Ordnance – Rocket launching – Having means to transfer rocket to launcher
Reexamination Certificate
1998-02-25
2001-02-13
Jordon, Charles T. (Department: 3641)
Ordnance
Rocket launching
Having means to transfer rocket to launcher
C089S001815
Reexamination Certificate
active
06186039
ABSTRACT:
TECHNICAL FIELD OF THE INVENTION
The invention relates generally to spacecraft launching, and more particularly to a spacecraft launch system and method.
BACKGROUND OF THE INVENTION
A traditional approach to fabricate, integrate, and launch spacecraft performs these operations while the spacecraft is in a vertical-orientation. This approach requires high bay areas, platforms or other scaffolding to access portions of the spacecraft, and a specialized transport to move the spacecraft from an assembly area to the launch site. Vertical processing of the spacecraft for launch introduces complexity, cost, and potential hazard since the spacecraft in a vertical orientation is more unstable and more difficult to access.
To overcome the limitations of vertical processing, some techniques perform integration and testing while the spacecraft is in a horizontal orientation. These prior systems that perform at least part of the pre-launch operations in a horizontal orientation benefit from a reduction in launch costs, complexity, and potential danger associated with vertical operations. Although some prior systems recognize the advantages of horizontal processing of a spacecraft, these systems fail to provide a cost-effective and reusable launch system that functions within an integrated launch services facility.
SUMMARY OF THE INVENTION
In accordance with the present invention, a launch system and method are provided that substantially eliminate or reduce disadvantages or problems associated with previously developed spacecraft launch systems and methods. In particular, the present invention provides a launch system that includes a support assembly and a seat that rotate about a hinge axis to move the spacecraft from a horizontal position to a vertical position.
In one embodiment of the present invention, a launch system includes a support assembly to support a spacecraft in a horizontal position and a seat to support the spacecraft during a transition from the horizontal position to a vertical position. A hinge is coupled to the support assembly and the seat, wherein the support assembly and the seat rotate about a hinge axis during the transition.
In another embodiment of the present invention, a method for moving a spacecraft from a horizontal position to a vertical position includes supporting the spacecraft on a support assembly in a horizontal position; aligning an aft portion of the spacecraft with a seat; and rotating the support assembly and the seat about a hinge axis to place the spacecraft in a vertical position.
Technical advantages of the present invention include a launch system that includes both a support assembly and a seat to support a spacecraft during a transition from a horizontal position to a vertical position. In a particular embodiment, the seat remains perpendicular to a longitudinal axis of the support assembly during the transition. After fueling and final preparation of the spacecraft for launch, the support assembly returns to its horizontal position. The launch system may integrate with a transport assembly to receive the spacecraft from a vehicle integration facility that, along with the launch system, is part of an integrated launch services facility. In a particular embodiment, the launch system includes alignment members and actuators to ensure proper alignment between the seat and an aft portion of the spacecraft. Also, the launch system may include a weight and a cooperative retention device that allows the support assembly and seat to rotate about the hinge axis without the need for hydraulics or other complex actuators. Moreover, an umbilical transfer mast integral with the support assembly provides access to the spacecraft while in the vertical position for fueling, monitoring, and other activities. Other technical advantages are readily apparent to one skilled in the art from the following figures, descriptions, and claims.
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Cohen Aaron
Mueller George E.
Myers Dale D.
Pohl Henry O.
Baker & Botts L.L.P.
Jordon Charles T.
Kistler Aerospace Corporation
Wesson Theresa M.
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