Aeronautics and astronautics – Spacecraft – Spacecraft formation – orbit – or interplanetary path
Reexamination Certificate
2002-08-15
2004-04-20
Carone, Michael J. (Department: 3641)
Aeronautics and astronautics
Spacecraft
Spacecraft formation, orbit, or interplanetary path
C244S173300, C136S292000, C136S245000
Reexamination Certificate
active
06722614
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Field of the Invention
This invention relates to a satellite deployment structure such as a solar array paddle, a radiator panel, an antenna, or the like, to be mounted on a satellite.
2. Description of Related Art
A satellite deployment structure has a plurality of panels which are connected to a satellite structure. Each of the panels is movably connected to another panel by means of hinges, or the like. Prior to launching a rocket, the panels are housed in the satellite with the panels folded and layered. After launching the rocket, the panels are deployed during an orbit to function as a part of the satellite in space.
FIGS. 3A and 3B
are schematic explanatory drawings showing the structure of a conventional solar array paddle
11
which is known as one of the satellite deployment structures, and show the solar array paddle
11
when it is being housed.
FIG. 3A
is a perspective view showing the uppermost panel of the solar array paddle
11
when it is being housed.
FIG. 3B
is a side view showing the entire solar array paddle
11
as seen from the direction D in FIG.
3
A. Here, the lower part of
FIG. 3A
is the side connected to a satellite structure (not shown). In
FIGS. 3A and 3B
, hatching to show the sectioned surfaces is partly omitted.
Referring to
FIGS. 3A and 3B
, reference numeral
11
denotes the solar array paddle, reference numeral
12
four folded panels, reference numeral
13
hinges which movably connect the panels
12
together, reference numeral
14
a yoke which connects the satellite structure and the panel adjacent to the satellite structure, reference numeral
15
a launch lock which fixes and holds the panels together, as well as the satellite structure and the panel
12
adjacent thereto. The holding lock
15
is provided in two positions, in the neighborhood of the center of the panel
12
as well as in four positions therearound, i.e., in six positions in total.
The operation of the conventional satellite deployment structure will be described.
Each of the panels
12
of the solar array paddle
11
is mounted on the rocket, folded and connected to the satellite structure (not shown) and is launched. After launching, the holding locks
15
are released in an orbit by a releasing mechanism (not shown), whereby each of the panels
12
is deployed. The deployment of the panels
12
in space is thus finished, and the solar array paddle
11
functions as a part of the satellite.
The conventional solar array paddle as one of the satellite deployment structures thus constituted as described above entails the following problems.
Namely, in order to prevent a resonance with very large vibrations that occurs at the time the rocket is launched, an increased characteristic frequency of the solar array paddle is essential.
On the other hand, since the rocket has a limited volume and weight lifting ability, the thickness of each panel of the solar array paddle must preferably be thin as possible. Regrettably, the thinner the panel is, the higher the characteristic frequency of the solar array paddle.
In order not to make the characteristics frequency higher when the thickness of the panel is made as thin as possible, there is a way of increasing in the number of holding locks for fixing and holding in position the panels when the panels are being housed, i.e., of increasing the number of positions for fixing the panels.
However, since the holding locks are to be released during the orbiting of the satellite, the number of the releasing mechanisms inevitably increases in correspondence with the number of the holding locks, resulting in an increase in weight to be mounted on the rocket.
Further, since the panels are not deployed unless all of the holding locks have been released, as increase in the number of the holding locks possibly lowers the reliability of the deployment of the panels.
SUMMARY OF THE INVENTION
The present invention has been made to solve the above and other problems and an object thereof is to provide a satellite deployment structure in which the characteristics frequency can be made higher without increasing the number of holding locks even if the thickness of the panels is made thinner as far as possible.
In order to attain the above and other objects, a satellite deployment structure according to the present invention is provided with a plurality of insertion members for prevention of vibration disposed in a clearance between each of the panels and in that between a main body of a satellite and the panel adjacent to the main body when the panels are being housed with them folded and layered.
According to the present invention, when the panels are being housed with them folded and layered, a plurality of elastic members for prevention of vibration are disposed in the clearance between each of the panels and in that between the main body of the satellite and the panel adjacent to the main body. Therefore, even if the thickness of the panels is made thinner as much as possible, there is provided a satellite deployment structure in which the characteristics frequency can be made higher without increasing the number of the holding locks. At the same time, the satellite deployment structure which is capable of reducing the vibration response can be provided.
The above and other objects and the attendant advantages of the present invention will become readily apparent by reference to the following detailed description when considered in conjunction with the accompanying drawings wherein:
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QuakeSat Team, Dec. 18, 2001, Stanford University,Preliminary Design Review, pp. 19-34.
Ozaki Tsuyoshi
Ozawa Takuo
Carone Michael J.
Leydig , Voit & Mayer, Ltd.
Mitsubishi Denki & Kabushiki Kaisha
Semuwegus L.
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