Military
Space Plane
Air Force interest in military space planes stretches back nearly 40 years. This has taken the form of science and technology development, design and mission studies, and engineering development programs. Examples of these activities include: the first Aerospace plane program and Dyna-Soar/X-20 program (late 1950s-early 1960s); X-15 hypersonic and X-24 lifting body flight test programs (late 1950s through early 1970s); Advanced Military Space Flight Capability (AMSC), Transatmospheric Vehicle (TAV), and Military Aerospace Vehicle (MAV) concept and mission studies (early 1980s); the Copper Canyon air breathing single-stage-to-orbit (SSTO) feasibility assessment and the National Aerospace Plane (NASP) program (1984-1992); SCIENCE DAWN, SCIENCE REALM, and HAVE REGION rocket-powered SSTO feasibility assessments and technology demonstration programs (late 1980s); and, most recently, the Ballistic Missile Defense Organization's Single-Stage Rocket Technology program that built the Delta Clipper-Experimental (DC-X) experimental reusable space plane.
Industry sources are being sought to develop critical technologies for future military spaceplanes using ground based advanced technology demonstrations. The first step is envisioned to include a streamlined acquisition that develops, integrates and tests these technologies in an Integrated Technology Testbed (ITT). Due to constrained budgets, the Air Force is seeking innovative, "out of the box", industry feedback and guidance to: 1) develop and demonstrate key military spaceplane technologies, 2) ensure competitive industry military spaceplane concepts are supported via critical technology demonstrations, and 3) ensure a viable, competitive military spaceplane industrial base is retained now and in the future.
The primary objective of the ITT is to develop the MSP Mark I concept design and hardware with direct scaleability: directly scaleable weights, margins, loads, design, fabrication methods and testing approaches; and traceability: technology and general design similarity, to a full-scale Mark II-IV system. The ITT is intended to demonstrate the technologies necessary to achieve systems integration within the mass fraction constraints of Single Stage to Orbit (SSTO) vehicles. In addition, the ITT will meet the military operational requirements outlined in the MSP SRD. The ITT is an unmanned ground demonstration. The Mark I demonstrator is also envisioned to be unmanned.
The Military Space plane (MSP) ITT ground demonstration consists of an effort to develop a computer testbed model. It may also include options for multiple technology, component and subsystem hardware demonstrations to support and enable the acquisition and deployment of MSP systems early in the next century. Although the ITT is not a flight demonstrator, it is anticipated that critical ground Advanced Technology Demonstrator (ATD) components and subsystems shall be designed, fabricated and tested with a total systems and flight focus to demonstrate the potential for military "aircraft like" operations and support functions. The latter point refers to eventual systems that 1) can be recovered and turned around for another mission in several hours or less on a routine basis, 2) require minimal ground and flight crew to conduct routine operations and maintenance , 3) are durable enough to sustain a mission design life of hundreds of missions, 4) are designed for ease of maintenance and repair based on military aircraft reliability, maintainability, supportability and availability (RMS&A) standards including the use of line replaceable units to the maximum extent possible, and 5) can be operated and maintained by military personnel receiving normal levels of technical training. The ITT effort is envisioned to culminate with a vigorous integrated test program that demonstrates how specific components and subsystems are directly traceable and scaleable to MSP system requirements and meet or exceed these operational standards.
The testbed itself shall be a computer sizing model of the Military Spaceplane. Input parameters include mission requirements and all of the critical component, subsystem and system technical criteria. Output are the critical design features, size, physical layout, and performance of the resulting vehicle. The computer model shall be capable of modeling the technology componenta, subsystems and systems demonstrated characteristics and the resulting effect(s) on the Military Spaceplane vehicle concept design. Although the ITT is required to show analytical component and subsystem scaleability to SSTO, the contractor may also show scaleability and traceability to alternative MSP configurations. Those alternatives may include two stage to orbit (TSTO) configurations. The ITT is using SSTO as a technology stretch goal in the initial ground demonstrations. However, a future Military Spaceplane can use either single or multiple stages.
The contract structure for ITT is anticipated to be Cost Reimbursement type contracts with possible multiple options and a total funding of approximately $125-150M. Due to initial funding limitations, the minimum effort for the contract is anticipated to consist of a broad conceptual military spaceplane design supported by a computer testbed model. However, should funding become available, additional effort may be initiated prior to the conclusion of the testbed model design. Offerors will be requested to submit a series of alternatives for delivery of major technology components and subsystems as well as an alternative for subsystem/system integration and test.
Upon direction of the Government through exercise of the option(s) the contractor shall design, fabricate, analyze, and test Ground Test Articles (GTAs), and provide a risk reduction program for all critical technology components, subsystems and subsystems assembly. The contractor will prepare options for an ITT GTA designs which satisfy the technical objectives of this SOO, including both scaleability and traceability to the Mark I and Mark II-IV vehicles. These design shall be presented to the Government at a System Requirements Review (SRR). The contractor shall use available technologies and innovative concepts in the designs, manufacturing processes, assembly and integration process, and ground test. Designs shall focus on operational simplicity and minimizing vehicle processing requirements. The contractor shall provide the detailed layout and systems engineering analysis required to demonstrate the feasibility and performance of the Mark I vehicle as well as scaleability and traceability to the Mark II-IV vehicles. The low cost reusable upper stage (i.e., mini-spaceplane) is envisioned to be an integral part of an overall operational MSP system.
The contractor shall use the ITT to implement the initial risk reduction program that mitigates risks critical to developing both the Mark I and Mark II-IV MSP configurations. The ITT shall mitigate risks critical to engineering, operability, technology, reliability, safety, or schedule and any subsequent risk reduction program deemed necessary. The program may include early component fabrication, detailed vehicle integration planning or prudent factory and ground/flight testing to reduce risks. The Technology levels will be frozen at three points in the Military Spaceplane Program (MSP): At the ITT contract award for the Ground Demonstrator, at contract award for any future Flight Demonstrator, and at contract award for an orbital system EMD.
Since the ITT is not a propulsion demonstration/integration effort there are two parallel propulsion efforts. One in NASA for the X-33 aerospike, and one in the AF for the Integrated Powerhead Demonstration ( IPD). It is anticipated that the Mark I demonstrator would use an existing engine. Propulsion modifications and integration will be addressed in the offerors concept design but limited funding probably precludes any new engine development. The contractor should evaluate the use of the Integrated Powerhead Demonstration (IPD) XLR-13X engine as a risk reduction step being done in parallel and as a baseline engine for MSP. LOX/LH2 offers an excellent propellant combination for future Military Spaceplanes. Nearer term demonstrators, however, may be asked to use alternative propellants with superior operability characteristics.
MAXIMUM PERFORMANCE MISSION SETS
Maximum Performance Missions Sets are system defining and encompass the four missions and the Design Reference Missions. Instead of giving a threshold and objective for each mission requirement, missions sets are defined. Each mission set will define a point solution and provide visibility into the sensitivities of the requirements from the thresholds (Mark I) to the objective (Mark IV). If takeoff and landing bases are constrained to the U.S. (including Alaska and Hawaii), this will reduce stated pop-up payloads by at least half.
Mark I (Demonstrator or ACTD non-orbital vehicle that can only pop up)
- Pop-up profile: Approximately Mach 16 at 300 kft at payload separation
- Pop up and deliver 1 to 3 klbs of mission assets (does not include boost stage, aeroshell, guidance or propellant) to any terrestrial destination
- Pop up and deliver 3 to 5 klbs of orbital assets (does not include upperstage) due east to a 100 x 100 NM orbit
- Payload bay size 10' x 5' x 5', weight capacity 10 klbs
Mark II (Orbit capable vehicle)
- Pop up and deliver 7 to 9 klbs of mission assets (does not include boost stage, aeroshell, guidance or propellant) to any terrestrial destination
- Pop up and deliver 15 klbs of orbital assets (does not include upperstage) due east to a 100 x 100 NM orbit
- Launch due east, carrying 4-klb payload, orbit at 100 x 100 NM
- Payload bay size 25' x 12' x 12', weight capacity 20 klbs
Mark III
- Pop up and deliver 14 to 18 klbs of mission assets (does not include boost stage, aeroshell, guidance or propellant) to any terrestrial destination
- Pop up and deliver 25 klbs of orbital assets (does not include upperstage) due east to a 100 x 100 NM orbit
- Launch due east, carrying a 6-klb payload, orbit at 100 x 100 NM and return to base
- Launch polar, carrying 1-klb payload and return to base
- Payload bay size 25' x 12' x 12', weight capacity 40 klbs
Mark IV
- Pop up and deliver 20 to 30 klbs of mission assets (does not include boost stage, aeroshell, guidance or propellant) to any terrestrial destination
- Pop up and deliver 45 klbs of orbital assets (does not include upperstage) due east to a 100 x 100 NM orbit
- Launch due east, carrying a 20-klb payload, orbit at 100 x 100 NM and return to base
- Launch polar, carrying 5-klb payload and return to base
- Payload bay size 45' x 15' x 15', weight capacity 60 klbs
REFERENCE MISSIONS TO MISSION SETS MATRIX
Ref Mission Mark I Mark II Mark III Mark IV
Payload Bay Data 10' x 5' x 25' x 12' x 25' x 12' x 45' x 15' x
5' 12' 12' 15'
10 klbs 20 klbs 40 klbs 60 klbs
DRM 1 (Pop up and 1-3 klb 7 to 9 klb 14 to 18 klb 20 to 30 klb
deliver mission
assets)
DRM 2 (Pop up and 3-5 klb 15 klb 25 klb 45 klb
deliver orbit assets
due east 100 x 100 NM)
DRM 3 (Co-Orbit) N/A 4 klb due 6 klb due east 20 klb due
east 100 x 100 x 100 NM east 100 x 100
100 NM NM
DRM 4 (Recover) N/A TBD TBD TBD
DRM 5 (Polar Once N/A N/A 1 klb 5 klb
Around)
NOTES:
Mission asset weight is a core weight and does not include a boost stage, aeroshell, guidance or propellant.
Orbital asset weight does not include an upperstage.
Requirements Matrix for Mark II, III and IV
(Desired for Mark I)
Requirement Threshold Objective
Sortie Utilization Rates
Peacetime sustained 0.10 sortie/day 0.20 sortie/day
War/exercise sustained (30 days) 0.33 sortie/day 0.50 sortie/day
War/exercise surge (7 days) 0.50 sortie/day 1.00 sortie/day
Turn Times
Emergency war or peace 8 hours 2 hours
MOB peacetime sustained 2 days 1 day
MOB war/exercise sustained (30 days) 18 hours 12 hours
MOB war/exercise surge (7 days) 12 hours 8 hours
DOL peacetime sustained 3 days 1 day
DOL war/exercise sustained (30 days) 24 hours 12 hours
DOL war/exercise surge (7 days) 18 hours 8 hours
System Availability
Mission capable rate 80 percent 95 percent
Flight and Ground Environments
Visibility 0 ft 0 ft
Ceiling 0 ft 0 ft
Crosswind component 25 knots 35 knots
Total wind 40 knots 50 knots
Icing light rime icing moderate rime icing
Absolute humidity 30 gms/m3 45 gms/m3
Upper level winds 95th percentile all shear conditions
shear
Outside temperature -20 to 100F -45 to 120F
Precipitation light moderate
Space Environment
Radiation level TBD TBD
Flight Safety
Risk to friendly population < 1 x 10-6 < 1 x 10-7
Flight Segment loss < 1 loss /2000 < 1 loss/5000 sorties
sorties
Reliability 0.9995 0.9998
Cross Range
Unrestricted pop-up cross range 600 NM 1200 NM
CONUS pop-up cross range 400 NM 600 NM
Orbital cross range 1200 NM 2400 NM
"Pop-up" Range
CONUS pop-up range 1600 NM 1200 NM
Ferry range minimum 2000 NM worldwide
On-orbit Maneuver
Excess V (at expense of payload) 300 fps 600 fps
Pointing accuracy 15 milliradians 10 milliradians
Mission Duration
On-orbit time 24 hours 72 hours
Emergency extension on-orbit 12 hours 24 hours
Orbital Impact
Survival impact object size 0.1-cm diameter 1-cm diameter
Survival impact object mass TBD TBD
Survival impact velocity TBD TBD
Alert Hold
Hold Mission Capable 15 days 30 days
Mission Capable to Alert 2-hour 4 hours 2 hours
Status
Hold Alert 2-hour Status 3 days 7 days
Alert 2-hour to Alert 15-minute 1 hour 45 minutes 30 minutes
Status
Hold Alert 15-minute Status 12 hours 24 hours
Alert 15 Minute to Launch 15 minutes 5 minutes
Design Life
Primary Structure 250 sorties 500 sorties
Time between major overhauls 100 sorties 250 sorties
Engine life 100 sorties 250 sorties
Time between engine overhauls 50 sorties 100 sorties
Subsystem life 100 sorties 250 sorties
Take-off and Landing
Runway size 10,000 ft x 150 ft 8000 ft x 150 ft
Runway load bearing S65 S45
Vertical landing accuracy 50 ft 25 ft
Payload Container
Container change-out 1 hour 30 minutes
Crew Station Environment (if rqd)
Life support duration 24 hours 72 hours
Emergency extension on-orbit 12 hours 24 hours
Crew Escape (if rqd)
Escape capability subsonic full envelope
Maintenance and Support
Maintenance work hours/sortie 100 hours 50 hours
R&R engine 8 hours 4 hours
X-40 Space Manoeuvre Vehicle (SMV)
The Air Force Research Laboratory's Space Manoeuvre Vehicle (SMV) is a small, powered space vehicle technology demonstrator. An eventual operational version could function as the second stage-to-orbit vehicle as well as a reusable satellite with a variety of available payloads. SMV could perform missions such as:- Tactical reconnaissance
- Filling gaps in satellite constellations
- Rapid deployment of Space Manoeuvre Vehicle constellations
- Identification and surveillance of space objects
- Space asset escorting
An SMV is envisioned to dwell on-orbit for up to one year. Its small size and ability to shift orbital inclination and altitude would allow repositioning for tactical advantage or geographic sensor coverage. Interchangeable SMV payloads would permit a wide variety of missions. SMV would use low-risk subsystem components and technology for aircraft-like operability and reliability.
An operational SMV might include:
- Up to 1,200 pounds of sensors/payload
- 72-hours or less turnaround time between missions
- Up to 12 month on-orbit mission duration
- Rapid recall from orbit
- Up to 10,000 feet per second on-orbit velocity change for manoeuvring
The Space Manoeuvre Vehicle Program is directed by the Air Force Research Laboratory's Military Space plane Technology Office at Kirtland Air Force Base, New Mexico. A three phase program is planned to provide affordable technology and operations demonstrations. The program is presently funded through Phase I. The schedule for Phases II and III depends on additional Air Force funding.
The program is currently conducting ground and flight tests of a 22-foot-long, 2,500-pound, graphite-epoxy and aluminium vehicle. The cost of this vehicle is approximately $1 million for fabrication and construction. In addition, the government has contributed approximately $5 million to the project. The partnership with the Air Force Research Laboratory's Air Vehicles Directorate and has already accomplished:
- A helicopter release of a 90-percent-scale of the SMV to demonstrate autonomous control and landing capability.
- The design and construction of a full-scale SMV center fuselage and wing carry-through box that successfully passed its structural tests.
The Space Manoeuvre Vehicle completed a successful autonomous approach and landing on its first flight test on 11 August 1998. The unmanned vehicle was dropped from an Army UH-60 Black Hawk helicopter at an altitude of 9,000 feet above the ground, performed a controlled approach and landed successfully on the runway. The total flight time was 1-1/2 minutes. During the initial portion of the its free fall, the manoeuvre vehicle was stabilized by a parachute. After it is released from the parachute, the vehicle accelerated and perform a controlled glide. This glide simulated the final approach and landing phases of such a vehicle returning from orbit. The vehicle, which landed under its own power, used an integrated Navstar Global Positioning Satellite and inertial guidance system to touch down on a hard surface runway. The 90 percent-scale vehicle was built by Boeing Phantom Works, Seal Beach CA, under a partnership between Air Force Research Laboratory Space Vehicles Directorate at Kirtland Air Force Base NM and the Air Vehicles Directorate at Wright-Patterson Air Force Base OH