Minimum fuel attitude and nutation controller for spinning spacecraft
US6347262B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 5, 2000 |
| Grant date | Feb 12, 2002 |
| Priority date | — |
| Expiry date | Jan 5, 2020 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/369
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A method, apparatus, article of manufacture, and a memory structure for controlling an attitude and a nutation of a spacecraft spinning about a first axis. The method comprises the steps of measuring a spacecraft attitude rate &ohgr;1(t) about a second axis substantially orthogonal to the first axis; generating a rate correction value &agr;&ohgr;1(t)/&lgr;0, wherein &lgr;0 is an inertial nutation frequency of the spinning spacecraft, and &agr; is a proportionality factor; determining a spacecraft attitude angle &phgr;2(t) about a third axis substantially orthogonal to the first axis and the second axis; generating an error signal e(t) as &phgr;2(t)+&agr;&ohgr;1(t)/&lgr;0; and applying a torque to rotate the spacecraft along the second axis. The article of manufacture comprises a program storage device storing instructions implementing the instructions described above. The apparatus comprises an attitude rate sensor for measuring the spacecraft attitude rate &ohgr;1(t) about a second axis substantially orthogonal to the first axis; means for measuring a spacecraft attitude angle &phgr;2(t) about a third axis substantially orthogonal to the first axis; a processor, in communication w…
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