Actuator with transfer of angular momentum for the attitude control of a spacecraft
US9180983B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Nov 18, 2008 |
| Grant date | Nov 10, 2015 |
| Priority date | — |
| Expiry date | Jan 14, 2031 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/285
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An attitude control actuator of a spacecraft includes a first momentum wheel driven in rotation by a motor and a second momentum wheel. Both momentum wheels are movable in rotation about an axis and are mechanically coupled by coupling means imposing between a rotation speed ω1 of the first momentum wheel and a rotation speed ω2 of the second momentum wheel a ratio R=ω2/ω1, negative on the one hand and continuously modifiable by the coupling means in response to a command on the other hand so as to modify the total angular momentum of the actuator while the total kinetic energy of the wheels are kept constant. In one embodiment, both momentum wheels have the same inertia and are coupled through a toroidal variable rotation speed drive, where ratio R varies between −3 and −⅓. The motor drives the momentum wheels and operates as a generator for braking the momentum wheels.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.