Patent US4817895A successfully refreshed from Google Patents.
US4817895A
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Aerobraking orbital transfer vehicle
Assignee: National Aeronautics and Space Administration
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Filing: 1987-10-14
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Granted: 1989-04-04
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Expires: 2007-10-14
Abstract
Abstract An aerobraking orbital transfer vehicle which includes an aerobraking device which also serves as a heat shield in the shape of a raked-off elliptic or circular cone with a circular or elliptical base, and with an ellipsoid or other blunt shape nose. The aerobraking device is fitted with a toroid-like skirt and is integral with the support structure of the propulsion system and other systems of the space vehicle. The vehicle is intended to be transported in components to a space station in lower earth orbit where it is assembled for use as a transportation system from low earth orbit to geosynchronous earth orbit and return. Conventional guidance means are included for autonomous flight.
Inventors
- 👤 Carl D. Scott
- 👤 Kornel Nagy
- 👤 Barney B. Roberts
- 👤 Robert C. Ried
- 👤 Kenneth R. Kroll
- 👤 Joe Gamble
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-09 06:20
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/14; B64G1/22; B64G1/52; B64G1/58
Claims Analysis
Total Claims: 19
Claim 1
Independent Claim
168 words
A reusable, spaced-based, aerobraking orbital transfer vehicle, said vehicle including a structure formed of bulkheads and stringers, the external configuration of said structure being in the shape of a raked-off, wide angle cone with a blunted nose and a toroid-like skirt about the base of the cone to form an aerobrake providing drag and lift for said vehicle, the blunted nose reduces the stagnation point heat flux and the windward surface heat flux, the skirt provides a smooth transition from the conical surface to a surface that is more nearly parallel to the wind velocity reducing the heat flux near the trailing edge of the cone, the external surface of the aerobrake being covered with a material that will provide reuseable thermal protection during excursions of the vehicle into the atmosphere, the structure integrally supporting an ascent/descent propulsion system, the tankage therefor and other systems of said vehicle, the thrust vector of the propulsion system being approximately normal to an axis extending through the base of the cone.
Claim 2
Dependent Claim
168 words
A reusable, spaced-based, aerobraking orbital transfer vehicle, said vehicle including a structure formed of bulkheads and stringers, the external configuration of said structure being in the shape of a raked-off, wide angle cone with a blunted nose and a toroid-like skirt about the base of the cone to form an aerobrake providing drag and lift for said vehicle, the blunted nose reduces the stagnation point heat flux and the windward surface heat flux, the skirt provides a smooth transition from the conical surface to a surface that is more nearly parallel to the wind velocity reducing the heat flux near the trailing edge of the cone, the external surface of the aerobrake being covered with a material that will provide reuseable thermal protection during excursions of the vehicle into the atmosphere, the structure integrally supporting an ascent/descent propulsion system, the tankage therefor and other systems of said vehicle, the thrust vector of the propulsion system being approximately normal to an axis extending through the base of the cone.
Claim 3
Dependent Claim
27 words
The aerobraking orbital transfer vehicle as set forth in claim 1 including support structure and attachment means integral with said structure for at least one payload module.
Claim 4
Dependent Claim
22 words
The aerobraking orbital transfer vehicle as set forth in claim 2 in which the payload module is attached aft of the aerobrake.
Claim 5
Dependent Claim
26 words
The aerobraking orbital transfer vehicle opposite the propulsion system in a position so that the thrust vector of the propulsion system is approximately in line therewith.
Claim 6
Dependent Claim
26 words
The aerobraking orbital transfer vehicle opposite the propulsion system in a position so that the thrust vector of the propulsion system is approximately in line therewith.
Claim 7
Dependent Claim
18 words
The aerobraking orbital transfer vehicle as claimed in claim 1 in which said cone is an elliptic cone.
Claim 8
Dependent Claim
18 words
The aerobraking orbital transfer vehicle as claimed in claim 1 in which said cone is a circular cone.
Claim 9
Dependent Claim
18 words
The aerobraking orbital transfer vehicle as claimed in claim 1 in which the blunted nose is an ellipsoid.
Claim 10
Dependent Claim
37 words
The aerobraking orbital transfer vehicle as set forth in claim 1 in which the propulsion system includes at least one rocket engine utilizing hydrogen and oxygen as fuel and the tankage for the hydrogen and the oxygen.
Claim 11
Dependent Claim
23 words
The aerobraking orbital transfer vehicle set forth in claim 8 in which there is a separate tank for the hydrogen required for descent.
Claim 12
Dependent Claim
166 words
A reusable, spaced-based, aerobraking orbital transfer vehicle, said vehicle including a structure formed of bulkheads and stringers, the external configuration of said structure being in the shape of a raked-off, wide angle, cone with a blunted nose and a toroid-like skirt about the base of the cone to form an aerobrake providing drag and lift for said vehicle, the blunted nose reduces the stagnation point head flux and the windward surface heat flux, the skirt provides a smooth transition from the conical surface to a surface that is more nearly parallel to the wind velocity reducing the heat flux near the trailing edge of the cone, the external surface of the aerobrake being covered with a material that will provide reuseable thermal protection during excursions of the vehicle into the atmosphere, the structure integrally supporting an ascent/descent propulsion system, the tankage therefor and other systems of said vehicle, and support structure and attachment means for a payload module positioned aft of and protected by the aerobrake.
Claim 13
Dependent Claim
166 words
A reusable, spaced-based, aerobraking orbital transfer vehicle, said vehicle including a structure formed of bulkheads and stringers, the external configuration of said structure being in the shape of a raked-off, wide angle, cone with a blunted nose and a toroid-like skirt about the base of the cone to form an aerobrake providing drag and lift for said vehicle, the blunted nose reduces the stagnation point head flux and the windward surface heat flux, the skirt provides a smooth transition from the conical surface to a surface that is more nearly parallel to the wind velocity reducing the heat flux near the trailing edge of the cone, the external surface of the aerobrake being covered with a material that will provide reuseable thermal protection during excursions of the vehicle into the atmosphere, the structure integrally supporting an ascent/descent propulsion system, the tankage therefor and other systems of said vehicle, and support structure and attachment means for a payload module positioned aft of and protected by the aerobrake.
Claim 14
Dependent Claim
17 words
The aerobraking orbital transfer vehicle as set forth in claim 10 in which said cone is elliptical.
Claim 15
Dependent Claim
17 words
The aerobraking orbital transfer vehicle as set forth in claim 10 in which said cone is circular.
Claim 16
Dependent Claim
20 words
The aerobraking orbital transfer vehicle as set forth in claim 10 in which the blunted is nose is an ellipsoid.
Claim 17
Dependent Claim
193 words
A reusable, spaced-based, aerobraking orbital transfer vehicle, said vehicle including a structure formed of bulkheads and stringers, the external configuration of said structure being in the shape of an elliptical cone with an angle of approximately 60° raked-off at an angle of approximately 73° with an ellipsoidal nose and a toroid-like skirt about the base of the cone to form an aerobrake providing lift at zero angle of attack with respect to the cone axis, the ellipsoidal nose minimizing the stagnation point heat flux, the skirt providing a smooth transition from the conical surface to a surface that is more nearly parallel to the wind velocity reducing the heat flux near the trailing edge of the cone, the external surface of the aerobrake being covered with a material that will provide reuseable thermal protection during excursions of the vehicle into the atmosphere, the structure integrally supporting an ascent/descent propulsion system, the tankage therefor and other systems of said vehicle, the thrust vector of the propulsion system being approximately normal to an axis extending through the base of the cone, the structure including integral support structure and attachment for at least one payload module.
Claim 18
Dependent Claim
193 words
A reusable, spaced-based, aerobraking orbital transfer vehicle, said vehicle including a structure formed of bulkheads and stringers, the external configuration of said structure being in the shape of an elliptical cone with an angle of approximately 60° raked-off at an angle of approximately 73° with an ellipsoidal nose and a toroid-like skirt about the base of the cone to form an aerobrake providing lift at zero angle of attack with respect to the cone axis, the ellipsoidal nose minimizing the stagnation point heat flux, the skirt providing a smooth transition from the conical surface to a surface that is more nearly parallel to the wind velocity reducing the heat flux near the trailing edge of the cone, the external surface of the aerobrake being covered with a material that will provide reuseable thermal protection during excursions of the vehicle into the atmosphere, the structure integrally supporting an ascent/descent propulsion system, the tankage therefor and other systems of said vehicle, the thrust vector of the propulsion system being approximately normal to an axis extending through the base of the cone, the structure including integral support structure and attachment for at least one payload module.
Claim 19
Dependent Claim
22 words
The aerobraking orbital transfer vehicle as set forth in claim 14 in which the payload module is attached aft of the aerobrake.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1992-04-03 | 1992-10-03 | 1993-04-04 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1996-04-03 | 1996-10-03 | 1997-04-04 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2000-04-03 | 2000-10-03 | 2001-04-04 | $7700.00 | Window Closed / Lapsed |