Thrust vector control using electric actuation
- Marshall Space Flight Center, Marshall Space Flight Center, Alabama 35812 (United States)
Presently, gimbaling of launch vehicle engines for thrust vector control is generally accomplished using a hydraulic system. In the case of the space shuttle solid rocket boosters and main engines, these systems are powered by hydrazine auxiliary power units. Use of electromechanical actuators would provide significant advantages in cost and maintenance. However, present energy source technologies such as batteries are heavy to the point of causing significant weight penalties. Utilizing capacitor technology developed by the Auburn University Space Power Institute in collaboration with the Auburn CCDS, Marshall Space Flight Center (MSFC) and Auburn are developing EMA system components with emphasis on high discharge rate energy sources compatible with space shuttle type thrust vector control requirements. Testing has been done at MSFC as part of EMA system tests with loads up to 66000 newtons for pulse times of several seconds. Results show such an approach to be feasible providing a potential for reduced weight and operations costs for new launch vehicles. {copyright} 1995 {ital American} {ital Institute} {ital of} {ital Physics}
- Sponsoring Organization:
- USDOE
- OSTI ID:
- 165145
- Journal Information:
- AIP Conference Proceedings, Vol. 325, Issue 1; Other Information: PBD: 25 Jan 1995
- Country of Publication:
- United States
- Language:
- English
Similar Records
Single-stage-to-orbit performance enhancement from take-off thrust augmentation
A conceptual design tool for RBCC engine performance analysis