Aeronautics and astronautics – Spacecraft – With fuel system details
Reexamination Certificate
2002-05-16
2003-09-23
Jordan, Charles T. (Department: 3641)
Aeronautics and astronautics
Spacecraft
With fuel system details
Reexamination Certificate
active
06622971
ABSTRACT:
FIELD OF THE INVENTION
The invention is related to the field of space vehicles for use in launching a payload from a stationary ground-based position into orbit, and specifically to an adapter for connecting at least a first and second rocket stage of a space vehicle.
BACKGROUND OF THE INVENTION
Rocket powered space vehicles used in space missions can generally be categorized into launch vehicles and payloads. Launch vehicles provide the primary thrust for launching and delivering a payload from the earth's surface into orbit. Launch vehicles generally include two or more rocket stages arranged to fire at different times as the launch vehicle travels from the earth's surface into orbit. The rocket stages are fired sequentially and typically include at least a first stage or booster stage rocket and a second stage or upper stage rocket. The booster stage rocket is designed to launch and deliver the payload a pre-determined distance above the earth before exhaustion. Upon exhaustion, the booster stage rocket is jettisoned and the upper stage rocket is fired to deliver the payload the remainder of the distance into a desired orbit. Once in orbit, a payload such as a satellite, interplanetary probe, or the like is released from the upper stage. In some cases, the payload may include propulsion subsystems for orbital maintenance, attitude control, and orbital transfer depending on its intended function.
The jettisoned booster and upper stage rockets typically fall back toward the earth where they either bum up in the earth's atmosphere or reach the ground or a body of water. The separation of the rockets is accomplished using adapters that connect the various rocket stages and ultimately the final rocket stage to the payload. The adapters are designed to separate at a forward interface from the next sequential rocket stage, while a rear interface of the adapter remains attached to the separated rocket stage and returns to earth or is destroyed with the separated rocket stage in the earth's atmosphere. Several techniques are utilized to separate the adapter and exhausted rocket stage from an upper rocket stage or payload. Some common techniques include pneumatic, hydraulic, and pyrotechnic joints.
Because of the expensive nature of disposable rockets, an emphasis exists on the development of reusable launch vehicles. Reusable launch vehicles utilize rocket stages that include methods and apparatus for a controlled return to the earth's surface that prevents damage upon impact or entry and travel through the earth's atmosphere. The rocket stage may then be recovered and used in future space missions with little or no refurbishment.
SUMMARY OF THE INVENTION
The present invention generally relates to an adapter for connecting rocket stages of a space vehicle. In the context of the present invention, a rocket stage is defined as one or more rocket sections, e.g. separate rockets with individual thrust sources, or a rocket section and a payload. The present adapter provides specific advantages when used with reusable rocket stages, but those skilled in the art will appreciate that the adapter described herein could easily be used to connect any two rocket stages or a rocket stage and a payload.
In view of the foregoing, a primary object of the present invention is to provide an adapter for joining rocket stages. Another object of the present invention is to provide an adapter that upon separation of the rocket stages, the adapter itself is at least partially separatable from an exhausted rocket stage. Another object of the present invention is to protect the exhausted rocket stage during a return flight back to the earth's surface. Another object of the present invention is to enhance the aerodynamic characteristics of the exhausted rocket stage to facilitate the return flight back to the earth's surface.
One or more of the above-noted objectives, as well as additional advantages, are provided by a first aspect of the present invention, which includes an adapter for connecting a first rocket stage and a second rocket stage. The adapter forms a first interconnection between the second rocket stage and the adapter that is separatable by a first separating system. The adapter also forms a second interconnection between the first rocket stage and the adapter that is separatable by a second separating system. That is, the adapter not only separates the first and second rocket stages, but also subsequently separates from the first or exhausted rocket stage. Where the first rocket stage is a reusable rocket stage, separation of the adapter from the first rocket stage “cleans up” the first rocket stage for a controlled descent and flight back to the earth's surface.
Various refinements exist of the features noted in relation to the subject first aspect of the present invention. Further features may also be incorporated in the subject first aspect of the present invention as well. These refinements and additional features may exist individually or in any combination. For instance, the adapter of the subject first aspect may define an elongated housing made up of a plurality of detachably interconnected adapter sections (e.g., first, second, and third adapter sections). The adapter sections may be interconnected by any suitable method (both in terms of how the structural interconnection between the individual adapter sections is established and how the individual adapter sections are separated from each other). In the case where three such adapter sections are used, the interconnected adapter sections define a first, second, and third separation interface at the interconnections of the mating edges of the adapter sections. In one embodiment, the interconnected adapter sections could connect at a base thereof to the first rocket stage and include a ribbed interface about their exterior surface that mates with the second rocket stage to connect the first and second rocket stages.
Any appropriate way of detachably interconnecting the adapter with each of the first and second rocket stages may be used (both in terms of how the structural interconnection is established, and how the adapter is separated from both the first rocket stage and the second rocket stage). For instance, the separating systems could include numerous apparatus, e.g. pyrotechnics, hydraulics, and mechanical devices. In one embodiment, the first or second separating system may include an explosive fastener assembly, such as low shock producing explosive bolts, that are used to connect the base of the elongated housing to the first rocket stage. In another embodiment, where the adapter includes the plurality of adapter sections, an adapter section separating system may be utilized that includes at least one pulley mounted on one of the adapter sections, e.g. the first section, and at least one other pulley mounted on a mating adapter section, e.g. the second section. A cable alternatively wound between the pulleys and connected at one end to the first section and the other end to the second section may secure the two sections together. A similar set of pulleys and cable may then be used to secure the other adapter sections together to form the housing for the adapter, e.g. the second and third sections and the third and first sections. One or more cutting devices may also be included in the adapter section separating system to cut the cables at the desired separation time to release the first, second, and third adapter sections thereby separating the adapter sections.
The adapter of the subject first aspect may be used in combination with a shield apparatus that remains connected to the first rocket stage. In this characterization, the shield apparatus may be internally contained within the above-noted elongated housing. The adapter and shield apparatus may be characterized as a rocket stage interconnect assembly. In this characterization, the shield apparatus is longitudinally deployable relative to the first rocket stage, following the separation of the adapter from the first rocket st
Lockheed Martin Corporation
Lofdahl Jordan M
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