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【空軍戰機】『每日軍事武器鑑賞』－ X-40A 無人駕駛太空飛機

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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 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 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 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.

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克里斯Chris

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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.

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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.

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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

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克里斯Chris

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發表於 07-5-22 17:52:06 |只看該作者大字中字小字正體化简体化載入全部圖片

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 additional 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 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 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.

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(文章來自:無人機動飛行載具)

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克里斯Chris

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發表於 07-5-22 17:53:48 |只看該作者大字中字小字正體化简体化載入全部圖片

Boeing X-40
aus Wikipedia, der freien Enzyklopädie

Wechseln zu: Navigation, Suche

Die Boeing X-40 Space Maneuver Vehicle war Teil des X-37 Projekts zur Entwicklung eines wiederverwendbaren Raumfahrzeugs. 2001 wurden an einem Modell mit 85% Originalgröße die Flugeigenschaften des eigentümlichen Flugzeugs mit breitem Rumpf und kleinen Flügeln getestet. Bei diesem Test wurde auch das Leitsystem von Honeywell erprobt. Am 14. März 2001 fand die erste erfolgreiche Landung einer X-40, nach dem Abwurf aus einem Boeing-Vertol CH-47, in Kalifornien statt.

KenngrößeDatenBaujahr(e)ab 2001HerstellerBoeingSpannweite3,5 mLänge6,5 mHöhe2,3 mBesatzung0Höchstgeschwindigkeit480 km/h

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克里斯Chris

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X-40

　　X-40A 是波音公司在上個世紀 90 年代中期研製一種無人航天飛行器，最早是作為美國空軍航天機動飛行器（SMV）項目的 90% 縮尺比例原型機，但實際上基本是作為 X-37 的亞音速空氣動力驗證機來使用。X-40A 只進行過 1 次 SMV試驗，而參與 X-37 項目投放的試驗則有 7 次之多。

　　X-40A 長 6.7 米，高 2.19 米，翼展 3.50 米，重 1.13 噸，機身採用碳纖維環氧樹脂和鋁製造，將依靠運載火箭發射升空。因為 X-40A 體積較小，它最長可以在軌道中運行 1 年時間。X-40 的發射準備時間只要數天，而目前的太空船和不可回收火箭的發射都需要進行數周的準備。一旦進入軌道，X-40 就能馬上開始工作。任務完成後，X-40 依靠全球定位系統 GPS 返回大氣層，再通過自動著陸系統安全降落在地面跑道上。X-40A 是無動力的，據稱另外一種具有動力的 X-40B 也在秘密研製中。