US4471926A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Transfer vehicle for use in conjunction with a reusable space shuttle
Assignee: Northrop Grumman Space and Mission Systems Corp
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Filing: 1982-02-22
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Granted: 1984-09-18
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Expires: 2002-02-22
Abstract
Abstract A spacecraft or transfer vehicle for transportation of a payload from a space shuttle parking orbit to a higher operation orbit, wherein the transfer vehicle utilizes housekeeping subsystems integrated into the payload, to avoid unnecessary duplication of these subsystems, for such functions as power supply, guidance, control, and communications. The transfer vehicle disclosed includes a propulsion system with at least one low-thrust bipropellant liquid rocket engine, to provide a "soft" or low-acceleration ascent, and employs two tanking stages, each having four propellant tanks, arranged symmetrically in a circular configuration. The first stage of four tanks is jettisoned during ascent, and the second stage, including the remaining four tanks, the rocket engine, and related supporting structure, is separated from the payload when the operational orbit is reached.
Inventors
- 👤 Robert W. Steel, III
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 14:13
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/14
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
248 words
A spacecraft comprising: a transfer vehicle for transporting a payload from a parking orbit to an operational orbit, said transfer vehicle having front and rear ends, a forward support at said front end including a generally octagonal frame, a central, substantially cylindrical core having forward and aft separable segments, said forward segment being rigidly connected to the aft side of said forward support and said aft segment being releasably secured to said forward cylindrical segment, at least one relatively low-thrust liquid bipropellant rocket engine secured to said forward cylindrical segment, a first tank stage including two diametrically opposed fuel tanks and two diametrically opposed oxidizer tanks supported symmetrically about said engine and rigidly connected to said aft cylindrical segment, a second tank stage including two additional diametrically opposed fuel tanks and two additional diametrically opposed oxidizer tanks supported symmetrically about said engine, spaced between said first-stage tanks, and rigidly connected to said forward cylindrical segment; a payload vehicle releasibly connected to said forward support for separation from said transfer vehicle at said operational orbit, said payload vehicle including an equipment module for providing spacecraft housekeeping functions both for said transfer vehicle during transition from the parking orbit to the operational orbit and for the payload vehicle when in its operational orbit; and said first tank stage is jettisoned after its propellant tanks have been emptied, and the payload vehicle and said housekeeping subsystems are separated from said forward support structure when said transfer vehicle reaches the operational orbit.
Claim 2
Dependent Claim
248 words
A spacecraft comprising: a transfer vehicle for transporting a payload from a parking orbit to an operational orbit, said transfer vehicle having front and rear ends, a forward support at said front end including a generally octagonal frame, a central, substantially cylindrical core having forward and aft separable segments, said forward segment being rigidly connected to the aft side of said forward support and said aft segment being releasably secured to said forward cylindrical segment, at least one relatively low-thrust liquid bipropellant rocket engine secured to said forward cylindrical segment, a first tank stage including two diametrically opposed fuel tanks and two diametrically opposed oxidizer tanks supported symmetrically about said engine and rigidly connected to said aft cylindrical segment, a second tank stage including two additional diametrically opposed fuel tanks and two additional diametrically opposed oxidizer tanks supported symmetrically about said engine, spaced between said first-stage tanks, and rigidly connected to said forward cylindrical segment; a payload vehicle releasibly connected to said forward support for separation from said transfer vehicle at said operational orbit, said payload vehicle including an equipment module for providing spacecraft housekeeping functions both for said transfer vehicle during transition from the parking orbit to the operational orbit and for the payload vehicle when in its operational orbit; and said first tank stage is jettisoned after its propellant tanks have been emptied, and the payload vehicle and said housekeeping subsystems are separated from said forward support structure when said transfer vehicle reaches the operational orbit.
Claim 3
Dependent Claim
70 words
A spacecraft as set forth in claim 1, wherein: said forward support structure further includes a pair of attachments for transferring shear loads, in the plane of said structure, to corresponding supports in a reusable vehicle employed to carry said transfer vehicle and its payload to the parking orbit, and also includes means for supporting the forward ends of said first-stage propellant tanks prior to separation of said first stage.
Claim 4
Dependent Claim
35 words
A spacecraft as set forth in claim 2, and further including means for releasably coupling said transfer vehicle to an aft support cradle located in the reusable vehicle employed for transportation to the parking orbit.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1987-09-18 | 1988-03-19 | 1988-09-18 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-09-18 | 1992-03-19 | 1992-09-18 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-09-18 | 1996-03-19 | 1996-09-18 | $7700.00 | Window Closed / Lapsed |