Aeronautics and astronautics – Spacecraft – With payload accommodation
Reexamination Certificate
1998-07-27
2001-01-16
Poon, Peter M. (Department: 3644)
Aeronautics and astronautics
Spacecraft
With payload accommodation
C307S009100
Reexamination Certificate
active
06173923
ABSTRACT:
TECHNICAL FIELD
The present invention relates to spacecrafts, and more particularly, to spacecrafts having battery packs integrated into the solar wing structure.
BACKGROUND ART
A typical spacecraft comprises a main body portion comprising a payload module and a bus module, a first solar wing, and a second solar wing. Each solar wing is selectively rotatably by a respective solar wing drive extending from diametrically opposite sides of the main body portion of the spacecraft. Each wing is connected to a boom which connects to a respective solar wing drive. The solar wings are typically planar and have solar cells on one side for converting sunlight into energy for powering the spacecraft.
Spacecrafts usually require four battery packs which supply energy for the spacecraft when the solar cells on the solar wings are not exposed to sunlight. These battery packs are typically secured at the four ends, or corners, of the bottom portion of the main body portion of the spacecraft to balance the weight of the battery packs. This particular placement of the battery packs, while adding stability to the spacecraft, also increases the height of the spacecraft. The height of the spacecraft is determinative of the size of the launch vehicle used for launching the spacecraft and/or the number of spacecrafts that can be launched per flight in a particular launch vehicle.
The main body portion of the spacecraft typically contains radiators for eliminating waste heat generated from the main body portion. The radiators are usually secured to the surfaces defining the main body portion, or can comprise the surfaces defining the main body portion, so that the radiators cover the main body portion. Radiators can also extend from the main body portion to maximize the elimination of spacecraft waste heat generated from the main body portion. Each battery pack has its own radiator which operates to eliminate waste heat generated from the battery pack. With the battery packs positioned on the bottom of the bus module, the height of the spacecraft is increased without increasing the available main body portion radiator space. It would be desirable to maximize the available area for main body portion radiators to maximize the spacecrafts ability to eliminate waste heat from the main body portion without increasing the size of the spacecraft.
Another problem with the positioning of the battery packs on the bottom side of the bus module, in addition to taking up space that could be used for main body portion radiators, is that the battery packs are susceptible to sunlight. Thermal loading from the sunlight operates to decrease the battery pack's operating life and efficiency.
Accordingly, it would be desirable to provide a spacecraft wherein the battery packs were positioned in such a manner as to increase available main body portion radiator area without increasing the size of the spacecraft. It would also be desirable to be able to decrease the height of a spacecraft without decreasing the available main body portion radiator area. It would also be further desirable to provide a spacecraft wherein the battery packs were positioned in such a manner as to reduce their exposure to sunlight thereby improving the battery pack's operating life and efficiency.
DISCLOSURE OF INVENTION
One object of the present invention is to provide a spacecraft wherein the battery packs were positioned in such a manner as to increase available main body portion radiator area without increasing the size of the spacecraft.
Another object of the present invention is to provide a spacecraft wherein the battery packs were positioned in such a manner as to decrease spacecraft height without decreasing available main body portion radiator area.
Yet another object of the present invention is to provide a spacecraft wherein the battery packs were positioned in such a manner as to reduce their exposure to sunlight thereby improving the battery packs' operating life and efficiency.
In carrying out the above objects, the present invention includes a spacecraft having a main body portion, a first solar wing, a second solar wing, a first battery pack secured to the first solar wing and, a second battery pack secured to the second solar wing.
In a preferred embodiment, the spacecraft comprises a bus module, a payload module and an antenna portion, with the solar wings being secured to the bus module of the main body portion.
The above, and other objects, features and advantages of the present invention will be readily apparent from the following detailed description of the best mode for carrying out the invention when taken in connection with the accompanying drawings.
REFERENCES:
patent: 5228644 (1993-07-01), Garriott et al.
patent: 5271582 (1993-12-01), Perkins et al.
patent: 5372183 (1994-12-01), Strickberger
patent: 5400986 (1995-03-01), Amore et al.
patent: 5798574 (1998-08-01), Coronel
patent: 5823476 (1998-10-01), Caplin
patent: 5874924 (1999-02-01), Csongor et al.
patent: 2672746 (1991-11-01), None
patent: 10-258800 (1988-09-01), None
patent: 6-329100 (1994-11-01), None
Felland Jane R.
Penera Cecilia A.
Perez James
Gudmestad T.
Hughes Electronics Corporation
Palo Francis T.
Poon Peter M.
Sales M. W.
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