US5211360A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Spacecraft thermal disturbance control system
Assignee: Fairchild Space and Defense Corp
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Filing: 1991-06-26
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Granted: 1993-05-18
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Expires: 2011-06-26
Abstract
Abstract A spacecraft thermal disturbance control system for controlling the torque exerted on the main portion of a spacecraft as a result of a thermal gradient being applied to a portion of the spacecraft that projects from the spacecraft's main portion. The spacecraft thermal disturbance control system includes a network of distributed temperature sensors located on the surfaces of the projecting portion of the spacecraft, a microcomputer operatively connected to the temperature sensors for receiving temperature information from the temperature sensors and a reaction wheel assembly operatively connected to the microcomputer. The microcomputer provides command signals to the reaction wheel assembly based upon temperature information received from the temperature sensors to cause the reaction wheel assembly to generate a torque that counteracts the torque exerted on the main portion of the spacecraft as a result of the thermal gradient applied to the projecting portion of the spacecraft.
Inventors
- 👤 Darrell F. Zimbelman
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 11:51
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/22; B64G1/24; B64G1/28; B64G1/283; B64G1/36; B64G1/46; B64G1/50; B64G1/503
Claims Analysis
Total Claims: 15
Claim 1
Independent Claim
181 words
A spacecraft thermal disturbance control system for a spacecraft with a main portion and a projecting potion extending from said main portion which is to be subjected to a thermal gradient which in turn produces a torque exerted on the main portion of said spacecraft comprising a plurality of thermal sensors located on said projecting portion of the spacecraft projecting from the main portion of the spacecraft; control means operatively connected to said thermal sensors for receiving temperature information from said thermal sensors and for providing control commands based upon the received temperature information to counter said thermal gradient torque exerted on the main portion of said spacecraft as a result of a thermal gradient being applied to said projecting portion of the spacecraft projecting from the main portion of the spacecraft; and anti-torque means operatively connected to said control means for providing a torque based upon commands received from said control means to counter the torque exerted on the main portion of said spacecraft as a result of a thermal gradient being applied to the projecting portion of said spacecraft.
Claim 2
Dependent Claim
181 words
A spacecraft thermal disturbance control system for a spacecraft with a main portion and a projecting potion extending from said main portion which is to be subjected to a thermal gradient which in turn produces a torque exerted on the main portion of said spacecraft comprising a plurality of thermal sensors located on said projecting portion of the spacecraft projecting from the main portion of the spacecraft; control means operatively connected to said thermal sensors for receiving temperature information from said thermal sensors and for providing control commands based upon the received temperature information to counter said thermal gradient torque exerted on the main portion of said spacecraft as a result of a thermal gradient being applied to said projecting portion of the spacecraft projecting from the main portion of the spacecraft; and anti-torque means operatively connected to said control means for providing a torque based upon commands received from said control means to counter the torque exerted on the main portion of said spacecraft as a result of a thermal gradient being applied to the projecting portion of said spacecraft.
Claim 3
Dependent Claim
35 words
The spacecraft thermal disturbance control system of claim 1 wherein said control means includes means for estimating a thermal gradient on said projecting portion of said spacecraft based upon temperature measurements from said thermal sensors.
Claim 4
Dependent Claim
34 words
The spacecraft thermal disturbance control system of claim 2 wherein said control means includes means for predicting the magnitude of torque based upon the thermal gradient information obtained from said thermal gradient estimating means.
Claim 5
Dependent Claim
31 words
The spacecraft thermal disturbance control system of claim 3 wherein said projection portion of the spacecraft has two sides and wherein said thermal sensors are located on both of said sides.
Claim 6
Dependent Claim
45 words
The spacecraft thermal disturbance control system of claim 4 wherein said thermal sensors located on both sides of said projecting portion of the spacecraft comprise an array of thermal sensors located on each side of the two sides of said projecting portion of the spacecraft.
Claim 7
Dependent Claim
32 words
The spacecraft thermal disturbance control system of claim 3 wherein said spacecraft has a communication system and wherein said control means includes remote interface means for communicating with said spacecraft communication system.
Claim 8
Dependent Claim
22 words
The spacecraft thermal disturbance control system of claim 6 wherein said control means includes means for receiving electrical power from said spacecraft.
Claim 9
Dependent Claim
23 words
The spacecraft thermal disturbance control system of claim 7 wherein said means for receiving electrical power from said spacecraft includes a power converter.
Claim 10
Dependent Claim
16 words
The spacecraft thermal disturbance control system of claim 3 wherein said control means includes a microprocessor.
Claim 11
Dependent Claim
26 words
The spacecraft thermal disturbance control system of claim 9 wherein said control means also includes an analog to digital converter operatively connected to said thermal sensors.
Claim 12
Dependent Claim
25 words
The spacecraft thermal disturbance control system of claim 10 wherein said control means also includes a programmable peripheral interface operatively connected to said thermal sensors.
Claim 13
Dependent Claim
24 words
The spacecraft thermal disturbance control system of claim 11 wherein said control means includes a voltage making circuit operatively connected to said thermal sensors.
Claim 14
Dependent Claim
25 words
The spacecraft thermal disturbance control system of claim 9 wherein said control means includes a digital to analog converter operatively connected to said antitorque means.
Claim 15
Dependent Claim
18 words
The spacecraft thermal disturbance control system of claim 13 wherein said antitorque means comprises a reaction wheel assembly.
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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) | 1996-05-17 | 1996-11-16 | 1997-05-18 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2000-05-17 | 2000-11-16 | 2001-05-18 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2004-05-17 | 2004-11-16 | 2005-05-18 | $7700.00 | Window Closed / Lapsed |