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 Title: |
US5641135:
Inflatable torus and collapsible hinged disc spacecraft designs for satellite communication system
[ Derwent Title ]
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| Country: |
US United States of America
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| Inventor: |
Stuart, James R.; Louisville, CO
Patterson, David Palmer; Los Altos, CA
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| Assignee: |
Teledesic Corporation, Kirkland, WA
other patents from TELEDESIC CORPORATION (710519) (approx. 10)
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| Published / Filed: |
1997-06-24
/ 1994-05-05
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| Application Number: |
US1994000238568
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| IPC Code: |
Advanced:
B64G 1/10;
B64G 1/22;
B64G 1/44;
B64G 1/00;
Core:
B64G 1/42;
more...
IPC-7:
B64G 1/22;
B64G 1/44;
H01L 31/045;
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| ECLA Code: |
B64G1/10C; B64G1/10M; B64G1/22D; B64G1/44;
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| U.S. Class: |
Current:
244/172.6;
136/245;
136/292;
244/158.3;
244/172.7;
Original:
244/173;
244/158.R;
136/245;
136/292;
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| Field of Search: |
244/158 R,173
136/244,245,292
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| Priority Number: |
| 1994-05-05 |
US1994000238568 |
| 1992-08-18 |
US1992000931625 |
| 1991-11-08 |
US1991000790748 |
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| Abstract: |
A series of spacecraft designs (10, 42 and 52) for a Satellite Communication System is disclosed. One of the preferred embodiments of the invention called "Gearsat.TM." (10) comprises a hollow torus which inflates when it reaches orbit. When viewed from the side along its circumference, Gearsat (10) looks like two flattened pyramids sharing a common base. Phased array antenna panels (14) are deployed across the top of the pyramid along an exterior cylindrical surface (12), while twin arrays of solar cells (16) cover the slanted surfaces. The satellite (10) rotates about its center, and individual antenna panels (14) are spatially synchronized to transmit and receive signals from particular regions on the ground. An alternative embodiment, called "Batsat.TM." (42, 52), includes a central cylindrical body (B) and a plurality of substantially circular linked antenna and solar/thermal panels (A1-A9 and S1 and S2) which carry individual antennas (X) and solar/thermal surfaces (Y). All of the embodiments (10, 42 and 52) are capable of being nested or stacked in a compact arrangement that fit within the payload bay of a launch vehicle (L).
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| Attorney, Agent or Firm: |
Anglin & Giaccherini ;
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| Primary / Asst. Examiners: |
Kashnikow, Andres; Mojica, Virna Lissi
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| INPADOC Legal Status: |
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Family Legal Status Report
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| Parent Case: |
CLAIM FOR PRIORITY
The present application is a Continuation-in-Part Patent Application. The Applicants hereby claim the benefit of priority under Section 120 of Title 35 of the United States Code of Laws for any and all subject matter which is commonly disclosed in the present application and in a pending patent application by James R. Stuart, filed on Aug. 18, 1992 and assigned U.S. Ser. No. 07/931,625 now U.S. Pat. No. 5,386,953, which claims the benefit of priority of a parent application entitled Spacecraft Designs for Satellite Communication System by James R. Stuart filed on Nov. 8, 1991 and assigned U.S. Ser. No. 07/790,748 now abandoned.
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| Designated Country: |
AT AU BB BG BR CA CH CS DE DK EP ES FI GB HU JP KP KR LK LU MG MN MW NL NO OA PL RO RU SD SE UA
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| Family: |
Show 4 known family members
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First Claim:
Show all 20 claims |
What is claimed is:
1. A spacecraft apparatus capable of being placed in a low Earth orbit (32) using a launch vehicle (L), said spacecraft having a velocity direction (VD) and a direction to the Nadir (ND) while in orbit comprising:
- a central body (B);
- a plurality of antenna panels (A1-A9);
- a plurality of solar/thermal panels (S1-S2);
- said antenna panels (A1-A9) and said solar/thermal panels (S1-S2) stowed before launch in said launch vehicle (L) in stacked layered relationship against said central body (B);
- a plurality of hinges (H) for movably coupling said antenna panels (A1-A9) and said solar/thermal panels (S1-S2), serially, each to another and to said central body (B) at an attachment point on an edge of each of said panels (A1-A9, S1-S2); each said attachment point being rotatable, in respect of a preceding attachment point, to a hinge locking angle in an elevation direction and displaced from said preceding attachment point by an offset angle in an azimuth direction;
- said antenna panels (A1-A9) and said solar/thermal panels (S1-S2) being deployed in orbit, taking the shape of an arm, and being uniquely positioned in said arm with respect to said direction to the Nadir (ND), by said hinge locking angle and said offset angle in combination, to cover a desired footprint area on the Earth's surface and to achieve an optimal angle for solar energy collection and thermal radiation.
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| Background / Summary: |
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| Drawing Descriptions: |
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| Description: |
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| Forward References: |
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