Spacecraft payload ejection system
US10513354B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 12, 2019 |
| Grant date | Dec 24, 2019 |
| Priority date | — |
| Expiry date | Jul 12, 2039 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/6457
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
There is disclosed a Payload Ejection System (PES) able to store any set of payloads for launch and eject that set of payloads at a controlled speed with a low tumble rate while accommodating any offset centre of mass within a restricted volume. The need for ballasting or balancing is eliminated thus freeing up the design space for these payloads. Insensitivity to centre of mass location is enabled by the use of a deployment hinge assembly arrangement which uses two or more non-parallel folding hinge arrangements that allow for linear motion of the output link in one direction while restricting the motion all other directions. One embodiment of the current PES concept uses four (4) hinge panel assemblies, selected to provide optimal stiffness around the entire mechanism. The stiffness of the PES is integral to managing offset centre-of-mass locations by allowing the mechanism to translate the effective force vector to the center of mass location.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.