Spacecraft attitude stabilization system
US4807835A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Apr 10, 1987 |
| Grant date | Feb 28, 1989 |
| Priority date | — |
| Expiry date | Apr 10, 2007 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/244
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
The attitude of a spacecraft can be effectively controlled in three axes using the combination of a gravity gradient boom and three electromagnets. The electromagnets are controlled according to a control law that takes into consideration signals from a magnetometer and a signal indicating the orbital angular velocity of the spacecraft. During the acquisition phase of the flight, the gravity gradient boom is not extended and electromagnets are operated according to a control law that only takes into account the output of the magnetometer. After the acquisition phase is complete, the gravity gradient boom is extended and the spacecraft enters the libration phase of the flight. In the libration phase of the flight, electromagnets are controlled according to a control law that takes into account both the output of the magnetometer and a signal which indicates the orbital angular velocity of the spacecraft.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.