.   IRVINE01 will decay from an orbit defined as follows:   Perigee: 500 km   Apogee: 600 km   Orbital Inclination: 97 degrees                             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 8  

  IRVINE01   Orbital  Debris  Assessment  Report  (ODAR)     Description of all propulsion systems (cold gas, monopropellant, bipropellant, electric, nuclear): None, but there is a zero-propellant mass-model of an electric thruster attached to balance the mass distribution of the spacecraft for the magnetorquers.   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: None   Fluids in Pressurized Batteries: None     9  

  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 APPLICABLE   4.3-2, Mission Related Debris Passing Near GEO: NOT APPLICABLE       10  

  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 satellite and its short orbital lifetime, 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 6 months the IRVINE01 CubeSat is compliant.       11  

  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 6 months.           12  

  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 6 months. 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: 141 cm2     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”.   13  

  IRVINE01   Orbital  Debris  Assessment  Report  (ODAR)       Output  from  GMAT  simulation:  Orbital  Radius  (km  to  Earth  center)  vs.  Elapsed  Days     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.         14  

  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.     10 26 2016; 18:11:48PM Processing Requirement 4.3-2: Return Status : Passed     =====================   No Project Data Available   =====================     =============== End of Requirement 4.3-2 ===============   10 26 2016; 18:11:49PM Requirement 4.4-3: Compliant     =============== End of Requirement 4.4-3 ===============   10 26 2016; 18:11:52PM Processing Requirement 4.5-1: Return Status : Passed     ==============   Run Data   ==============     **INPUT**     Space Structure Name = IRVINE01   Space Structure Type = Payload   Perigee Altitude = 500.000000 (km)   Apogee Altitude = 600.000000 (km)   Inclination = 97.000000 (deg)   RAAN = 0.000000 (deg)   15  

  IRVINE01   Orbital  Debris  Assessment  Report  (ODAR)     Argument of Perigee = 0.000000 (deg)   Mean Anomaly = 0.000000 (deg)   Final Area-To-Mass Ratio = 1.000000 (m^2/kg)   Start Year = 2017.000000 (yr)   Initial Mass = 1.000000 (kg)   Final Mass = 0.900000 (kg)   Duration = 3.000000 (yr)   Station-Kept = True   Abandoned = True   PMD Perigee Altitude = -1.000000 (km)   PMD Apogee Altitude = -1.000000 (km)   PMD Inclination = 0.000000 (deg)   PMD RAAN = 0.000000 (deg)   PMD Argument of Perigee = 0.000000 (deg)   PMD Mean Anomaly = 0.000000 (deg)     **OUTPUT**     Collision Probability = 0.000008   Returned Error Message: Normal Processing   Date Range Error Message: Normal Date Range   Status = Pass     ==============     =============== End of Requirement 4.5-1 ===============   10 26 2016; 18:11:54PM Requirement 4.5-2: Compliant   10 26 2016; 18:11:55PM Processing Requirement 4.6 Return Status : Passed     ==============   Project Data   ==============     **INPUT**     Space Structure Name = IRVINE01   Space Structure Type = Payload     Perigee Altitude = 500.000000 (km)   Apogee Altitude = 600.000000 (km)   Inclination = 97.000000 (deg)   RAAN = 0.000000 (deg)   Argument of Perigee = 0.000000 (deg)   Mean Anomaly = 0.000000 (deg)   Area-To-Mass Ratio = 1.000000 (m^2/kg)   Start Year = 2017.000000 (yr)   16  

  IRVINE01   Orbital  Debris  Assessment  Report  (ODAR)     Initial Mass = 1.000000 (kg)   Final Mass = 0.900000 (kg)   Duration = 3.000000 (yr)   Station Kept = True   Abandoned = True   PMD Perigee Altitude = 500.000000 (km)   PMD Apogee Altitude = 600.000000 (km)   PMD Inclination = 97.000000 (deg)   PMD RAAN = 0.000000 (deg)   PMD Argument of Perigee = 0.000000 (deg)   PMD Mean Anomaly = 0.000000 (deg)     **OUTPUT**     Suggested Perigee Altitude = 500.000000 (km)   Suggested Apogee Altitude = 600.000000 (km)   Returned Error Message = Passes LEO reentry orbit criteria.     Released Year = 2020 (yr)   Requirement = 61   Compliance Status = Pass     ==============     =============== End of Requirement 4.6 ===============   10 26 2016; 18:12:00PM *********Processing Requirement 4.7-1   Return Status : Passed     ***********INPUT****   Item Number = 1     name = IRVINE01   quantity = 1   parent = 0   materialID = 5   type = Box   Aero Mass = 0.900000   Thermal Mass = 0.900000   Diameter/Width = 0.100000   Length = 0.100000   Height = 0.100000     name = IRVINE01   quantity = 1   parent = 1   materialID = 5   type = Box   17  

  IRVINE01   Orbital  Debris  Assessment  Report  (ODAR)     Aero Mass = 0.900000   Thermal Mass = 0.900000   Diameter/Width = 0.100000   Length = 0.100000   Height = 0.100000     **************OUTPUT****   Item Number = 1     name = IRVINE01   Demise Altitude = 77.997590   Debris Casualty Area = 0.000000   Impact Kinetic Energy = 0.000000     *************************************   name = IRVINE01   Demise Altitude = 67.662378   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))             18  

  IRVINE01   Orbital  Debris  Assessment  Report  (ODAR)     ODAR  Section  8:  Assessment  for  Tether  Missions   Not applicable. There are no tethers in the IRVINE01 mission.     19  


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