RADIAL BLEED TOTAL THRUST CONTROL APPARATUS AND METHOD FOR A ROCKET PROPELLED MISSILE
Assignee
PROPULSION RESEARCH, INC.
Filed
Nov 15, 1988
Granted
Jul 2, 1991
Location
SPRINGFIELD VA US
Abstract
A radial bleed total thrust control system for a rocket propelled missile. In the preferred embodiment, the apparatus employs at least two pairs of straight radial nozzles which are disposed within and penetrate the skin of the missile and at least two pairs of tangentially canted radial nozzles which are also disposed within and penetrate the skin of the missile to provide control moments necessary to control the pitch, yaw, roll and/or the axial thrust of the missile. In one embodiment the radial and tangential nozzles are supplied by the same source of propelling gas as the main thrust nozzle, and in a second embodiment the straight radial and tangentially canted radial nozzles have a separate gas supply source.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Mar 24, 1989
Rescinded
Jan 19, 1990
Duration
10 months
Inventor
- 1CARL W. ANDERSON
Record Details
- Patent number
- US 5028014
- Application
- 07271504
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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