MS1-A Military Spaceplane System and Space Maneuver Vehicle. Lt Col Ken Verderame Air Force Research Laboratory 27 October 1999

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1 MS1-A Military Spaceplane System and Space Maneuver Vehicle Lt Col Ken Verderame Air Force Research Laboratory 27 October 1999

2 ReentryWorkshop_27Oct99_MS1-AMSP-SMV_KV p 2 MS-1A Military Spaceplane System Architecture Space Operations Vehicle (SOV) Space Maneuver Vehicle (SMV) Modular Insertion Stage (MIS)

3 ReentryWorkshop_27Oct99_MS1-AMSP-SMV_KV p 3 TSTO Military Spaceplane Characteristics Payload to Low Earth Orbit All Inclinations 1 st Stage up to 12,000 lbs to orbit 2 nd Stage lbs to orbit

4 Low Cost / Low Risk Demonstrator Is Affordable Alternative To Large Orbital System Boeing & Lockheed Martin Concepts Reference Orbital MSP Options (10-20 yrs) STS Orbiter Commercial RLV (Unfunded) F-15 Two Stage To Orbit Ops Demonstrator Options (5-10 yrs) COST Propellant: LOX/RP LOX/LH2 LOX/LH2 LOX/LH2 ReentryWorkshop_27Oct99_MS1-AMSP-SMV_KV p 4

5 ReentryWorkshop_27Oct99_MS1-AMSP-SMV_KV p 5 Pop-Up Flight Profile Reduces Military Spaceplane Size & Cost Sub-Orbital Sub-Orbital MSP MSP Capability Capability Orbit-Capable Orbit-Capable MSP MSP Greatly Greatly Enhances Enhances Capability Capability 1 SMV to LEO 3 SMV to all orbits ~Mach 17 Separation Altitude: ~250K ft Q<1 PSF 1 MIS to LEO ~Mach 22 Separation Altitude: ~300K ft Q<1 PSF 25Klb Sat to LEO Launch Landing Launch Landing Downrange 1200NM Downrange 2500NM

6 ReentryWorkshop_27Oct99_MS1-AMSP-SMV_KV p 6 Military Spaceplane Mission Profile PREPARE MISSION SMV ON MSP READY TO LAUNCH SMV ON MSP READY FOR DEPLOYMENT SMV DEPLOYMENT / MSP LANDING CONDUCT OPERATIONS OBJECT IDENTIFICATION SPACE RECCE SMV DEORBIT BURN REENTRY APPROACH & LANDING ON RUNWAY SERVICE VEHICLE & PAYLOAD MSP / SMV REMATED FOR NEXT MISSION

7 ReentryWorkshop_27Oct99_MS1-AMSP-SMV_KV p 7 Space Maneuver Vehicle Characteristics Length 20-25ft Loaded Weight 10-12,000lbs Dry Weight lbs Payload 1200lbs Payload Bay 4ft x 7ft V Ideal 10,500-12,000fps Boeing Concept Orbital Sciences Concept Features On Demand Launch Recallable/Recoverable Short Notice Tasking Landing Gear for Runway Recovery Up to 12 Months on Orbit Multiple Payloads Missions Space Support Force Enhancement Space Surveillance Lockheed-Martin Concept Employment Pop-Up LEO Co-orbit Capability Fly-By of Higher Altitude Satellites Constellation Building Gap Filler Once Around (SR-71)

8 SMV and NASA Future-X NASA Research Announcement 8-22 ~$100M for Pathfinder and experiments $20M congressional add for AF related activities AF Participated in Source Selection Boeing Advanced Technology Vehicle (ATV) Chosen as X-37 Very similar to AF Space Maneuver Vehicle (SMV) Cooperative program between NASA and Boeing At 21 Dec 98 Flag Officer VTC, MGen Paul Promised AFRL would Provide $16.1M S&T Funds to Make X-37 More Like SMV Solar array and power system for longer on-orbit time Sensors and algorithms for rendezvous / proximity ops Improved attitude / pointing system Improved reentry maneuvering potential 98/99 Congressional Add Spend Plan X-37 SMV Dry Weight 5300 lbs 3100 lbs Payload 500 lbs 1200 lbs Velocity Change 6,000 ft/sec 10,500 ft/sec On-Orbit Duration <12 hr * 4-15 mo Design modular integrated Engine low performance high performance $5.0M Future-X X-37 $2.5M Propulsion for SMV/Upper Stage $2.5M Flight Test of X-40A SMV AFRL S&T Investment in Future-X/X $5.0M $5.0M $5.1M $1M * Will Improve With AF Investment ReentryWorkshop_27Oct99_MS1-AMSP-SMV_KV p 8

9 ReentryWorkshop_27Oct99_MS1-AMSP-SMV_KV p 9 Space Maneuver Vehicle Family Tree X-40A Dropped from Helicopter at Holloman AFB, NM 11 Aug 98 Based on Original 7000 lb Gross Weight Boeing Refly TM Design Will be Used During NASA/Boeing X-37 Program Dropped from B-52 X-37 NASA/Boeing Future-X Cooperative Program Similar Outer Mold Line to lb SMV Modular for major component exchange Over 35 experiments designed in AF Participating to Obtain Data for SMV X-40B AF Second Tail Number Prototype SMV More Capable than X-37 SMV Operational Reusable Satellite and Upper Stage Highly Operable lb Vehicle Designed for Launch from ELV or SOV Final Design not Determined Lockheed-Martin Concept Boeing Concept Orbital Sciences Concept

10 ReentryWorkshop_27Oct99_MS1-AMSP-SMV_KV p 10 X-37 and X-40B Tentative Schedule CY 01 X-37 Roll-Out CY 02/3 X-37 Orbital Test Flight CY 02/3 X-40B Roll-Out CY 03/4 X-40B Orbital Test Flights

11 X-37 Program Status Boeing Selection Announcement 8 Dec 98 Cooperative Agreement Negotiations Took Six Months Ownership /progress payments / indemnification AF $16.1M Test team / RTO / test sites Cooperative Agreement Finally Signed 14 Jul 99 Total value (Boeing + NASA + AF) $172.9M Kick-Off Meeting at Seal Beach, CA 4-5 Aug 99 Considerable technical work already accomplished Schedule very compressed due to negotiation time lost Target date for X-37 Shuttle mission late CY02 Issues No firm Shuttle mission yet X-37 overweight (5800 lbs at landing incl 500 lb payload) Weight gain has performance less than 6000 fps V ELV launch as fallback to Shuttle No program funds allocated for actual ELV launch Boeing told no Peacekeepers available (X-37 too heavy for Peacekeeper anyway) Boeing will concentrate on Athena II and Delta II as ELV options ReentryWorkshop_27Oct99_MS1-AMSP-SMV_KV p 11

12 The NASA X-37 is not Designed to Satisfy Air Force Operational Requirements ReentryWorkshop_27Oct99_MS1-AMSP-SMV_KV p 12 NASA X-37 Current X-37 Plans Call For: Off the Shelf AR-2/3 H 2 O 2 /JP Engine A Vehicle Which Addresses Both Earth-to-Orbit (ETO) and On-Orbit Technology Maturation 16 Modularity Features Incorporated for Rapid Technology/Experiment Insertion 35 Embedded Technologies/Experiments for Orbital Flight #1:!Propulsion (2)!Structure & TPS (9)!Avionics (6)!Operations (12)!Planned Experiments (6) 45 Technologies/Experiments Identified for Follow-on Insertion and Testing Air Force SMV Operational SMV Requires: High Performance H 2 O 2 /JP Engine High Responsiveness High Maneuvering Capability Extended On-orbit Duration Survivable CONOPS Hardened Vehicle High Precision GN&C Rapid Automatic Rendezvous and Extended Proximity Ops Capability Greatly Expanded Payload Accommodations High Crossrange SOV Compatibility

13 ReentryWorkshop_27Oct99_MS1-AMSP-SMV_KV p 13 Space Support - Current Tasks (IOC 2008) Satellite Reposition Space Lift

14 Space Support - Future Tasks (Beyond 2008) On-Orbit Refuel Satellite Recovery On-Orbit Servicing ReentryWorkshop_27Oct99_MS1-AMSP-SMV_KV p 14

15 ReentryWorkshop_27Oct99_MS1-AMSP-SMV_KV p 15 X-40A First Flight X-40A SMV Flew at Holloman AFB, NM on 11 August 1998 All Test Objectives Met X-40A Future Part of X-37 Flight Test

16 Neutral Buoyancy Laboratory (NBL) Test May 1999 Full Scale SMV in NBL Tank Shuttle Bay Simulated AF and NASA Missions Using Astronauts in Space Suites Missions Included Payload Change Out and Refueling Characterized by NASA as Extremely Well Planned and Executed Test All Test Objectives Were Met SMV Model Will be Used in Future NBL Tests ReentryWorkshop_27Oct99_MS1-AMSP-SMV_KV p 16

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