Patent US5141180A successfully refreshed from Google Patents.
US5141180A
Expired / Lapsed
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Satellite attitude control system using a superconducting magnetic loop
Assignee: Airbus Group SAS
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Filing: 1990-06-22
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Granted: 1992-08-25
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Expires: 2010-06-22
Abstract
Abstract A satellite comprising a deployable solar generator that can be oriented relative to the satellite body is kept facing the sun at all times. It includes an attitude stabilization device comprising a superconductive material closed loop carried by a support coupled to the solar generator and disposed on a side of the support facing substantailly away from the sun. A secondary loop parallel to the closed loop is substantially the same shape and size as the closed loop, and is carried by the support near the loop. A resistive circuit is carried by the support near at least part of the closed loop. A selective electrical power supply circuit is connected electrically to the secondary loop and to the resistive circuit.
Inventors
- 👤 Alain Reboux
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 00:45
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/22; B64G1/42; B64G1/44; B64G1/24; B64G1/32; B64G1/28; B64G1/285; Y; Y10; Y10S; Y10S136/00; Y10S136/291; Y10S136/292
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
129 words
Satellite comprising a deployable solar generator comprising solar generator panels that can be oriented relative to a satellite body and is adapted to be kept facing the sun at all times and an attitude stabilization device comprising at least: a superconductive material closed loop carried by a support coupled to the solar generator and disposed on a side of said support adapted to face substantially away from the sun; a secondary loop parallel to said closed loop with substantially the same shape and size as said closed loop, carried by said support near said closed loop. a resistive circuit carried by said support near at least part of said closed loop; and a selective electrical power supply circuit connected electrically to said secondary loop and to said resistive circuit.
Claim 2
Dependent Claim
129 words
Satellite comprising a deployable solar generator comprising solar generator panels that can be oriented relative to a satellite body and is adapted to be kept facing the sun at all times and an attitude stabilization device comprising at least: a superconductive material closed loop carried by a support coupled to the solar generator and disposed on a side of said support adapted to face substantially away from the sun; a secondary loop parallel to said closed loop with substantially the same shape and size as said closed loop, carried by said support near said closed loop. a resistive circuit carried by said support near at least part of said closed loop; and a selective electrical power supply circuit connected electrically to said secondary loop and to said resistive circuit.
Claim 3
Dependent Claim
21 words
Satellite according to claim 1 wherein said superconductive material closed loop is in a plane parallel to said solar generator panels.
Claim 4
Dependent Claim
19 words
Satellite according to claim 1 , wherein said support is an additional panel coupled mechanically to said solar generator.
Claim 5
Dependent Claim
23 words
Satellite according to claim 3 wherein said additional panel is articulated to the end of said solar generator farthest from said satellite body.
Claim 6
Dependent Claim
17 words
Satellite according to claim 1 wherein said superconductive material loop is formed by a substantially circular strip.
Claim 7
Dependent Claim
22 words
Satellite according to claim 1 wherein said superconductive material loop is formed by a thin-layer deposit of superconductive material on a substrate.
Claim 8
Dependent Claim
24 words
Satellite according to claim 1 wherein said closed loop is carried by a frame coupled mechanically to said support by thermally insulative material means.
Claim 9
Dependent Claim
18 words
Satellite according to claim 1 wherein said secondary loop is disposed on said support opposite said closed loop.
Claim 10
Dependent Claim
22 words
Satellite according to claim 1 wherein said resistive circuit and said secondary loop are supplied with electrical power by said solar generator.
Claim 11
Dependent Claim
13 words
Satellite according to claim 1 wherein said solar generator has only one wing.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1995-08-25 | 1996-02-24 | 1996-08-25 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1999-08-25 | 2000-02-24 | 2000-08-25 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2003-08-25 | 2004-02-24 | 2004-08-25 | $7700.00 | Window Closed / Lapsed |