Attachment Presentation to NOAA

This document pretains to SAT-STA-20101202-00250 for Special Temporal Authority on a Satellite Space Stations filing.

IBFS_SATSTA2010120200250_854478

OrbView‐3 De‐Orbit November 1, 2010 Bill Schuster Chief Operating Officer, GeoEye 1

Agenda • Briefing Overview • Regulatory Approvals • OrbView‐3 Spacecraft Status • Timing • Execution and Verification Team • De‐Orbit Plan • Risks and Mitigation Approach • Summary 2

Overview • OrbView‐3 is no longer capable of performing its mission • GeoEye’s License to Operate a Private Remote Sensing Space System from NOAA includes requirement for proper vehicle disposal – Paragraph 11 states “…The Licensee will deorbit the spacecraft by means of either a Licensee‐ controlled de‐orbit and re‐entry over a broad ocean area, or a natural orbital decay and uncontrolled atmospheric re‐entry.” • GeoEye has chosen to complete a controlled deorbit to ensure we remove OV‐3 as potential source of orbital debris 3

Overview (continued) • Regulatory Approvals: OrbView‐3 satellite (OV‐3) de‐ orbit requires NOAA/FCC regulatory approvals • OV‐3 is Non‐Operational: No imaging operations since 2007; decision has been made to de‐orbit • Timing: By January 2011; no space for OV‐3 flight operations in GeoEye’s new HQ facilities • De‐Orbit Plan: Developed by expert team with de‐orbit and flight dynamics experience • Risk Mitigation: Risks identified and mitigated 4

Regulatory Approvals • OV‐3 licensed by NOAA in 1994 – Regulations require that satellite disposal be in a manner satisfactory to the President and de‐orbit plans be approved by NOAA – NOAA license requires either controlled de‐orbit over broad ocean area or natural orbital decay/uncontrolled atmospheric reentry • OV‐3 licensed by FCC in 1999 – Regulations require special temporary authority if de‐orbit changes the satellite orbital parameters originally authorized 5

OV‐3 Spacecraft Status • OV‐3 was launched June 26, 2003 – Normal imaging operations until Spring 2007 • Anomaly experienced and reported March 2007 • Total loss of camera operations; unrecoverable – Satellite attitude and control is fully functional – Current altitude approximately 438 km (271 miles) – Remaining usable propellant 22.98 kg • 150% of calculated amount necessary for deorbit • Insurance – On‐orbit insurance claim was paid in 2008 – GeoEye holds $22M of third party general commercial liability insurance for property damage and personal injury 6

OV‐3 Spacecraft Status cont. Subsystem Key Parameters Mission  Commercial Imaging  5 Year Mission Mass:  670 lb launch weight (303.9 kg) Size:  104 x 75 x 45 inch (deployed)  Cylindrical Structure: 40” dia. x 75 “ long  Solar Array: 104” x 66”, body mounted Attitude Control  3-axis controlled, zero momentum control system  Fiber Optic IRU  2 x Star Trackers  Coarse Sun Senors  3-Axis Magnetometer  GPS receiver  Magnetic Torque Rods  4 Reaction Wheels (3 axes + skew) Payload  1m panchromatic, 4m Multispectral Camera  32 Gigabit Solid State Recorder  X-band transmiter for payload data downlink  2-axis gimbal High Gain X-band antenna  Dedicated Payload Interface Processor TT&C  UHF Telemetry and Encrypted Command link  Backdoor receiver for limited commanding C&DH  Distributed Architecture  Dedicated CDH, ACS, and Payload 80C186 Processors Propulsion System  Monopropellant Blowdown  Four x 1.0 lbf thrusters Electric Power  Bus Voltage: 22-34 Vdc  22 Cell Nickel Hydrogen Battery (11 CPV’s)  625 Watt Solar Array (EOL) ADS Proprietary 7

Timing • January 2011: GeoEye moving to new HQ building – No space planned for OV‐3 flight operations • [December 15, 2010]: Begin implementation of OV‐3 de‐orbit plan; complete de‐orbit around December 31, 2010 – Assumes NOAA/FCC de‐orbit regulatory approvals obtained • [January 4, 2011]: Latest start date to complete OV‐3 de‐orbit before GeoEye HQ move 8

Execution Team • GeoEye selected experienced de‐orbit contractor • Applied Defense Solutions (ADS) to perform the OV‐3 de‐orbit analysis and operations • Based on experience in de‐orbit precision analysis/planning and operations work – NASA COTS – International Space Station (ISS) Resupply • Re‐entry flight dynamics software • Re‐entry analysis – verified and validated by NASA/JSC • Monte Carlo analysis tools development • Re‐entry documentation – NASA’s Compton Gamma Ray Observatory • Re‐Entry Trajectory Analysis • Re‐entry performed by NASA/GSFC June 4, 2000 – NASA’s Tropical Rainfall Measuring Mission (TRMM) – Feasibility Study • Re‐Entry Trajectory Analysis • Monte Carlo footprint analysis – Mir Reentry • Re‐entry analysis – NASA LCROSS Lunar Impact Planning • Maneuvering calibration • Precision impact targeting – Debris Assessment Software 9

Verification Team • Lockheed‐Martin Space Systems Company • Independent review by orbit / mission experts – Mr. R. Tanner – BS/MS Aerospace Engineering » 29 years experience as orbital analyst / mission analyst » Areas of Expertise: orbit adjust planning, orbit adjust modeling, engine performance modeling, orbital mechanics, operational timelines and space vehicle operations. – Mr. E. Meek – BS/MS Electrical Engineering / Computer Science » 10 years experience as orbital analyst / mission analyst » Areas of Expertise: satellite GN&C, collision avoidance, maneuver planning, proximity operations, and orbital analysis. • Independent Auditor – Col. J. Lopez (Ret.)– BS/MS Aerospace Engineering » 35 years experience in orbital mechanics » Areas of Expertise: Orbital mechanics, space modeling, satellite tool kit 10

DE‐ORBIT PLAN 11

De‐Orbit Planning & Execution Process • Conceptual Planning – Completed – Development of a conceptual scenario to showcase how OV‐3 will be de‐orbited • Understand how lowering could occur • Identify potential issues and start addressing them • Analysis – In Progress – Design Trajectory Plan – Orbit Determination Error Analysis – Run Monte Carlo algorithm against Trajectory Plan • Operations – Maneuver & Trajectory Planning – Verification of impact footprint after each maneuver – Orbit Determination – Conjunction Assessment • All burns will be coordinated with JSpOC prior to execution – Reporting and notification 12

OV‐3 Final Orbit Impact Footprint • Impact occurs quickly after last maneuver • Impact location chosen to be near center of potential zone area – If maneuver under burns or over burns, the impact point is still within potential area • Monte Carlo analysis will provide definition of splash down footprint – Much smaller than the potential zone area • Total duration from the first maneuver execution is approximately 17 days and 2 hours 13

De‐Orbit Plan • The de‐orbit plan contains a iterative process that includes analysis of each step prior to proceeding – Ensures operations follow the plan • 2 to 3 day maneuver execution cycle – Plan maneuver and upload commands – Spacecraft performs commanded maneuver – Ground station contacts the spacecraft and retrieves data • May happen more than once depending on time duration post maneuver – Maneuver analysis is performed, and orbit solution is determined – Verify analyses of executed vs. planned maneuver • Details below – Subsequent maneuver planned and/or overall sequence plan updated as needed – Repeat 14

De‐Orbit Plan (continued) • Two phase de‐orbit plan – Phase 1: Safely lower orbit below the International Space Station (ISS) – Phase 2: Continue lowering orbit to atmospheric entry point • Total of 11 maneuvers are expected to be performed – One calibration burn • Additional calibration maneuvers added as necessary • May be performed at any time prior to de‐orbit – Ten orbit lowering burns • Controlled, Measured, and Verifiable – Burn plan adjusted to account for prior event actual performance 15

De‐Orbit Plan – Phase 1 • Phase 1 consists of 5 maneuvers – 1 Calibration maneuver • Additional calibration maneuvers may be needed based on results – 4 Orbit lowering maneuvers • GeoEye will coordinate with NASA on ISS operations prior to plan commencement and prior to each Phase 1 maneuver • Fail‐safe de‐orbit strategy – Maintain and verify safe distances away from other space objects • Primarily the ISS, due to the risk of human life • All other space objects contained in the space catalog – Provide significant amount of time to recover if a contingency occurs • Guarantees recovery time from contingencies without interfering with the ISS – Each maneuver contributes to de‐orbiting OV‐3 16

De‐Orbit Plan – Phase 2 • 6 maneuvers – Maneuvers lowers orbit to atmospheric entry interface • Eccentric orbit provides steep reentry angle – Increases impact location predictability – Eliminates risk of atmospheric skip • Pacific Ocean is the largest broad ocean impact area • Deorbit area is 700 km away from any land mass • Exceeds 370 km requirement – Exact location dependent on time and duration of maneuvers • Reporting and notification for atmospheric entry to ground propagation – Notify FAA and other proper authorities – NOAA’s assistance coordinating with outer agencies involved in deorbit requested 17

Risks & Risk Mitigation • Risk: Calendar time remaining before the GeoEye move from Dulles, VA to Herndon, VA • Mitigation: Plan in work for over a year. – Solicited NOAA’s input – Plan submittal within sufficient time for USG approval. Pre‐de‐orbit tasks such as calibration burn, to create margin. • Risk: To de‐orbit OV‐3 must pass through the ISS orbital radius – OV‐3 orbital radius higher than ISS’s, inclination is different • Mitigation: Passing through the ISS orbital radius has been addressed in the technical approach – OV‐3/ISS proximity avoided with proper maneuver timing and phasing – Plan keeps OV‐3 and ISS significantly separated at the orbit crossing points – This approach also allows for significant time to respond to a contingency event without risk to the ISS • Interim OV‐3 orbits calculated to provide at least 240 days until next ISS close approach 18

Risks & Risk Mitigation Cont. • Risk: Last orbit adjust maneuver for OV‐3 was July 25, 2006 • Mitigation: Incorporate lessons learned from similar case this past summer (OV‐2) – Fully understand the current state of the spacecraft and what has changed since last maneuver – Same ADS personnel working both missions • Mitigation: Planning on performing a calibration burn to test the engines, ensuring that: – The engines fire as commanded – Allows for the validation of the maneuver plan and adjust as necessary – Verifies spacecraft pointing accuracy and stability • Risk: Limited amount of fuel remaining • Mitigation: Fuel usage has been modeled and will be monitored throughout trajectory planning process – Sufficient fuel for re‐entry – Reserve for additional maneuvers if required 19

Risks & Risk Mitigation Cont. • Risk: Modeling uncertainties – Maneuver plan verses maneuver performance – Desired impact location verses actual impact location – Orbit decay • Mitigation: Uncertainties in impact location will be analyzed in a Monte Carlo analysis – Monte Carlo analysis will vary maneuver performance for each maneuver as well as propagation properties – Bounds debris impact ellipse • Mitigation: Planning on performing a calibration burn to test the engines, ensuring that: – The engines fire as commanded – Allows for the validation of the modeling of maneuver plan and adjust as necessary – Verifies spacecraft attitude control system performance 20

Risk Mitigation Cont. • Risk: The possible loss of attitude control authority as the altitude is decreased • Mitigation: The control torques can be assessed as the altitude is lowered and a minimum altitude for positive control can be estimated based on the max torque available from the wheels • Risk: The ability to contact the spacecraft as the altitude decreases and contact durations become shorter • Mitigation: Impact location has also been chosen so that if the actual impact trajectory is long or short the debris will still be within the impact parameters 21

Addressing NASA‐STD 8719.14 • Atmospheric Skip – Req 56580 – The final maneuver lowers periapsis altitude into the Earth’s atmosphere • The design will be verified in a Monte Carlo analysis, with perturbed maneuvers and various atmospheric conditions • Impact Area – Req 56627 – 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, 50 km from continental U.S., U.S territories, or Antarctica • The design chooses an impact location in the center in the potential impact zone • Potential impact zone meets or exceeds all distance requirements – Req 56628 – For controlled reentries, the product of the probability of failure of the reentry burn and the risk of human casualty assuming uncontrolled reentry shall not exceed 0.0001 • Further analysis required, but related to the distance requirement 22

Summary • GeoEye has developed a prudent plan for the de‐orbit of OV‐3 with ample safeguards and verification • Risks are clearly identified and mitigated • NOAA’s assistance requested to ensure GeoEye notifies and coordinates with all appropriate agencies • GeoEye is ready to execute upon USG approval 23


Document Created: 2010-11-30 14:53:56
Document Modified: 2010-11-30 14:53:56
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