Universal spacecraft attitude steering control system
US5692707A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | May 15, 1995 |
| Grant date | Dec 2, 1997 |
| Priority date | — |
| Expiry date | May 15, 2015 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/286
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A method and system of attitude steering and momentum management for a spacecraft suitable over a wide range of orbit altitude and inclination parameters and a similar wide range of mission steering profiles is provided. The system utilizes two active momentum wheels positioned with their spin axes nominally coaligned on the spacecraft pitch axis. Each wheel is pivoted by jackscrew type mechanisms which allow the angular momentum to be tilted (e.g. within the range 0-45.degree. from the nominal alignment with respect to the spacecraft body). The spacecraft control processor generates wheel torque commands for the wheel speed electronics and jackscrew drive commands for the platform assemblies in order to adjust the speed and amount of tilt of the momentum wheels. The invention provides a two-momentum wheel array that allows use of either momentum bias steering or large angle zero-momentum steering and accommodates multiple orbit geometries and varying degrees of attitude steering agility.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.