Aeronautics and astronautics – Spacecraft – Attitude control
Reexamination Certificate
2000-08-22
2002-03-26
Barefoot, Galen L. (Department: 3644)
Aeronautics and astronautics
Spacecraft
Attitude control
C244S115000, C244S13500B
Reexamination Certificate
active
06360995
ABSTRACT:
CROSS-REFERENCE TO RELATED APPLICATIONS
Not applicable.
STATEMENTS REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT
Not applicable.
FIELD OF THE INVENTION
The present invention generally relates to the field of space travel vehicles and, more particularly, to docking systems and methods for such space travel vehicles.
BACKGROUND OF THE INVENTION
Docking systems are used by space travel vehicles to receive/engage objects when in space (hereafter “space object(s)”), such that the space travel vehicle and space object are then interconnected in at least some manner and for one or more purposes. Representative “space objects” of this type include other space travel vehicles, satellites, nanosatellites, free-flying satellites, and the like. Numerous types of docking systems/methods have at least been discussed in the literature, although the same have not necessarily been incorporated on a space travel vehicle which has actually flown in space. Booms have been proposed for space travel vehicles to facilitate the docking of another space object thereto by having the boom extend beyond the space travel vehicle in a deployed position. Typically the space object will include an at least generally conically-shaped cone to direct the end of the boom into a receiving receptacle, cavity, or the like on the space object as the space travel vehicle moves relatively toward the space object. Once the end of the boom is disposed in this receiving receptacle, typically some type of locking/latching mechanism is activated (e.g., by having the end of the boom be appropriately contoured/configured). At least one published docking station then retracts the boom to complete the docking of the space object to the space travel vehicle (with the boom) to dispose the space travel vehicle and space object in mating relation. Such a mating relation is also established by another type of docking system which utilizes mating cones (e.g., a “convex” cone on the space travel vehicle and a similarly sized “concave” cone on the space object, or vice versa).
Another type of docking system which has been discussed in the literature is commonly referred to as a “bola.” These bolas include a main line of an appropriate material (e.g., cable) which is propelled from the space travel vehicle toward the space object which is to be docked to the space travel vehicle. Disposed on the end of this main line are a plurality of secondary lines which effectively wrap around the space travel object to capture the same so as to effectively “lasso” the space object. Various types of structures have been proposed to facilitate this wrapping action and/or the manner in which these secondary lines engage the space object. Nonetheless, the main line is then retracted to dock the space object to the space travel vehicle.
BRIEF SUMMARY OF THE INVENTION
The present invention is generally directed toward to a system/method for docking a space object to a space travel vehicle or the like. A first aspect of the present invention is embodied by a space travel vehicle which includes a space travel vehicle body and a space object docking system which is interconnected with this space travel vehicle body (e.g., integral therewith, detachably interconnected therewith so as to provide a discrete subassembly which may be retrofit on existing space travel vehicles). The space object docking system includes a frame assembly formed by a plurality of individual frame members (e.g., bipod arms). Each frame member is pivotally connected to the space travel vehicle body to allow each frame member to move between a stowed position (e.g., where the plurality of frame members are at least substantially contained within a single reference plane or disposed in at least substantially coplanar relation to provide a reduced storage volume) and a deployed position where the plurality of frame members collectively define an at least generally funnel-shaped profile. Another part of the space object docking system is a space object capture envelope assembly which is interconnected with the noted frame assembly and which occupies a space within the generally above-noted funnel-shaped profile defined by the frame assembly when in its deployed position.
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. The space travel vehicle may include a space object receiving cavity. Certain characterizations may be made of the frame assembly in relation to this space object receiving cavity. One such characterization is that the pivotal connection between each of the individual frame members of the frame assembly may be characterized as being disposed about this space object receiving cavity in spaced relation thereto. An example of “being disposed about” is that the noted pivotal connections may be disposed on a reference circle whose center corresponds with a center of the space object receiving cavity, such that the pivotal connections are radially spaced along this reference circle (e.g., disposed at different radial positions relative to the center of the reference circle, as well as being disposed radially outwardly from this center of the noted reference circle).
The frame assembly may be disposed relative to the above-noted space subject receiving cavity and/or pivotable relative to the space travel vehicle such that when the frame assembly moves from the deployed position to the stowed position, the frame assembly directs a space object which has adhered to the capture envelope assembly toward and preferably into the space object receiving cavity. Consider the case where each frame member may be characterized as having a pair of ends. A first of these ends may be that which is pivotally connected with the space travel vehicle body, and a second of these ends may be that which is “free” to move toward/away from the space object receiving cavity through pivotal movement of the associated frame member. In this case the second or “free” end of each individual frame member may be disposed at least generally proximate the space object receiving cavity when the frame assembly is in its stowed position (including actually extending within the space object receiving cavity), and its corresponding first end may be disposed further from the space object receiving cavity. Therefore, by pivoting the individual frame members from the deployed position to the stowed position about their corresponding first ends, the second end of each frame member will at least generally move toward the space object receiving cavity. This motion of the frame assembly may then be used to direct a space object which has adhered to the space object capture envelope toward and more preferably actually into the space object receiving cavity. Conversely, when the frame assembly is moved from the stowed position to the deployed position, the second end of each frame member will move at least generally away from the space object receiving cavity to define the noted at least generally funnel-shaped profile for the frame assembly when in the deployed position. Typically the frame members will be pivoted an amount so that the second end of each individual frame member will be disposed further from the space object receiving cavity than its corresponding first end when the frame assembly is in its fully deployed position.
As noted above, the individual frame members may be in the form of a bipod arm or the like. Other configurations may be appropriate as well. In addition, at least some of the frame members may be configured/adapted to facilitate directing a space object which has adhered to the capture envelope assembly into the noted space object receiving cavity. One such configuration is where the subject frame member extends axially away from the pivotal connection on the space travel vehicle body to a first location at a first angle relative to a ref
Barefoot Galen L.
Lockheed Martin Corporation
Marsh & Fischmann & Breyfogle LLP
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