Booz Allen Hamilton ODAR

0531-EX-ST-2014 Text Documents

Booz Allen Hamilton Inc.

2014-06-27ELS_150760

Centennial-1 Orbital Debris Assessment Report (ODAR) Centennial-1 Orbital Debris Assessment Report (ODAR) This report is presented in compliance with NASA-STD-8719.14, Appendix A Report Version: 1, 6/1/2014 Document Data is Not Restricted This document contains no proprietary, ITAR, or export controlled information. DAS Software Version Used in Analysis: v2.0.2 Page 1 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) VERSION APPROVAL and/or FINAL APPROVAL*: Brian Abbe OIC, Centennial-1 Program Booz Allen Hamilton Inc. 8283 Greensboro Drive Phone: 703.902.5000 Email:abbe_brian@bah.com Brian S Abbe June 13, 2014 _______________________________________________ Senior Vice President Signature of Official Date Signed *Approval signatures indicate acceptance of the ODAR-defined risk. Page 2 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) Table of Contents Self-assessment of the ODAR using the format in Appendix A.2 of NASA-STD-8719.14: ......... 3 Assessment Report Format: ............................................................................................................ 5 ODAR Section 1: Program Management and Mission Overview .................................................. 5 ODAR Section 2: Spacecraft Description....................................................................................... 6 ODAR Section 3: Assessment of Spacecraft Debris Released during Normal Operations ............ 7 ODAR Section 4: Assessment of Spacecraft Intentional Breakups and Potential for Explosions . 7 ODAR Section 5: Assessment of Spacecraft Potential for On-Orbit Collisions .......................... 11 ODAR Section 6: Assessment of Spacecraft Post-Mission Disposal Plans and Procedures ........ 13 ODAR Section 7: Assessment of Spacecraft Reentry Hazards .................................................... 15 ODAR Section 8: Assessment for Tether Missions ...................................................................... 19 Self-assessment of the ODAR using the format in Appendix A.2 of NASA-STD-8719.14: A self-assessment is provided below in accordance with the assessment format provided in Appendix A.2 of NASA-STD-8719.14. Page 3 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) Orbital Debris Self-Assessment Report Evaluation: Centennial-1 Mission Launch Vehicle Spacecraft Requirement Standard Not Not Comments # Compliant Incomplete Non Compliant Incomplete Compliant Compliant Compliant 4.3-1.a No Debris Released in LEO. See note 1. 4.3-1b No Debris Released in LEO. See note 1. 4.3-2 No Debris Released in GEO. See note 1. 4.4-1 See note 1. 4.4-2 See note 1. 4.4-3 No planned breakups. See note 1. 4.4-4 No planned breakups. See note 1. 4.5-1 See note 1. No critical subsystems needed for EOM 4.5-2 disposal 4.6-1(a) See note 1. 4.6-1(b) See note 1. 4.6-1(c) See note 1. 4.6-2 See note 1. 4.6-3 See note 1. 4.6-4 See note 1. 4.6-5 See note 1. 4.7-1 See note 1. 4.8-1 No tethers used. Notes: 1. This launch has several spacecraft manifested and the Booz Allen Hamilton spacecraft is not the primary mission. Page 4 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) Assessment Report Format: ODAR Technical Sections Format Requirements: As Booz Allen Hamilton is a US company, this ODAR follows the format recommended in NASA-STD-8719.14, Appendix A.1 and includes the content indicated at a minimum in each section 2 through 8 below for the Centennial-1 satellite. Section 9 through 14 apply to the launch vehicle ODAR and are not covered here. ODAR Section 1: Program Management and Mission Overview Project Manager: William Hojnowski Foreign government or space agency participation: None. Schedule of upcoming mission milestones: FRR: August 2014 Launch: October 2014 Mission Overview: Centennial-1 will be ejected from the International Space Station into a circular orbit 420km at 51.65 degrees. The experiment will operate for a maximum duration of 6 months. 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 (8.4 months after 6 months of nominal operations, as calculated by DAS 2.0.2). Launch vehicle and launch site: Antares, Wallops Island, VA Proposed Launch Date: October 3, 2014 Mission duration: Maximum Nominal Operations: 6 months, Post-Operational Orbit Lifetime: 8.4 months until reentry via atmospheric orbital decay (14.4 months total). Launch and deployment profile, including all parking, transfer and operational orbits with apogee, perigee and inclination: The Antares rocket, being able to restart to perform orbital change maneuvers, will be delivering supplies to the International Space Station. Centennial-1 will be deployed from the International Space Station. The Centennial-1 satellite will deploy to, and decay naturally from, a circular orbit defined as follows: Apogee: 420 km Perigee: 420 km Page 5 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) Inclination: 51.65 degrees Centennial-1 has no propulsion and therefore does not actively change orbits. There is no parking or transfer orbit. ODAR Section 2: Spacecraft Description Physical description of the spacecraft: Centennial-1 conforms to the 1U CubeSat specification, with a launch mass of 1.3kg. Basic physical dimentions are 100mm x 100 mm x 100 mm with a deployable antenna. The Centennial-1 load bearing structure is comprised of three 100mm x 100mm skeleton plates, with L rails along each 100mm corner edge. The solar arrays are body mounted. Power storage is provided by Lithium-Polymer cells. The batteries will be recharged by solar cells mounted on the body of the satellite. Centenial-1 attitude will be controlled by a Z-axis Figure 1: Centennial-1 Configuration permanent magnet and determined by 3-axis gyroscope. Total satellite mass at launch, including all propellants and fluids: ~1.3 kg. Dry mass of satellite at launch, excluding solid rocket motor propellants: ~1.3kg Description of all propulsion systems (cold gas, mono-propellant, bi-propellant, electric, nuclear): None. Identification, including mass and pressure, of all fluids (liquid and gasses) 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. Centennial-1 uses an unpressurized standard COTS Lithium-Polymer battery cell. Description of attitude control system and indication of the normal attitude of the spacecraft with respect to the velocity vector: Centennial-1 utilizes permanent magnet passive stabilization, which will orient the spacecraft into a predictable configuration for antennas and sensors. The nominal attitude will be the Z axis aligning to the magnetic poles with the +Z face pointing north and the X and Y axes free to rotate. There is no active attitude control on Centennial-1. Page 6 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) Description of any range safety or other pyrotechnic devices: No pyrotechnic devices are used. Description of the electrical generation and storage system: Standard COTS Lithium-Ion battery cells are charged before payload integration and provide electrical energy during the mission. The cells are recharged by solar cells mounted on the deployable arrays. The battery cell protection circuit manages the charging cycle. Identification of any other sources of stored energy not noted above: None. Identification of any radioactive materials on board: None. 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 v2.0.2) 4.3-1, Mission Related Debris Passing Through LEO: COMPLIANT 4.3-2, Mission Related Debris Passing Near GEO: COMPLIANT ODAR Section 4: Assessment of Spacecraft Intentional Breakups and Potential for Explosions Potential causes of spacecraft breakup during deployment and mission operations: There is no credible scenario that would result in spacecraft breakup during normal deployment and operations. Summary of failure modes and effects analyses of all credible failure modes which may lead to an accidental explosion: Page 7 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) In-mission failure of a battery cell protection circuit could lead to a short circuit resulting in overheating and a very remote possibility of battery cell explosion. The battery safety systems discussed in the FMEA (see requirement 4.4-1 below) describe the combined faults that must occur for any of seven (7) independent, mutually exclusive failure modes to lead to explosion. The deployment of the UHF/VHF antenna will feature a simple spring system, released by a simple burn-wire. The probability of a detachment during deployment is negligible. Detailed plan for any designed spacecraft breakup, including explosions and intentional collisions: There are no planned breakups. List of components which shall be passivated at End of Mission (EOM) including method of passivation and amount which cannot be passivated: None. The battery will not be passivated at End of Mission due to the low risk and low impact of explosive rupturing. The maximum total energy stored in the battery is 36kJ. Rationale for all items which are required to be passivated, but cannot be due to their design: Centennial-1 battery charge circuits include overcharge protection to limit the risk of battery failure. However, in the unlikely event that the battery cell does explosively rupture, the small size, mass, and potential energy, of this small battery is such that while the spacecraft could be expected to vent gases, most debris from the battery rupture should be contained within the vessel due to the lack of penetration energy. Assessment of spacecraft compliance with Requirements 4.4-1 through 4.4-4: Requirement 4.4-1: Limiting the risk to other space systems from accidental explosions during deployment and mission operations while in orbit about Earth or the Moon: For each spacecraft and launch vehicle orbital stage employed for a mission, the program or project shall demonstrate, via failure mode and effects analyses or equivalent analyses, that the integrated probability of explosion for all credible failure modes of each spacecraft and launch vehicle is less than 0.001 (excluding small particle impacts (Requirement 56449). Compliance statement: Required Probability: 0.001. Page 8 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) Expected probability: 0.000. Supporting Rationale and FMEA details: Battery explosion: Effect: All failure modes below might theoretically result in battery explosion with the possibility of orbital debris generation. However, in the unlikely event that a battery cell does explosively rupture, the small size, mass, and potential energy, of the selected COTS batteries is such that while the spacecraft could be expected to vent gases, most debris from the battery rupture should be contained within the vessel due to the lack of penetration energy. Probability: Extremely Low. It is believed to be a much less than 0.1% probability that multiple independent (not common mode) faults must occur for each failure mode to cause the ultimate effect (explosion). Failure Mode 1: Internal short circuit. Mitigation 1: Qualification and acceptance shock, vibration, thermal cycling, and vacuum tests followed by maximum system rate-limited charge and discharge to prove that no internal short circuit sensitivity exists. Combined faults required for realized failure: Environmental testing AND functional charge/discharge tests must both be ineffective in discovery of the failure mode. Failure Mode 2: Internal thermal rise due to high load discharge rate. Mitigation 2: Cells were tested in lab for high load discharge rates in a variety of flight-like configurations to determine like likelihood and impact of an out of control thermal rise in the cell. Cells were also tested in a hot environment to test the upper limit of the cells capability. No failures were seen. Combined faults required for realized failure: Spacecraft thermal design must be incorrect AND external over-current detection and disconnect function must fail to enable this failure mode. Failure Mode 3: Excessive discharge rate or short circuit due to external device failure or terminal contact with conductors not at battery voltage levels (due to abrasion or inadequate proximity separation). Mitigation 4: This failure mode is negated by a) qualification-tested short circuit protection on each external circuit, b) design of battery packs and insulators such that no contact with nearby board traces is possible without being caused by some Page 9 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) other mechanical failure, c) obviation of such other mechanical failures by protoqualification and acceptance environmental tests (shock, vibration, thermal cycling, and thermal-vacuum tests). Combined faults required for realized failure: An external load must fail/short circuit AND external over-current detection and disconnect function failure must all occur to enable this failure mode. Failure Mode 4: Inoperable vents. Mitigation 5: Battery vents are not inhibited by the battery holder design or the spacecraft. Combined effects required for realized failure: The final assembler fails to install proper venting. Failure Mode 5: Crushing. Mitigation 6: This mode is negated by spacecraft design. There are no moving parts in the proximity of the batteries. Combined faults required for realized failure: A catastrophic failure must occur in an external system AND the failure must cause a collision sufficient to crush the batteries leading to an internal short circuit AND the satellite must be in a naturally sustained orbit at the time the crushing occurs. Failure Mode 6: Low level current leakage or short-circuit through battery pack case or due to moisture-based degradation of insulators. Mitigation 7: These modes are negated by a) battery holder/case design made of non-conductive plastic, and b) operation in vacuum such that no moisture can affect insulators. Combined faults required for realized failure: Abrasion or piercing failure of circuit board coating or wire insulators AND dislocation of battery packs AND failure of battery terminal insulators AND failure to detect such failure modes in environmental tests must occur to result in this failure mode. Failure Mode 7: Excess temperatures due to orbital environment and high discharge combined. Mitigation 8: The spacecraft thermal design will negate this possibility. Thermal rise has been analyzed in combination with space environment temperatures showing that batteries do not exceed normal allowable operating temperatures which are well below temperatures of concern for explosions. Combined faults required for realized failure: Thermal analysis AND thermal design AND mission simulations in thermal-vacuum chamber testing AND overcurrent monitoring and control must all fail for this failure mode to occur. Page 10 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) Requirement 4.4-2: Design for passivation after completion of mission operations while in orbit about Earth or the Moon: Design of all spacecraft and launch vehicle orbital stages shall include the ability to deplete all onboard sources of stored energy and disconnect all energy generation sources when they are no longer required for mission operations or postmission disposal or control to a level which cannot cause an explosion or deflagration large enough to release orbital debris or break up the spacecraft (Requirement 56450). Compliance statement: Centennial-1 battery charge circuits include overcharge protection and a parallel design to limit the risk of battery failure. However, in the unlikely event that a battery cell does explosively rupture, the small size, mass, and potential energy, of these small batteries is such that while the spacecraft could be expected to vent gases, most debris from the battery rupture should be contained within the vessel due to the lack of penetration energy. Requirement 4.4-3: Limiting the long-term risk to other space systems from planned breakups: Compliance statement: This requirement is not applicable. There are no planned breakups. Requirement 4.4-4: Limiting the short-term risk to other space systems from planned breakups: Compliance statement: This requirement is not applicable. There are no planned breakups. 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 v2.0.2, 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: Centennial-1; Collision Probability: 0.000000; COMPLIANT. Page 11 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) Figure 2: Number of Impacts vs. Altitude. 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 postmission disposal requirements is less than 0.01 (Requirement 56507). Small Object Impact and Debris Generation Probability: Centennial-1; Collision Probability: 0.00000; COMPLIANT. Identification of all systems or components required to accomplish any postmission disposal operation, including passivation and maneuvering: Centennial-1 will decay within 1.2 years without any active systems. The spacecraft orbit prediction is based on the non-deployable or maneuverable cube geometry and mass properties of Centennial-1 using DAS 2.0.2. Page 12 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) ODAR Section 6: Assessment of Spacecraft Postmission Disposal Plans and Procedures 6.1 Description of spacecraft disposal option selected: Centennial-1 will de-orbit naturally by atmospheric re-entry within 1.2 years. At the end of Centennial-1's operational life (i.e. at EOM) the satellite orbit will decay naturally without control input. Centennial-1 is a dynamically stable configuration that requires no positioning for reentry. 6.2 Plan for any spacecraft maneuvers required to accomplish postmission disposal: The cube configuration of Centennial-1 does not require maneuvers to accomplish a stable reentry. Postmission disposal will occur as a result of normal atmospheric drag. 6.3 Calculation of area-to-mass ratio after post mission disposal, if the controlled reenter option is not selected: Spacecraft Mass: ~1.3kg Cross-sectional Area: 0.01 m2 (dynamically stable) Area to mass ratio: 0.0077 m2/kg (dynamically stable) 6.4 Assessment of spacecraft compliance with Requirements 4.6-1 through 4.6-5 (per DAS v 2.0.2 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 reentry 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, but no more than 30 years after launch; or • 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 Centennial-1 satellite reentry is COMPLIANT using method “a”. Page 13 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) Satellite Name: Centennial-1 BOL Orbit: 420x420 km EOL Orbit*: 370x388 km Total Lifetime: 1.2 years Post-Ops Life: 0.7 years *EOM orbit was calculated using DAS 2.0.2 output of orbit history over the 6 months mission duration. Figure 3: Altitude History of Centennial-1. 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. Page 14 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) Analysis: Not applicable. Requirement 4.6-4: Reliability of Post Mission Disposal Operations Analysis: The normal configuration is the aerodynamically stable state, meaning that even under massive subsystem failure we would eventually assume this orientation. 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 v2.0.2 reports that Centennial-1 is compliant with the requirement. Total human casualty probability is reported by the DAS software as less than 1:10,000 for Centennial-1. This is expected to represent the absolute maximum casualty risk, as calculated with DAS's limited modeling capability. Analysis (per DAS v2.0.2): 05 23 2014; 10:53:38AM DAS Application Started 05 23 2014; 10:53:40AM Opened Project C:\Program Files (x86)\NASA\DAS 2.0\Centennial-1\ 05 23 2014; 10:54:57AM Mission Editor Changes Applied 05 23 2014; 10:55:12AM Mission Editor Changes Applied 05 23 2014; 10:55:15AM Mission Editor Changes Applied 05 23 2014; 10:55:25AM Processing Requirement 4.3-1: Return Status : Not Run ===================== No Project Data Available ===================== =============== End of Requirement 4.3-1 =============== 05 23 2014; 10:55:29AM Processing Requirement 4.3-2: Return Status : Passed Page 15 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) ===================== No Project Data Available ===================== =============== End of Requirement 4.3-2 =============== 05 23 2014; 10:55:32AM Requirement 4.4-3: Compliant =============== End of Requirement 4.4-3 =============== 05 23 2014; 10:55:35AM Processing Requirement 4.5-1: Return Status : Passed ============== Run Data ============== **INPUT** Space Structure Name = Centennial-1 Space Structure Type = Payload Perigee Altitude = 420.000000 (km) Apogee Altitude = 420.000000 (km) Inclination = 51.645600 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass Ratio = 0.007700 (m^2/kg) Start Year = 2014.875000 (yr) Initial Mass = 1.300000 (kg) Final Mass = 1.300000 (kg) Duration = 0.500000 (yr) Station-Kept = False 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** Page 16 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) Collision Probability = 0.000000 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range Status = Pass ============== =============== End of Requirement 4.5-1 =============== 05 23 2014; 10:55:38AM Requirement 4.5-2: Compliant 05 23 2014; 10:55:39AM Processing Requirement 4.6 Return Status : Passed ============== Project Data ============== **INPUT** Space Structure Name = Centennial-1 Space Structure Type = Payload Perigee Altitude = 420.000000 (km) Apogee Altitude = 420.000000 (km) Inclination = 51.645600 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.007700 (m^2/kg) Start Year = 2014.875000 (yr) Initial Mass = 1.300000 (kg) Final Mass = 1.300000 (kg) Duration = 0.500000 (yr) Station Kept = False Abandoned = True PMD Perigee Altitude = 383.968096 (km) PMD Apogee Altitude = 391.769883 (km) PMD Inclination = 51.639558 (deg) PMD RAAN = 169.106414 (deg) PMD Argument of Perigee = 146.521649 (deg) PMD Mean Anomaly = 0.000000 (deg) Page 17 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) **OUTPUT** Suggested Perigee Altitude = 383.968096 (km) Suggested Apogee Altitude = 391.769883 (km) Returned Error Message = Passes LEO reentry orbit criteria. Released Year = 2016 (yr) Requirement = 61 Compliance Status = Pass ============== =============== End of Requirement 4.6 =============== 05 23 2014; 10:56:33AM *********Processing Requirement 4.7-1 Return Status : Passed ***********INPUT**** Item Number = 1 name = Centennial-1 quantity = 1 parent = 0 materialID = 8 type = Box Aero Mass = 1.300000 Thermal Mass = 1.300000 Diameter/Width = 0.100000 Length = 0.100000 Height = 0.100000 name = Centennial-1 quantity = 1 parent = 1 materialID = 8 type = Box Aero Mass = 1.300000 Thermal Mass = 1.300000 Diameter/Width = 0.100000 Length = 0.100000 Page 18 of 19

Centennial-1 Orbital Debris Assessment Report (ODAR) Height = 0.100000 **************OUTPUT**** Item Number = 1 name = Centennial-1 Demise Altitude = 77.996918 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Centennial-1 Demise Altitude = 65.210062 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 Centennial-1does not use controlled reentry. 4.7-1, b) NOT APPLICABLE. For controlled reentry, 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 landmasses, 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 reentries, the product of the probability of failure of the reentry burn (from Requirement 4.6-4.b) and the risk of human casualty assuming uncontrolled reentry 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 Centennial-1 mission. END of ODAR for Centennial-1 Page 19 of 19


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