Missile control surface actuator system

Claim 2

A missile control surface actuator system for controlling and steering fins on a missile, the actuator system comprising: a high pressure gas source; a high pressure manifold connected to the gas source; a pressure regulator connected between the high pressure source and the high pressure manifold for regulating the amount of high pressure gas to the manifold; a first and second fill line connected at one end to the manifold; a first and second fill valve connected in the first and second fill lines for controlling the amount of gas received from the manifold the first and second fill valves each operating independently of each other, an actuator housing connected to the other end of the first and second fill lines, the actuator having an actuator vane connected to an actuator shaft, the vane rotating the shaft when gas is received in the housing, the shaft is directly connected to one of the missile's fins for controlling and steering the missile; a first and second vent valve connected to a first and second vent lines, the first and second vent lines connected to the actuator housing for discharging gas from the housing; and an electrical control system connected to the first and second fill valves, first and second vent valves and the regulator for opening and closing the valves and controlling the amount of gas received and discharged from the actuator housing.

Claim 3

The system as described in claim 1 wherein the first fill valve and the first vent valve is a two-way valve and the second fill valve and the second vent valve is a two way valve.

Claim 4

The system as described in claim 1 wherein the first fill line is received in the actuator housing on one side of the actuator vane, the second fill line is received in the actuator housing on the opposite side of the actuator vane and the first vent line is received in the actuator housing on the opposite side of the actuator vane from the second vent line received in the actuator housing.

Claim 5

The system as described in claim 1 further including spring biasing means mounted on the actuator housing for urging the missile fin outwardly from a retracted position to deployed position.

Claim 6

A missile control surface actuator system for controlling and steering fins on a missile, the actuator system comprising: a high pressure gas source; a high pressure manifold connected to the gas source; a pressure regulator connected between the high pressure source and the high pressure manifold for regulating the amount of high pressure gas to the manifold; a first and second fill line connected at one end to the manifold; a first and second fill valve connected in the first and second fill lines for controlling the amount of gas received from the manifold; an actuator housing connected to the other end of the first and second fill lines, the actuator having an actuator vane connected to an actuator shaft, the vane rotating the shaft when gas is received in the housing, the shaft is directly to one of the missile's fins for controlling and steering the missile, a first and second vent valve connected to a first and second vent lines, the first and second vent lines connected to the actuator housing for discharging gas from the housing, the first fill valve and first vent valve is a two-way valve and the second fill valve and second vent valve is a two-way valve, the valves each operating independently of each other; an electrical control system connected to the first and second fill valves, the first and second vent valves and the regulator for opening and closing the valves and controlling the amount of gas received and discharged from the actuator housing; and a potentiometer attached to the actuator shaft and the control system for providing feedback of shaft rotation and thus fin rotation to the control system.

Claim 7

A missile control surface actuator system for controlling and steering fins on a missile, the actuator system comprising: a high pressure gas source; a high pressure manifold connected to the gas source; a pressure regulator connected between the high pressure source and the high pressure manifold for regulating the amount of high pressure gas to the manifold; a first and second fill line connected at one end to the manifold; a first and second fill valve connected in the first and second fill lines for controlling the amount of gas received from the manifold; an actuator housing connected to the other end of the first and second fill lines, the actuator having an actuator vane connected to an actuator shaft, the vane rotating the shaft when gas is received in the housing, the shaft is directly to one of the missile's fins for controlling and steering the missile, a first and second vent valve connected to a first and second vent lines, the first and second vent lines connected to the actuator housing for discharging gas from the housing, the first fill valve and first vent valve is a two-way valve and the second fill valve and second vent valve is a two-way valve, the valves each operating independently of each other; an electrical control system connected to the first and second fill valves, the first and second vent valves and the regulator for opening and closing the valves and controlling the amount of gas received and discharged from the actuator housing; and a potentiometer attached to the actuator shaft and the control system for providing feedback of shaft rotation and thus fin rotation to the control system.