High-energy to low-energy orbit transfer vehicle
US6409124B1 · kind B1 · utility
Inventor
Key dates
| Filing date | Jun 13, 2001 |
| Grant date | Jun 25, 2002 |
| Priority date | — |
| Expiry date | Jun 13, 2021 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/641
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
The excess space and weight capacity of a conventional launch vehicle for a high-energy orbit, such as GEO, is used to deploy satellites to a low-energy orbit, such as LEO. In a preferred embodiment, an orbit-transfer vehicle provides the navigation, propulsion, and control systems required to transport a payload satellite from a high-energy-transfer orbit, such as GTO, to a predetermined low-energy orbit. Upon entering the low-energy orbit, the payload satellite is released from the orbit-transfer vehicle. To reduce the fuel requirements for this deployment via the orbit-transfer vehicle, a preferred embodiment includes aerobraking to bring the satellite into a low-earth orbit. In a preferred embodiment of this method of deployment, the provider of the orbit-transfer vehicle identifies and secures available excess capacity on launch vehicles, and allocates the excess capacity to the satellites requiring low-earth orbit deployment, thereby providing a deployment means that is virtually transparent to the purchaser of this deployment service.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.