Exhibit 2 ODAR

0864-EX-CN-2017 Text Documents

BlackSky Global, LLC

2017-11-13ELS_201074

BlackSky Global, LLC Exhibit 2 FCC Form 442 BlackSky’s Global-1 Satellite Orbital Debris Assessment Report (ODAR) This report is presented in compliance with NASA-STD-8719.14, APPENDIX A. Report Version: 4 , September 28, 2017 Revision history: Version Date Author Description 1 1/4/17 Lang Kenney Creation of report for Global-1 spacecraft 2 1/20/2017 Lang Kenney Update of the report to include Global-2,3,4 3 4/26/2017 John Springmann Modified Global-1 orbit 3a 5/19/17 John Springmann Reduced to cover Global-1 satellite, only. Technical content otherwise unchanged. 4 9/28/2017 Lang Kenney Modified Global-1 Launch date Document Data is Not Restricted. This document contains no proprietary, ITAR, or export controlled information. DAS Software Version Used In Analysis: v2.0.2 DAS Solar flux file Used: Released 7 November 2016

Global-1 Orbital Debris Assessment Report (ODAR) Table Contents Self-assessment of the ODAR using the format in Appendix A.2 of NASA-STD- 8719.14:............................. 3 Assessment Report Format: .......................................................................................................................... 4 ODAR Section 1: Program Management and Mission Overview ................................................................... 4 ODAR Section 2: Spacecraft Description........................................................................................................ 5 ODAR Section 3: Assessment of Spacecraft Debris Released during Normal Operations ............................. 6 ODAR Section 4: Assessment of Spacecraft Intentional Breakups and Potential for Explosions. .................. 7 ODAR Section 5: Assessment of Spacecraft Potential for On-Orbit Collisions ............................................. 10 ODAR Section 6: Assessment of Spacecraft Post-mission Disposal Plans and Procedures ......................... 11 ODAR Section 7: Assessment of Spacecraft Reentry Hazards...................................................................... 13 ODAR Section 8: Assessment for Tether Missions ....................................................................................... 32 Table of figures Figure 1. CAD model of the Global-1 spacecraft........................................................................................... 5 Figure 2: Global-1 Apogee/Perigee Altitude History for a Given Orbit....................................................... 13 Table of tables Table 1: Mission Milestones ......................................................................................................................... 4 Table 2: Launch Vehicle and Launch Site ...................................................................................................... 4 Table 3: Orbit profile ..................................................................................................................................... 5 Table 4: Large Debris Generation ............................................................................................................... 11 Table 5: Lifetimes ........................................................................................................................................ 12 Table 6. Casualty risk from re-entry debris................................................................................................. 14 Page 2

Global-1 Orbital Debris Assessment Report (ODAR) 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. Orbital Debris Self-Assessment Report Evaluation: Global-1 Launch Vehicle Spacecraft Requirement # Compliant Not Incomplete Standard Non Compliant Not Incomplete Comments Compliant or N/A Compliant Compliant 4.3-1.a No Debris Released in LEO. 4.3-1.b No Debris Released in LEO. 4.3-2 No Debris Released in GEO. 4.4-1 Not applicable. 4.4-2 Warm-gas propulsion tank will be deplete during operations 4.4-3 No planned breakups. 4.4-4 No planned breakups. 4.5-1 Collision probability 0.00001 4.5-2 Damage probability < 0.0099 4.6-1(a) Natural forces cause atmospheric reentry 4.6-1(b) Not applicable. 4.6-1(c) Not applicable. 4.6-2 Spacecraft does not go to GEO. 4.6-3 Spacecraft does not go beyond LEO. 4.6-4 Requirements 4.6-1 through 4.6-3 are met 4.7-1 DAS reports human casualty probability < 1:10,000 4.8-1 No tethers used. Page 3

Global-1 Orbital Debris Assessment Report (ODAR) Assessment Report Format: ODAR Technical Sections Format Requirements: BlackSky Global, LLC is a US company; this ODAR, for BlackSky Global’s Global-1 satellite, 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. Sections 9 through 14 apply to the launch vehicles ODAR and are not covered here. All files created from the DAS 2.0.2 software and calculation files are located on Windchill. Windchill Link (This is a BlackSky Global, LLC internal reference) ODAR Section 1: Program Management and Mission Overview Project Manager: John Springmann Foreign government or space agency participation: none Schedule of upcoming mission milestones: Satellite Flight Readiness Review Launch Global-1 February 2018 May-June 2018 Table 1: Mission Milestones Mission Overview: Global-1 is an Earth observation satellite. It is a follow-on mission to BlackSky’s Pathfinder-1 satellite and is the first in a series of BlackSky satellites. The launch window for Global-1 is May-June 2018. The satellite will be deployed into circular sun-synchronous low-Earth orbit. The altitude of the circular orbit will be between 500 and 550 km. The spacecraft is a secondary payload on the launch, and the exact altitude within the 500-550 km range has not yet been confirmed. 550 km is the altitude used in this report as that is the conservative assumption from an orbital lifetime standpoint. The orbit details used in this report are summarized in Table 3 below. The planned mission duration for the satellite is 36 months (3 years). At the end of its mission, the satellite will release any remaining propellant (which is expected to be depleted during operations) and rely on atmospheric drag to fully deorbit the spacecraft. 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 (max is 16.5 years including 3 years of operations, as calculated by DAS 2.0.2). Launch vehicles and launch sites: Project Launch Vehicle Launch location Global-1 PSLV Satish Dhawan Space Centre, Sriharikota, India Table 2: Launch Vehicle and Launch Site Page 4

Global-1 Orbital Debris Assessment Report (ODAR) Mission duration: Maximum Nominal Operations: 36 months (3 years) Post-Operations Orbit lifetime: See Table 5 in section 6.3 Satellite launch and orbit profile: Project Altitude Inclination LTDN or Comments LTAN Global-1 550 km 97.59° 09:30 LTDN 550 km circular orbit Table 3: Orbit profile ODAR Section 2: Spacecraft Description Physical description of the spacecraft: Global-1 has a launch mass of 54.38 kg. Basic physical dimensions are 45 cm x 50 cm x 84.5 cm. A CAD model of the spacecraft is shown in Figure 1. Figure 1. CAD model of the Global-1 spacecraft. The satellite’s load bearing structure is comprised of three 45 cm x 50 cm skeleton deck plates, radiating side plates, and a vertical mounted 66.5cm x 84.5 cm side solar panel connected with struts. The satellite maintains 3-axis attitude control. Attitude knowledge is provided primarily by two orthogonally mounted star trackers. Attitude actuators include four reaction wheels and three orthogonal magnetorquers. Total satellite mass at launch, including all propellants and fluids: 54.38 kg. Dry mass of satellites at launch, excluding solid rocket motor propellants: 50.62 kg Page 5

Global-1 Orbital Debris Assessment Report (ODAR) Description of all propulsion systems (cold gas, mono-propellant, bi-propellant, electric, nuclear): Global-1 contains a single propulsion system with a single valve and a single thruster. This system uses electrically warmed butane as the working fluid. Butane is stored at saturation conditions (normally 1 to 100 psi) within two interconnected tanks. The butane is warmed to several hundred degrees Celsius via an electrically heated aluminum block just before exiting the nozzle. Propulsion is not required to deorbit the satellite, but is part of the satellite to allow for orbit phasing and minor orbit adjustments. 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: 3.76 kg of butane at saturation conditions not to exceed 100psia Fluids in Pressurized Batteries: None. Global-1 uses two unpressurized standard COTS Lithium-Ion batteries. Each battery has a height of 98mm, a width of 96mm, a length of 176mm, and a mass of 1.4 kg. Description of attitude control system and indication of the normal attitude of the spacecraft with respect to the velocity vector: The long axis of the spacecraft can be oriented parallel to the nadir vector during imaging, but the satellite will typically be oriented in a sun-pointing attitude. For the purposes of orbital debris assessment, the worst-case (smallest) cross-sectional area is used, meaning that the 45 cm x 50 cm face of the spacecraft is in the velocity direction. This results in a cross-section area of 0.225m2. Using the DAS software, the cross-sectional area during random tumbling is 0.56 m2, and the cross-sectional area during nadir pointing (“long” side of the spacecraft in the velocity direction) is 0.5619 m2. 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 solar 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. Page 6

Global-1 Orbital Debris Assessment Report (ODAR) 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: 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. In addition to the battery protection mentioned about, the Global-1 battery unit features two temperature sensors which monitor battery cells for high temperatures. 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: The butane propulsion system shall be passivated at the end of mission by operating the system to propellant depletion in a perigee lowering maneuver. However, it is expected that all propellant will have already been depleted before the end of the operational mission. Rationale for all items which are required to be passivated, but cannot be due to their design: The satellite’s 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 Page 7

Global-1 Orbital Debris Assessment Report (ODAR) 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. 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. 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. Page 8

Global-1 Orbital Debris Assessment Report (ODAR) 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 3: 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 other mechanical failure, c) obviation of such other mechanical failures by proto- qualification 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 4: 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 5: 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 6: 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 Page 9

Global-1 Orbital Debris Assessment Report (ODAR) environmental tests must occur to result in this failure mode. Failure Mode 7: Excess temperatures due to orbital environment and high discharge combined. Mitigation 7: 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 over- current monitoring and control must all fail for this failure mode to occur. 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: Global 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 Page 10

Global-1 Orbital Debris Assessment Report (ODAR) 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: Satellite Collision Probability Compliance status Global-1 0.00001 COMPLIANT Table 4: Large Debris Generation 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: Collision Probability: not applicable; COMPLIANT. The satellite orbits decay naturally; no propulsion is required for most-mission disposal. Thus there are no parts of the satellite that are critical to be in compliance with post-mission disposal requirements. Identification of all systems or components required to accomplish any postmission disposal operation, including passivation and maneuvering: No systems or components are required. The orbit for Global-1 naturally decays with no maneuvering required. ODAR Section 6: Assessment of Spacecraft Post-mission Disposal Plans and Procedures 6.1 Description of spacecraft disposal option selected: After completing its planned operations, the satellites will deorbit naturally by atmospheric re-entry. At the end of the satellite’s operational life (i.e. at EOM) the attitude control system will stop counteracting the aerodynamic disturbance torques. This will result in the satellite gradually assuming a dynamically stable configuration. For atmospheric drag / re-entry calculations in DAS, the minimum plausible cross-section drag area of 45 x 50 cm was assumed (smallest spacecraft side facing the velocity direction). This is conservative because it represents the minimum cross section possible and ignores the fact that the satellite may be in other Page 11

Global-1 Orbital Debris Assessment Report (ODAR) orientations after the end of the mission. 6.2 Plan for any spacecraft maneuvers required to accomplish postmission disposal: No maneuvers are required following normal operations. 6.3 Calculation of area-to-mass ratio after postmission disposal, if the controlled reentry option is not selected: Spacecraft Mass (EOL): 50.62 kg Cross-sectional Area: 0.225 m2 Area to mass ratio: 0.004444883 m2/kg 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. The analysis of this requirement for each satellite is shown below. Satellite Name Operational Orbit Post-ops Life Total Lifetime Global-1 550 km circular 13.5 years 16.5 years Table 5: Lifetimes Altitude history versus time was analyzed for Global-1 and is shown below. Page 12

Global-1 Orbital Debris Assessment Report (ODAR) Global-1 Altitude history over time: Figure 2: Global-1 Apogee/Perigee Altitude History for a Given Orbit Analysis: The Global-1 satellite reentry is COMPLIANT using method “a: Atmospheric reentry option”. 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 Postmission Disposal Operations Analysis: The minimum drag configuration is the aerodynamically stable state, and provides the worst-case re-entry time. This minimum drag configuration was assumed for atmospheric re-entry analysis. 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: Page 13

Global-1 Orbital Debris Assessment Report (ODAR) 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 Global-1 is compliant with the requirement. The total risk of human casualty for each spacecraft is given in the table below. According to DAS calculations, there is a low probability that some spacecraft components may reach the ground (see DAS input data below for input parameters). However, the DAS software does not currently allow explicit modeling of the specific geometries for these components, so these numbers are expected to be larger than anticipated due to conservatism in the inputs provided to DAS. Satellite Risk of Human Compliance status Casualty Global-1 1:26,300 COMPLIANT Table 6. Casualty risk from re-entry debris. Below is a full output from the DAS software for Global-1. Analysis (per DAS v2.0.2): 09 28 2017; 11:35:49AM DAS Application Started 09 28 2017; 11:36:44AM Processing Requirement 4.3-1: Return Status : Not Run ===================== No Project Data Available ===================== =============== End of Requirement 4.3-1 =============== 09 28 2017; 11:36:46AM Processing Requirement 4.3-2: Return Status : Passed ===================== No Project Data Available ===================== =============== End of Requirement 4.3-2 =============== 09 28 2017; 11:36:48AM Requirement 4.4-3: Compliant =============== End of Requirement 4.4-3 =============== 09 28 2017; 11:36:52AM Processing Requirement 4.5-1: Return Status : Passed ============== Run Data ============== **INPUT** Space Structure Name = Global-1 Page 14

Global-1 Orbital Debris Assessment Report (ODAR) Space Structure Type = Payload Perigee Altitude = 550.000000 (km) Apogee Altitude = 550.000000 (km) Inclination = 97.590000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass Ratio = 0.004445 (m^2/kg) Start Year = 2018.000000 (yr) Initial Mass = 58.080000 (kg) Final Mass = 54.320000 (kg) Duration = 3.000000 (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** Collision Probability = 0.000007 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range Status = Pass ============== =============== End of Requirement 4.5-1 =============== 09 28 2017; 11:38:04AM Requirement 4.5-2: Compliant ================================================== Spacecraft = Global-1 Critical Surface = FC+X ================================================== **INPUT** Apogee Altitude = 550.000000 (km) Perigee Altitude = 550.000000 (km) Orbital Inclination = 97.590000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass = 0.004445 (m^2/kg) Initial Mass = 54.320000 (kg) Final Mass = 54.320000 (kg) Station Kept = No Start Year = 2018.000000 (yr) Duration = 3.000000 (yr) Page 15

Global-1 Orbital Debris Assessment Report (ODAR) Orientation = Random Tumbling CS Areal Density = 16.221668 (g/cm^2) CS Surface Area = 0.026384 (m^2) Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w)) CS Pressurized = No Outer Wall 1 Density: 0.427403 (g/cm^2) Separation: 5.000000 (cm) **OUTPUT** Probabilty of Penitration = 0.000000 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range ================================================== Spacecraft = Global-1 Critical Surface = FX+Y ================================================== **INPUT** Apogee Altitude = 550.000000 (km) Perigee Altitude = 550.000000 (km) Orbital Inclination = 97.590000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass = 0.004445 (m^2/kg) Initial Mass = 54.320000 (kg) Final Mass = 54.320000 (kg) Station Kept = No Start Year = 2018.000000 (yr) Duration = 3.000000 (yr) Orientation = Random Tumbling CS Areal Density = 38.073997 (g/cm^2) CS Surface Area = 0.011241 (m^2) Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w)) CS Pressurized = No Outer Wall 1 Density: 0.383772 (g/cm^2) Separation: 5.000000 (cm) **OUTPUT** Probabilty of Penitration = 0.000000 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range ================================================== Spacecraft = Global-1 Critical Surface = Battery+X ================================================== **INPUT** Page 16

Global-1 Orbital Debris Assessment Report (ODAR) Apogee Altitude = 550.000000 (km) Perigee Altitude = 550.000000 (km) Orbital Inclination = 97.590000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass = 0.004445 (m^2/kg) Initial Mass = 54.320000 (kg) Final Mass = 54.320000 (kg) Station Kept = No Start Year = 2018.000000 (yr) Duration = 3.000000 (yr) Orientation = Random Tumbling CS Areal Density = 9.276438 (g/cm^2) CS Surface Area = 0.017248 (m^2) Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w)) CS Pressurized = No Outer Wall 1 Density: 0.427403 (g/cm^2) Separation: 1.000000 (cm) **OUTPUT** Probabilty of Penitration = 0.000001 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range ================================================== Spacecraft = Global-1 Critical Surface = Battery+Y ================================================== **INPUT** Apogee Altitude = 550.000000 (km) Perigee Altitude = 550.000000 (km) Orbital Inclination = 97.590000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass = 0.004445 (m^2/kg) Initial Mass = 54.320000 (kg) Final Mass = 54.320000 (kg) Station Kept = No Start Year = 2018.000000 (yr) Duration = 3.000000 (yr) Orientation = Random Tumbling CS Areal Density = 17.006803 (g/cm^2) CS Surface Area = 0.009408 (m^2) Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w)) CS Pressurized = No Outer Wall 1 Density: 0.383772 (g/cm^2) Separation: 1.000000 (cm) **OUTPUT** Page 17

Global-1 Orbital Debris Assessment Report (ODAR) Probabilty of Penitration = 0.000000 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range ================================================== Spacecraft = Global-1 Critical Surface = Tank+Y ================================================== **INPUT** Apogee Altitude = 550.000000 (km) Perigee Altitude = 550.000000 (km) Orbital Inclination = 97.590000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass = 0.004445 (m^2/kg) Initial Mass = 54.320000 (kg) Final Mass = 54.320000 (kg) Station Kept = No Start Year = 2018.000000 (yr) Duration = 3.000000 (yr) Orientation = Random Tumbling CS Areal Density = 1.672847 (g/cm^2) CS Surface Area = 1.003839 (m^2) Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w)) CS Pressurized = Yes Outer Wall 1 Density: 0.676247 (g/cm^2) Separation: 10.000000 (cm) **OUTPUT** Probabilty of Penitration = 0.001373 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range ================================================== Spacecraft = Global-1 Critical Surface = Tank+X ================================================== **INPUT** Apogee Altitude = 550.000000 (km) Perigee Altitude = 550.000000 (km) Orbital Inclination = 97.590000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass = 0.004445 (m^2/kg) Initial Mass = 54.320000 (kg) Page 18

Global-1 Orbital Debris Assessment Report (ODAR) Final Mass = 54.320000 (kg) Station Kept = No Start Year = 2018.000000 (yr) Duration = 3.000000 (yr) Orientation = Random Tumbling CS Areal Density = 1.672847 (g/cm^2) CS Surface Area = 0.707557 (m^2) Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w)) CS Pressurized = Yes Outer Wall 1 Density: 0.427403 (g/cm^2) Separation: 10.000000 (cm) **OUTPUT** Probabilty of Penitration = 0.003181 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range 09 28 2017; 11:38:58AM Processing Requirement 4.6 Return Status : Passed ============== Project Data ============== **INPUT** Space Structure Name = Global-1 Space Structure Type = Payload Perigee Altitude = 550.000000 (km) Apogee Altitude = 550.000000 (km) Inclination = 97.590000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.004445 (m^2/kg) Start Year = 2018.000000 (yr) Initial Mass = 58.080000 (kg) Final Mass = 54.320000 (kg) Duration = 3.000000 (yr) Station Kept = False Abandoned = True PMD Perigee Altitude = 548.898882 (km) PMD Apogee Altitude = 548.898882 (km) PMD Inclination = 97.641317 (deg) PMD RAAN = 359.660653 (deg) PMD Argument of Perigee = 1.693062 (deg) PMD Mean Anomaly = 0.000000 (deg) **OUTPUT** Suggested Perigee Altitude = 548.898882 (km) Page 19

Global-1 Orbital Debris Assessment Report (ODAR) Suggested Apogee Altitude = 548.898882 (km) Returned Error Message = Passes LEO reentry orbit criteria. Released Year = 2034 (yr) Requirement = 61 Compliance Status = Pass ============== =============== End of Requirement 4.6 =============== 09 28 2017; 11:39:02AM *********Processing Requirement 4.7-1 Return Status : Passed ***********INPUT**** Item Number = 1 name = Global-1 quantity = 1 parent = 0 materialID = 5 type = Box Aero Mass = 54.320000 Thermal Mass = 54.320000 Diameter/Width = 0.500000 Length = 0.845000 Height = 0.450000 name = Payload Deck quantity = 1 parent = 1 materialID = 8 type = Flat Plate Aero Mass = 12.770090 Thermal Mass = 5.400000 Diameter/Width = 0.450000 Length = 0.500000 name = Telescope quantity = 1 parent = 2 materialID = 5 type = Cylinder Aero Mass = 5.860000 Thermal Mass = 5.860000 Diameter/Width = 0.300000 Length = 0.478000 name = Camera quantity = 1 parent = 2 materialID = -2 type = Box Page 20

Global-1 Orbital Debris Assessment Report (ODAR) Aero Mass = 0.319000 Thermal Mass = 0.319000 Diameter/Width = 0.045000 Length = 0.045000 Height = 0.039000 name = Star Tracker quantity = 2 parent = 2 materialID = 5 type = Cylinder Aero Mass = 0.158000 Thermal Mass = 0.158000 Diameter/Width = 0.100000 Length = 0.120000 name = IMU quantity = 2 parent = 2 materialID = 8 type = Box Aero Mass = 0.055000 Thermal Mass = 0.055000 Diameter/Width = 0.038600 Length = 0.044800 Height = 0.021500 name = Magnetometer 1 quantity = 1 parent = 2 materialID = 8 type = Box Aero Mass = 0.080090 Thermal Mass = 0.080090 Diameter/Width = 0.043000 Length = 0.099170 Height = 0.017000 name = DC-DC Converter 1 quantity = 5 parent = 2 materialID = 8 type = Box Aero Mass = 0.137000 Thermal Mass = 0.137000 Diameter/Width = 0.077500 Length = 0.083000 Height = 0.018230 name = Antenna Deck quantity = 1 parent = 1 Page 21

Global-1 Orbital Debris Assessment Report (ODAR) materialID = 8 type = Flat Plate Aero Mass = 1.173090 Thermal Mass = 0.363000 Diameter/Width = 0.450000 Length = 0.500000 name = X-Band Antenna quantity = 1 parent = 9 materialID = 8 type = Flat Plate Aero Mass = 0.300000 Thermal Mass = 0.300000 Diameter/Width = 0.103403 Length = 0.149936 name = S-Band Antenna quantity = 1 parent = 9 materialID = 8 type = Flat Plate Aero Mass = 0.120000 Thermal Mass = 0.120000 Diameter/Width = 0.083820 Length = 0.083820 name = Magnetometer 2 quantity = 1 parent = 9 materialID = 8 type = Box Aero Mass = 0.080090 Thermal Mass = 0.080090 Diameter/Width = 0.045000 Length = 0.099170 Height = 0.017000 name = Coarse Sun Sensor quantity = 2 parent = 9 materialID = 8 type = Cylinder Aero Mass = 0.005000 Thermal Mass = 0.005000 Diameter/Width = 0.015300 Length = 0.064000 name = UHF Patch quantity = 1 parent = 9 materialID = -2 Page 22

Global-1 Orbital Debris Assessment Report (ODAR) type = Flat Plate Aero Mass = 0.300000 Thermal Mass = 0.300000 Diameter/Width = 0.088900 Length = 0.088900 name = Propulsion Deck quantity = 1 parent = 1 materialID = 8 type = Flat Plate Aero Mass = 13.033000 Thermal Mass = 5.400000 Diameter/Width = 0.450000 Length = 0.500000 name = Tank 1 quantity = 1 parent = 15 materialID = 5 type = Cylinder Aero Mass = 3.440000 Thermal Mass = 3.440000 Diameter/Width = 0.159766 Length = 0.249936 name = Tank 2 quantity = 1 parent = 15 materialID = 5 type = Cylinder Aero Mass = 3.440000 Thermal Mass = 3.440000 Diameter/Width = 0.159766 Length = 0.249936 name = Valve Assembly quantity = 1 parent = 15 materialID = 8 type = Box Aero Mass = 0.210000 Thermal Mass = 0.210000 Diameter/Width = 0.046355 Length = 0.096500 Height = 0.025400 name = HEX quantity = 1 parent = 15 materialID = 54 type = Box Page 23

Global-1 Orbital Debris Assessment Report (ODAR) Aero Mass = 0.388000 Thermal Mass = 0.388000 Diameter/Width = 0.054940 Length = 0.127000 Height = 0.007620 name = Couse Sun Sensor quantity = 4 parent = 15 materialID = 8 type = Cylinder Aero Mass = 0.005000 Thermal Mass = 0.005000 Diameter/Width = 0.015300 Length = 0.064000 name = Fine Sun Sensor quantity = 1 parent = 15 materialID = 5 type = Box Aero Mass = 0.035000 Thermal Mass = 0.035000 Diameter/Width = 0.032000 Length = 0.034000 Height = 0.021000 name = UHF Patch Antenna quantity = 1 parent = 15 materialID = 8 type = Flat Plate Aero Mass = 0.100000 Thermal Mass = 0.100000 Diameter/Width = 0.088900 Length = 0.088900 name = Avionics Deck quantity = 1 parent = 1 materialID = 8 type = Flat Plate Aero Mass = 18.226700 Thermal Mass = 5.400000 Diameter/Width = 0.450000 Length = 0.500000 name = PCU quantity = 1 parent = 23 materialID = 5 type = Box Page 24

Global-1 Orbital Debris Assessment Report (ODAR) Aero Mass = 0.990000 Thermal Mass = 0.990000 Diameter/Width = 0.147000 Length = 0.202000 Height = 0.050000 name = Battery quantity = 2 parent = 23 materialID = -1 type = Box Aero Mass = 1.600000 Thermal Mass = 1.600000 Diameter/Width = 0.098000 Length = 0.176000 Height = 0.096000 name = DC-DC Converter 2 quantity = 3 parent = 23 materialID = 8 type = Box Aero Mass = 0.137000 Thermal Mass = 0.137000 Diameter/Width = 0.077500 Length = 0.083000 Height = 0.018230 name = X-Band Radio quantity = 1 parent = 23 materialID = 8 type = Box Aero Mass = 1.000000 Thermal Mass = 1.000000 Diameter/Width = 0.115000 Length = 0.160000 Height = 0.046000 name = S-Band Radio quantity = 1 parent = 23 materialID = 8 type = Box Aero Mass = 0.200000 Thermal Mass = 0.200000 Diameter/Width = 0.050000 Length = 0.135000 Height = 0.025000 name = UHF Radio/Splitter quantity = 1 Page 25

Global-1 Orbital Debris Assessment Report (ODAR) parent = 23 materialID = 54 type = Box Aero Mass = 0.230000 Thermal Mass = 0.230000 Diameter/Width = 0.057150 Length = 0.082550 Height = 0.015748 name = FC quantity = 1 parent = 23 materialID = 8 type = Box Aero Mass = 4.280000 Thermal Mass = 4.280000 Diameter/Width = 0.121920 Length = 0.216408 Height = 0.092202 name = Reaction Wheels quantity = 4 parent = 23 materialID = 8 type = Box Aero Mass = 0.226000 Thermal Mass = 0.226000 Diameter/Width = 0.140000 Length = 0.140000 Height = 0.041900 name = Torque Rods quantity = 3 parent = 23 materialID = 54 type = Cylinder Aero Mass = 0.420000 Thermal Mass = 0.420000 Diameter/Width = 0.022220 Length = 0.227000 name = GPS Receiver quantity = 1 parent = 23 materialID = 54 type = Box Aero Mass = 0.214700 Thermal Mass = 0.214700 Diameter/Width = 0.057150 Length = 0.060320 Height = 0.012060 Page 26

Global-1 Orbital Debris Assessment Report (ODAR) name = DC-DC Converter 3 quantity = 1 parent = 23 materialID = 8 type = Box Aero Mass = 0.137000 Thermal Mass = 0.137000 Diameter/Width = 0.077500 Length = 0.083000 Height = 0.018230 name = Solar Array quantity = 1 parent = 1 materialID = 24 type = Flat Plate Aero Mass = 3.800000 Thermal Mass = 3.800000 Diameter/Width = 0.665000 Length = 0.845000 name = Radiating Side Panel quantity = 2 parent = 1 materialID = 8 type = Flat Plate Aero Mass = 0.700000 Thermal Mass = 0.700000 Diameter/Width = 0.380000 Length = 0.431000 name = Support Strut quantity = 2 parent = 1 materialID = 8 type = Box Aero Mass = 0.144000 Thermal Mass = 0.144000 Diameter/Width = 0.150000 Length = 0.582000 Height = 0.020000 name = Front Side Panel quantity = 1 parent = 1 materialID = 8 type = Flat Plate Aero Mass = 0.700000 Thermal Mass = 0.700000 Diameter/Width = 0.380000 Length = 0.480000 Page 27

Global-1 Orbital Debris Assessment Report (ODAR) **************OUTPUT**** Item Number = 1 name = Global-1 Demise Altitude = 77.997965 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Payload Deck Demise Altitude = 68.885222 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Telescope Demise Altitude = 58.509975 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Camera Demise Altitude = 68.885222 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Star Tracker Demise Altitude = 67.341347 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = IMU Demise Altitude = 66.264402 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Magnetometer 1 Demise Altitude = 66.786863 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = DC-DC Converter 1 Demise Altitude = 65.303589 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Antenna Deck Page 28

Global-1 Orbital Debris Assessment Report (ODAR) Demise Altitude = 77.366926 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = X-Band Antenna Demise Altitude = 72.430761 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = S-Band Antenna Demise Altitude = 73.483230 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Magnetometer 2 Demise Altitude = 75.139793 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Coarse Sun Sensor Demise Altitude = 76.988777 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = UHF Patch Demise Altitude = 77.366926 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Propulsion Deck Demise Altitude = 68.921589 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Tank 1 Demise Altitude = 57.402026 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Tank 2 Demise Altitude = 57.402026 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 Page 29

Global-1 Orbital Debris Assessment Report (ODAR) ************************************* name = Valve Assembly Demise Altitude = 64.311054 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = HEX Demise Altitude = 0.000000 Debris Casualty Area = 0.439607 Impact Kinetic Energy = 439.511475 ************************************* name = Couse Sun Sensor Demise Altitude = 68.593847 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Fine Sun Sensor Demise Altitude = 66.532441 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = UHF Patch Antenna Demise Altitude = 65.786589 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Avionics Deck Demise Altitude = 69.427870 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = PCU Demise Altitude = 61.972105 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Battery Demise Altitude = 69.427870 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = DC-DC Converter 2 Demise Altitude = 66.458191 Debris Casualty Area = 0.000000 Page 30

Global-1 Orbital Debris Assessment Report (ODAR) Impact Kinetic Energy = 0.000000 ************************************* name = X-Band Radio Demise Altitude = 61.091561 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = S-Band Radio Demise Altitude = 66.526620 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = UHF Radio/Splitter Demise Altitude = 0.000000 Debris Casualty Area = 0.428833 Impact Kinetic Energy = 185.780930 ************************************* name = FC Demise Altitude = 50.213670 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Reaction Wheels Demise Altitude = 67.211089 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Torque Rods Demise Altitude = 60.848722 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = GPS Receiver Demise Altitude = 0.000000 Debris Casualty Area = 0.416913 Impact Kinetic Energy = 217.243118 ************************************* name = DC-DC Converter 3 Demise Altitude = 66.458191 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Solar Array Page 31

Global-1 Orbital Debris Assessment Report (ODAR) Demise Altitude = 0.000000 Debris Casualty Area = 1.821465 Impact Kinetic Energy = 419.443970 ************************************* name = Radiating Side Panel Demise Altitude = 76.037082 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Support Strut Demise Altitude = 77.549590 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Front Side Panel Demise Altitude = 76.245402 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* =============== End of Requirement 4.7-1 =============== ODAR Section 8: Assessment for Tether Missions Not applicable. There are no tethers on the Global satellites. END of ODAR for Global-1 Page 32


Document Created: 2017-11-13 15:37:05
Document Modified: 2017-11-13 15:37:05
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