Aeronautics and astronautics – Spacecraft – Spacecraft formation – orbit – or interplanetary path
Reexamination Certificate
1998-12-03
2001-05-22
Swiatek, Robert P. (Department: 3643)
Aeronautics and astronautics
Spacecraft
Spacecraft formation, orbit, or interplanetary path
C292S113000
Reexamination Certificate
active
06234426
ABSTRACT:
BACKGROUND OF THE INVENTION
This invention relates generally to modular spacecraft configurations and, more particularly, to modular spacecraft electronic equipment panels that can be externally mounted on a core spacecraft structure.
Conventional spacecraft designs have placed electronic equipment units on panels located inside box-like equipment compartments, with the panels typically forming the walls of the compartments. The equipment compartments are an integral part of the spacecraft structure. Complex interconnecting wiring connects the different electronic units together. Heat dissipated from the electronics equipment is conducted into the compartment panels and radiates into space. The size of each compartment is determined in part by the heat radiating area needed to cool the equipment, so there is often unused volume within each compartment. Because only one side of the equipment panel is used as a radiator, the equipment compartments often have to be very large to maintain desired operating temperatures. A related problem is that accessing equipment requires the removal of panels from the equipment compartment. Not only are compartments of this type bulky to accommodate in a launch vehicle and difficult to access for servicing, but they typically need to be coupled to other thermal radiator panels, through heat-conducting pipes, to provide overall thermal management of the spacecraft.
Further, because the equipment compartments are integral with the core structure of the spacecraft, thermally induced stresses are a significant problem because of temperature differences between the modules and the spacecraft core structure. In brief, these conventional equipment compartments are structurally and thermally dependent on the spacecraft core structure, and the overall design of the spacecraft must take into account the thermal requirements of each module and the structural forces resulting from the presence of each module.
As a result of these difficulties, the spacecraft core structure is usually constructed to have a relatively high weight and volume, to support the modules and to provide an adequate thermal radiation area. Also, it is usually the case that the choice of materials of both the modules and the spacecraft core structure is limited because there is a concern for differential thermal expansion. A further difficulty is that removal or addition of an electronics equipment unit upsets the overall structural and thermal design to some degree. Alignment problems, thermal management problems, or both, can result from simply removing or adding a unit
All of the foregoing problems are attributable to interdependence of the equipment modules and the spacecraft core structure, which together interact, both structurally and thermally, as parts of a larger assembly. It will be appreciated, therefore, that there is a need for a different approach to the construction of spacecraft modules for supporting electronic equipment, to overcome the difficulties noted above. U.S. Pat. Ser. 5,897,080 filed DEC. 20, 1996, entitled “Externally Mountable Spacecraft Equipment Module,” and assigned to the same assignee as the present application, discloses a spacecraft architecture in which modules in the form of base panels to which electronic components are attached, are designed to be structurally and thermally independent of a spacecraft core structure to which the modules are attached. The prior application is hereby incorporated by reference into the present application, which discloses and claims improved techniques for assembly and disassembly of modules of the type disclosed in the prior application.
SUMMARY OF THE INVENTION
The present invention resides in a modular spacecraft construction in which modules may be conveniently assembled and disassembled without the need for tools. Briefly, and in general terms, the modular spacecraft construction of the invention comprises a spacecraft core structure; at least one spacecraft equipment module in the form of a generally flat panel; at least one electronic sub-module for installation on the equipment module; a plurality of hand-operated fasteners of a first type for attaching the spacecraft equipment module to the spacecraft core structure; and a plurality of hand-operated fasteners of a second type for attaching the electronic module to the spacecraft equipment module. The hand-operated fasteners of the first and second types hold each module and submodule securely, but allow for convenient assembly and disassembly without the need for tools.
More specifically, each fastener of the first type includes a hook-type latch with a hand-operated locking device. To secure the spacecraft panel module there are at least two fasteners of the first type located on each face of the spacecraft equipment module. In the disclosed embodiment of the invention, each fastener of the second type includes a screw-type fastener having a threaded stud that extends through the electronic module to be attached to the module panel, a threaded receptacle installed in the module panel to receive the threaded stud, a one-way ratchet mechanism that prevents deliberate or inadvertent unscrewing rotation of the threaded stud, and a ratchet release mechanism to permit removal of the threaded stud.
It will be appreciated from the foregoing that the present invention represents a significant advance in the field of modular spacecraft construction. In particular, the invention allows spacecraft modules and sub-modules to be quickly assembled and disassembled without the use of tools. Other aspects and advantages of the invention will become apparent from the following more detailed description, taken in conjunction with the accompanying drawings.
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Anderson Joseph F.
Renken Raymond H.
Swiatek Robert P.
TRW Inc.
Yatsko Michael S.
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