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NASA Future X Homepage
http://rlv.msfc.nasa.gov/stpweb/futurex/futurexhome.html
Boeing: Future X Homepage
http://www.boeing.com/defense-space/space/futurex/index.html

X-38
Update: On April 29, 2002, NASA announced the cancellation of the X-38 program due to budget pressures associated with the international space station. The X-38 was two years short of completing its flight test phase.
Engineers at NASA's Dryden Flight Research Center, Edwards, Calif., and the Johnson Space Center, (JSC) Houston, Texas, were flight-testing the X-38, a prototype spacecraft that could have become the first new human spacecraft built in the past two decades that travels to and from orbit. The vehicle was being developed at a fraction of the cost of past human space vehicles. The goal was to take advantage of available equipment, and already developed technology for as much as 80 percent of the spacecraft's design.
Using available technology and off-the-shelf equipment significantly reduces cost. The original estimates to build a capsule-type crew return vehicle (CRV) were more than $2 billion in total development cost. According to NASA project officials, the X-38 concept and four operational vehicles will to be built for approximately one quarter of the original $2 billion cost.

Current Status
Full-scale, unpiloted "captive carry" flight tests began at Dryden in July 1997 in which the vehicle remained attached to the NASA B-52 aircraft. Unpiloted free-flight drop tests from the B-52 began in March 1998.
Project Goals
The immediate goal of the innovative X-38 project, was to develop the technology for a prototype emergency CRV, or lifeboat, for the ISS. The project also intended to develop a crew return vehicle design that could be modified for other uses, such as a possible joint U.S. and international human spacecraft that could be launched on the French Ariane 5 booster.
In the early years of the International Space Station, a Russian Soyuz spacecraft was be attached to the station as a CRV. But, as the size of the crew aboard the station increases, a return vehicle that can accommodate up to six passengers would be needed. The X-38 design used a lifting body concept originally developed by the Air Force's X-24A project in the mid-1970's. After the deorbit engine module is jettisoned, the X-38 would glide from orbit unpowered like the Space Shuttle and then use a steerable, parafoil parachute, a technology recently developed by the Army, for its final descent to landing. Its landing gear would consist of skids rather than wheels.


Technology
Off-the-shelf technology doesn't mean it is old technology. Many of the technologies used in the X-38 had never before been applied to a human spacecraft.
The X-38 flight computer is commercial equipment that is currently used in aircraft, and the flight software operating system is a commercial system already in use in many aerospace applications. The video equipment on the atmospheric vehicles is existing equipment, some of which has already flown on the Space Shuttle for other NASA experiments. The electromechanical actuators that are used on the X-38 come from a previous joint NASA, Air Force, and Navy research and development project.
An existing special coating developed by NASA was to be used on the X-38 thermal tiles to make them more durable than the tiles used on the Space Shuttle. The X-38's primary navigational equipment, the Inertial Navigation System/Global Positioning System, is a unit already in use on Navy fighters.

Future Plans
Although the design could one day be modified for other uses such as a crew transport vehicle, the X-38 would strictly be used as a CRV. It was baselined with only enough life support supplies to last about nine hours flying free of the space station in orbit. The spacecraft's landing would be totally automated, although the crew would be able to switch to backup systems, control the orientation in orbit, pick a deorbit site, and steer the parafoil, if necessary. The X-38 CRV had a nitrogen gas-fueled attitude control system and used a bank of batteries for power. The spacecraft was to be 28.5 feet long, 14.5 feet wide, and weigh about 16,000 pounds.

X-38 three view
An, in-house development study of the X-38 concept began at JSC in early 1995. In the summer of 1995, early flight tests were conducted of the parafoil concept by dropping platforms with a parafoil from an aircraft at the Army's Yuma Proving Ground, Yuma, Arizona. In early 1996 a contract was awarded to Scaled Composites, Inc., of Mojave, Calif. to build three full-scale atmospheric test airframes. The first vehicle airframe was delivered to JSC in September 1996, where it was outfitted with avionics, computer systems, and other hardware in preparation for the flight tests at Dryden. A second vehicle was delivered to JSC in December 1996.

Team Approach
Some 200 people were working on the project at Johnson, Dryden, and the Langley Research Center in Hampton, Va. This was the first time a prototype vehicle has been built-up in-house at JSC, rather than by a contractor; an approach that has many advantages. By building up the vehicles in-house, engineers had a better understanding of the problems contractors experience when they build vehicles for NASA. JSC's X-38 team will have a detailed set of requirements for the contractor to use to construct the CRVs for the ISS. This type of hands-on work was done by the National Advisory Committee on Aeronautics (NACA), NASA's predecessor, before the space age began. Dryden conducted model flights in 1995. The 1/6 scale-model of the CRV spacecraft using a parafoil parachute system was flown 13 times. The results showed that the vehicle had good flight control characteristics and also demonstrated good slideout characteristics
Resources
Project's Cancellation Irks NASA, by Mark Carreau, Houston Chronicle, June 9, 2002

X-39
As of early 1999, the X-39 designator is apparenty unassigned, but it is reported to be reserved for use by the Air Force Research Laboratory. The designation may be intended for subscale unmanned demonstrators planned under the Future Aircraft Technology Enhancements (FATE) program.
FATE develops revolutionary technologies that will become the foundation for next generation warfighters. It will be these new systems that will provide the US with air and space superiority into the 21st century. Examples of FATE technologies include affordable low-observable data systems, active aeroelastic wing, robust composite sandwich structures, advanced compact inlets, photonic vehicle management systems, self-adaptive flight controls and electric actuation. Each of the major airframers has performed a long-range study on next-generation aircraft.
A subset of the national Fixed Wing Vehicle (FWV) Program, FATE was structured with three phases:
FATE I, Phase I: Define a set of aircraft technologies that must be flight test validated in a new air vehicle to meet FWV Phase I program goals for a fighter attack class of aircraft, including both inhabited and uninhabited aircraft.
FATE I, Phase II: Develop preliminary vehicle design concepts, a demonstrator system, and demonstration plans.
FATE II: Develop, build and flight-test a demonstrator vehicle to achieve program goals.
FATE I, Phase I was used as a jump start for the Unmanned Combat Air Vehicle Advanced Technology Demonstration [UCAV ATD] that will replace the FATE activity.

Sources and Resources
Unmanned Combat Air Vehicle
http://www.fas.org/man/dod-101/sys/ac/ucav.htm
"X-directory" by Guy Norris and Graham Warwick, Flight International January 6-12, 1999
FATE - Block 1 - Phase 1 Final Report Boeing (St. Louis) Study
http://www.fas.org/man/dod-101/sys/ac/ucav.htm
FATE - Block 1 - Phase 1 Final Report Lockheed-Martin Study
FATE 1 Report
http://www.fas.org/man/dod-101/sys/ac/docs/fatereport/index.htm
FATE 1 Ground Control Station Requirements Study
http://www.fas.org/man/dod-101/sys/ac/docs/gsnotes/index.htm
FWV Technology Matrix [XLS file]
http://www.fas.org/man/dod-101/sys/ac/docs/fwv_tech_matrix.xls
Future Aircraft Technology Enhancements
http://www.fas.org/man/dod-101/sys/ac/docs/fwv_tech_matrix.xls

Military Spaceplane
X-40 Space Maneuver Vehicle
Integrated Tech Testbed
Air Force interest in military spaceplanes 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 Aerospaceplane 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 airbreathing 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 spaceplane.
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 ad***ion, 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 Spaceplane (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 *****pport 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 *****stain 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, ad***ional effort may be initiated prior to the conclusion of the testbed model design. Offerors will be requested *****bmit 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 humi***y 30 gms/m3 45 gms/m3
Upper level winds 95th percentile all shear con***ions
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 Maneuver Vehicle (SMV)
The Air Force Research Laboratory's Space Maneuver 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 Maneuver 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 maneuvering
The Space Maneuver Vehicle Program is directed by the Air Force Research Laboratory's Military Spaceplane 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 ad***ional Air Force funding.
The program is currently conducting ground and flight tests of a 22-foot-long, 2,500-pound, graphite-epoxy and aluminum vehicle. The cost of this vehicle is approximately $1 million for fabrication and construction. In ad***ion, 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 Maneuver Vehicle completed a successful autonomous approach and landing on its first flight teston 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 maneuver 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.

The structural test article program is proving out and failure-testing composite building materials needed for the spaceplane development. A full-scale vehicle center fuselage and wing carry-through box is being built and will be tested to evaluate the composite materials.
Future phases will depend on Air Force guidance and availability of funds. Subsequent phases are currently being planned, but are not funded. They involve initial capability technology demonstrations leading to expanded operations. If the technology program is successful, a full operational capability would eventually be fielded.
Resources
Statement of Operational Objectives
Systems Requirements Document
MILITARY SPACEPLANE INTEGRATED TECHNOLOGY TESTBED (MSPITT) Commerce Business Daily: February 21, 1997
Briefing For Industry (BFI)
MSP ITT BFI QUESTIONS AND ANSWERS 11 MARCH 97
Launch on Demand Impact [LODI] Study - June 1998
The Need for a Dedicated Space Vehicle for Defensive Counterspace Operations David D. Thompson; Edward F. Greer (Faculty Advisor) Air Command and Staff College 1998 -- This vehicle should be ground-stationed, reusable, and prepared to launch into earth orbit in time of heightened tensions or war to carry out the defensive counterspace mission.
Man's Place in Spaceplane Flight Operations: ****pit, Cargo Bay, or Control Room? David M. Tobin; Mikael S. Beno (Faculty Advisor) Air Command and Staff College 1998 -- The proper place for humans in military Spaceplane flight operations is always in the control room, sometimes in the cargo bay, but possibly never in a tra***ional ****pit environment.
Access to Space: Routine, Responsive and Flexible: Implications for an Expe***ionary Force Dewey Parker; Edward F. Greer (Faculty Advisor) Air Command and Staff College 1999 -- The near-future advent of Reusable Launch Vehicles and their implications for an Expe***ionary Air Force as an illustration of how future Joint Force Commanders may effectively bring aerospace power to bear in the battlespace as a combined, synergistic whole.
Other Sources
Phillips Laboratory Contracting
NASA's RLV Technology Program
Aerospike Nozzle Engines
Spacecast 2020 - Spacelift: Suborbital, Earth to Orbit and On-Orbit
Air Force 2025 Spacelift 2025 The Supporting Pillar for Space Superiority
Air Force 2025 A Hypersonic Attack Platform: The S3 Concept
Air Force 2025 Space Operations: Through The Looking Glass (Global Area Strike System)
X-Prize Society sponsors a competitive prize rewarding advancement in low-cost human spaceflight for the public. The X PRIZE will stimulate the development of commercial space tourism by awarding a US $10,000,000 cash purse to the first private team to build and fly a reusable spaceship capable of carrying three individuals on a sub-orbital flight.
Advent Launch Services Space Flight Booster Society
Black Horse is a proposed design for a single stage to orbit, reusable launch vehicle. The primary investigator for the Black Horse was Mitchell Burnside Clapp.
Eclipse - Kelly Space & Technology
Delta Clipper
Kistler Reusable Rocketships
Pioneer Rocketplane - a new company dedicated to revolutionizing aviation and space launch.
ROTON - HMX, Inc.
SKYLON - Reaction Engines Ltd. addresses the technical deficiencies encountered in the original HOTOL vehicle
Some other novel launchers
Scorpius - Microcosm, Inc.
Pac Astro's PA-X
GreenSpace and other projects of William Mook Jr.
News
Phillips Lab, Boeing roll out Space Maneuver Vehicle Released: Sep 3, 1997 - The Space Maneuver Vehicle Program ties into another larger program called the Military Spaceplane Program.
Microcosm, Inc. Scorpius MINIMUM COST DESIGN EXPENDABLE LAUNCH VEHICLE TECHNOLOGY - January 26, 1998
X-33 Space plane ventures closerBy 1st Lt. Chris Hemrick Air Force Flight Test Center Public Affairs Leading Edge February '98
X-33 PROGRESS 03-Nov-97 THE REPLACEMENT FOR THE U-S SPACE SHUTTLE HAS CLEARED A MAJOR DESIGN HURDLE

Resources
Statement of Operational Objectives
http://www.fas.org/spp/military/program/launch/msp/soo.htm
Systems Requirements Document
http://www.fas.org/spp/military/program/launch/msp/soo.htm
MILITARY SPACEPLANE INTEGRATED TECHNOLOGY
TESTBED (MSPITT) Commerce Business Daily: February 21, 1997
http://www.fas.org/spp/military/program/launch/msp/soo.htm
Briefing For Industry (BFI)
http://www.fas.org/spp/military/program/launch/msp/soo.htm
MSP ITT BFI QUESTIONS AND ANSWERS 11 MARCH 97
http://www.fas.org/spp/military/program/launch/msp/soo.htm
Launch on Demand Impact [LODI] Study - June 1998
http://www.fas.org/spp/military/program/launch/msp/soo.htm
The Need for a Dedicated Space Vehicle for Defensive
Counterspace Operations David D. Thompson; Edward F. Greer (Faculty Advisor) Air Command and Staff College 1998 -- This vehicle should be ground-stationed, reusable, and prepared to launch into earth orbit in time of heightened tensions or war to carry out the defensive counterspace mission.
http://www.fas.org/spp/military/program/launch/98-280.htm
Man's Place in Spaceplane Flight Operations: ****pit, Cargo Bay, or Control Room? David M. Tobin; Mikael S. Beno (Faculty Advisor) Air Command and Staff College 1998 -- The proper place for humans in military Spaceplane flight operations is always in the control room, sometimes in the cargo bay, but possibly never in a tra***ional ****pit environment.
http://www.fas.org/spp/military/program/launch/98-280.htm
Access to Space: Routine, Responsive and Flexible: Implications for an Expe***ionary Force Dewey Parker; Edward F. Greer (Faculty Advisor) Air Command and Staff College 1999 -- The near-future advent of Reusable Launch Vehicles and their implications for an Expe***ionary Air Force as an illustration of how future Joint Force Commanders may effectively bring aerospace power to bear in the battlespace as a combined, synergistic whole.
http://www.fas.org/spp/military/program/launch/99-154.htm
Other Sources
Phillips Laboratory Contracting
http://www.fas.org/spp/military/program/launch/99-154.htm
NASA's RLV Technology Program
http://www.fas.org/spp/military/program/launch/99-154.htm
Aerospike Nozzle Engines
http://paris.lerc.nasa.gov/kdavidian/aerospike.html
Spacecast 2020 - Spacelift: Suborbital, Earth to Orbit and On-Orbit
http://www.fas.org/spp/military/docops/usaf/2020/app-h.htm
Air Force 2025 Spacelift 2025 The Supporting Pillar for Space Superiority
http://www.fas.org/spp/military/docops/usaf/2025/v2c5/v2c5-1.htm
Air Force 2025 A Hypersonic Attack Platform: The S3 Concept
http://www.fas.org/spp/military/docops/usaf/2025/v3c12/v3c12-1.htm
Air Force 2025 Space Operations: Through The Looking Glass (Global Area Strike System)
http://www.fas.org/spp/military/docops/usaf/2025/v3c14/v3c14-1.htm
X-Prize Society sponsors a competitive prize rewarding
advancement in low-cost human spaceflight for the public. The X PRIZE will stimulate the development of commercial space tourism by awarding a US $10,000,000 cash purse to the first private team to build and fly a reusable spaceship capable of carrying three individuals on a sub-orbital flight.
http://www.xprize.org/
Advent Launch Services Space Flight Booster Society
http://www.phoenix.net/~advent/
Black Horse is a proposed design for a single stage to orbit, reusable launch vehicle. The primary investigator for the Black
Horse was Mitchell Burnside Clapp.
http://www.im.lcs.mit.edu/bh/index.html
Eclipse - Kelly Space & Technology
http://www.kellyspace.com/
Delta Clipper
http://gargravarr.cc.utexas.edu/ssrt/
Kistler Reusable Rocketships
http://www.isso.org/Industry/Kistler/home.html
Pioneer Rocketplane - a new company dedicated to
revolutionizing aviation and space launch.
http://www.rocketplane.com/
ROTON - HMX, Inc.
http://www.hmx.com/
SKYLON - Reaction Engines Ltd. addresses the technical
http://www.im.lcs.mit.edu/~magnus/mirror/skylon/
deficiencies encountered in the original HOTOL vehicle
Some other novel launchers
Scorpius - Microcosm, Inc.
http://www.smad.com/home_scorpius.htm
Pac Astro's PA-X
http://www.isso.org/Industry/AeroAstro/AA-Projects.html#2.6
GreenSpace and other projects of William Mook Jr.
http://s1.ganet.net/~wm0/
News
Phillips Lab, Boeing roll out Space Maneuver Vehicle Released: Sep 3, 1997 - The Space Maneuver Vehicle Program ties into another larger program called the Military Spaceplane Program.
http://www.fas.org/spp/military/program/launch/n19970903_971093.html
Microcosm, Inc. Scorpius MINIMUM COST DESIGN EXPENDABLE LAUNCH VEHICLE TECHNOLOGY - January 26, 1998
http://www.fas.org/spp/military/program/launch/980126-cbd.htm
X-33 Space plane ventures closerBy 1st Lt. Chris Hemrick Air Force Flight Test Center Public Affairs Leading Edge February '98
http://www.fas.org/spp/military/program/launch/x33space.htm
X-33 PROGRESS 03-Nov-97 THE REPLACEMENT FOR THE U-S SPACE SHUTTLE HAS CLEARED A MAJOR DESIGN HURDLE
http://www.fas.org/spp/military/program/launch/x-33_progress.htm

X-41 Common Aero Vehicle (CAV)
The X-41 involves an experimental maneuverable re-entry vehicle carrying a variety of payloads through a suborbital trajectory, and re-entering and dispersing the payload in the atmosphere.
The Common Aero Vehicle (CAV) program is slated for a flight demonstration in FY2003. CAV will provide both an expendable and future reusable Military Space Plane [MSP] system architecture with the ability to deploy multiple payload types from and through space to a terrestrial target. A CAV will be able to achieve high terminal accuracy, extended cross range and be highly maneuverable in a low cost expendable or single use package supporting multiple military mission areas.
Sources and Methods
"X-directory" by Guy Norris and Graham Warwick, Flight International January 6-12, 1999
Broad Agency Announcement 98-01 9 Jan 98 Air Force Research Laboratory (AFRL), Space Vehicles Directorate (VS)
http://www.fas.org/spp/military/program/launch/baa9801.htm

X-42 Pop-Up Upper Stage
The X-42 is an experimental expendable liquid rocket motor upper stage designed to boost 2000-4000lb payloads into orbit.
Pop-Up Upper Stages can expand the utility of advanced military spacecraft, allowing for wider ranges of payload deployment. This project includes concepts on technologies which will improve pop-up upperstage technologies and/or stages themselves. The Orbit Transfer Propulsion AT DTO will demonstrate individual orbit transfer propulsion capabilities that significantly enhance low-cost, high-performance access to space via revolutionary propulsion techniques with improved designs, combustion and mixing technologies, and material advancements; and will develop and demonstrate chemical propulsion systems for military, civil, and commercial orbit transfer applications. Future orbit transfer systems will require advanced materials, low-cost power processing developments, and increased thruster efficiency in order to maintain the US global presence capability through enhanced strategic agility.
Specific demonstrated capabilities for chemical orbit transfer systems include an increased payload capability of 10% in FY00 and 20% in FY05. FY00 chemical/solar thermal orbit transfer propulsion demonstrations will achieve specific improvements of +10% Isp, and +15% mass fraction.
Milestones for orbit transfer propulsion include chemical thrust chamber assembly proof testing and hardware completion in FY97 for integration into the FY00 chemical upper-stage/orbit-transfer demonstration
Sources and Methods
"X-directory" by Guy Norris and Graham Warwick, Flight International January 6-12, 1999
Broad Agency Announcement 98-01 9 Jan 98 Air Force Research Laboratory (AFRL), Space Vehicles Directorate (VS)
1997 Space Platforms DTOs

Sources and Methods
"X-directory" by Guy Norris and Graham Warwick, Flight International January 6-12, 1999
Broad Agency Announcement 98-01 9 Jan 98 Air Force
http://www.fas.org/spp/military/program/launch/baa9801.htm
Research Laboratory (AFRL), Space Vehicles Directorate (VS)
1997 Space Platforms DTOs
http://www.fas.org/spp/military/docops/defense/97_dtos/dtap_dtos/sp_dto.htm#SP.11.06