Expendable launch vehicle
US6360993B1 · kind B1 · utility
Assignee
Inventor
Key dates
| Filing date | Apr 9, 1999 |
| Grant date | Mar 26, 2002 |
| Priority date | — |
| Expiry date | Apr 9, 2019 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K9/58
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A system for supplying a space station or satellite comprises a low cost expendable single-stage to orbit launch vehicle having a moderate reliability in the range of about 0.5 to 0.8 for launching a payload of consumable items to low earth orbit. For propulsion, the launch vehicle includes a pressure-fed rocket engine, preferably with a nozzle for aiming products of combustion in a direction away from the launch vehicle and having a fixed orientation relative to the launch vehicle. A pressurant tank contains an inert pressurant gas under pressure. A conduit system serves to introduce the inert pressurant gas from the pressurant tank to a fuel tank and thence to the rocket engine and also to introduce the inert pressurant gas from the pressurant tank to an oxidizer tank and thence to the rocket engine for combustion with the fuel. The initial pressure in the pressurant tank is maintained at a level in excess of about 100 bar; the initial pressure in the fuel tank and in the oxidizer tank is maintained at a level in the range of about 8.5 to 20.0 bar; and the initial pressure in the rocket engine is maintained at a level in the range of about 5 to 10 bar. Additional conduits are pro…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.