ROCKET PROJECTILES
Assignee
Filed
Dec 12, 1968
Granted
Aug 9, 1988
Location
Abstract
A control system for a guided missile includes means for rotating the missile about its axis, a discharge nozzle so directed that its thrust exerts a lateral force on the missile and an associated reaction motor arranged to deliver, in response to a suitable signal, a thrust of suitable timing and duration to correct the missile trajectory. A suitable reaction motor has a combustion chamber in communication with the discharge nozzle by way of a relief valve, a compressible fuel tank pressurized by gases from the combustion chamber by way of a differential piston pump actuable by the combustion gases and controlled by a command operable, solenoid actuated valve, and means for initially heating and pressurizing the combustion chamber.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Dec 18, 1981
Rescinded
Mar 17, 1988
Duration
6 years, 3 months
Record Details
- Patent number
- US 4762293
- Application
- 04785046
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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