Method using double thruster firings to deadbeat flexible solar array structural oscillations
US5957411A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Dec 24, 1997 |
| Grant date | Sep 28, 1999 |
| Priority date | — |
| Expiry date | Dec 24, 2017 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/245
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A spacecraft includes a plurality of thrusters mounted at predetermined locations on a spacecraft structure, individual ones the plurality of thrusters being fired for generating a torque about a desired axis. The firing of a thruster is partitioned into two firings that are offset in time by an amount .DELTA.t, wherein .DELTA.t=(1/2).times.(1/F).times.SF, where F is a dominant modal frequency, in Hertz, for any particular axis (nominally the 1st mode) of the spacecraft structure, and where SF is a scale factor that is adjustable about the frequency. In a presently preferred embodiment the thruster is a low thrust thruster that is mounted on a solar array panel, and the thrusters are fired in pairs.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.