Spacecraft thermal shock suppression system
US6607167B2 · kind B2 · utility
1Cited by
4References
28Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 1, 2001 |
| Grant date | Aug 19, 2003 |
| Priority date | — |
| Expiry date | Aug 3, 2021 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/369
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A satellite system includes a solar wing moveably connected to a satellite central body. A sensor, also coupled to the satellite central body, detects the movement of the body and generates a rate signal based on that movement. Additionally, an actuator, which controls momentum, is coupled to the satellite central body with maximum torque along the thermal shock axis. Subsequently, a rate-dominated thermal shock suppression controller, which is coupled to the satellite central body, receives the rate signal from the sensor to control the actuator.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.