Reduced fin span thrust vector controlled pulsed tactical missil

Details Reduced fin span thrust vector controlled pulsed tactical missil Reduced fin span thrust vector controlled pulsed tactical missil

1988-08-17

1989-09-19

Kyle, Deborah L.

Aeronautics and astronautics

Missile stabilization or trajectory control

Automatic guidance

244 324, 23926519, F42B 15027, F42B 15033

Patent

active

048673935

ABSTRACT:
A tactical pulsed missile with a movable nozzle for thrust vector control and movable aerofins to provide greater maneuverability and flexibility. The first pulse is fired at launch and the later pulses are fired as needed whereby steerage may be provided by thrust vector control during the firing of the pulses. When none of the pulses are firing, steerage may be provided by the movable aerofins. The missile is provided with separate small electromechanical actuators for each of the aerofins and each of the movable nozzle axes which are preferably placed closely adjacent the respective aerofins and nozzle so that the weight and space of various linkages may be eliminated. The motors are provided with a source of high voltage so that their size may be reduced whereby they burn up when the high voltage is applied for a short period of time but not before their task has been achieved. The fin span is reduced to less than about four inches to enable the packaging of a greater number of such tactical missiles in the payload bay of an airplane. A flexible bearing may be provided between the nozzle and nozzle housing. An elastomeric material may be provided between and bonded to the nozzle and nozzle housing to prevent the ingestion of exhaust and debris into the space therebetween.

REFERENCES:
patent: 2996267 (1961-08-01), Warren
patent: 4044970 (1977-08-01), Maudal
patent: 4163534 (1979-08-01), Seeger
patent: 4560121 (1985-12-01), Terp
patent: 4709877 (1987-12-01), Goulding

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