초록 ▼

A retractable thrust vector control system (10) for a rocket motor (26) that can generate an exhaust plume comprises at least one control vane (12) connectable to an attitude control assembly (20) that rotates the vane (12) about a control axis (44). The system also includes a retraction mechanism

A retractable thrust vector control system (10) for a rocket motor (26) that can generate an exhaust plume comprises at least one control vane (12) connectable to an attitude control assembly (20) that rotates the vane (12) about a control axis (44). The system also includes a retraction mechanism (14) for withdrawing the control vane (12) along the control axis (44) from an extended position at least partially within a path of a rocket exhaust plume and a retracted position substantially out of a path of a rocket exhaust plume.

대표청구항 ▼

What is claimed is: 1. A retractable thrust vector control system for a rocket motor that generates an exhaust plume, comprising a control vane connected to an attitude control assembly, where the control assembly rotates the control vane about a control axis to control the attitude of the control

What is claimed is: 1. A retractable thrust vector control system for a rocket motor that generates an exhaust plume, comprising a control vane connected to an attitude control assembly, where the control assembly rotates the control vane about a control axis to control the attitude of the control vane, and a retraction mechanism for withdrawing the control vane in a direction along the control axis from an extended position at least partially within a path of the rocket exhaust plume to a retracted position substantially out of the path of the rocket exhaust plume. 2. A system as set forth in claim 1, wherein the retraction mechanism includes an actuator for moving the control vane toward the retracted position. 3. A system as set forth in claim 2, wherein actuator includes a spring. 4. A system as set forth in claim 3, wherein the spring is a compression spring. 5. A system as set forth in claim 2, wherein the control vane is mounted on a shaft, the shaft is supported by a pair of bearing towers, and the shaft includes a stop that acts against a bearing tower to stop the control vane at the retracted position. 6. A system as set forth in claim 2, wherein the actuator includes a biasing device for biasing the control vane toward the retracted position. 7. A system as set forth in claim 1, wherein the retraction mechanism includes a movable element having a hold position where the control vane is held in the extended position and moves to a release position where the control vane is allowed to move from the extended position. 8. A system as set forth in claim 7, wherein the control vane is mounted on a shaft, the retraction mechanism includes a biasing device for biasing the control vane toward the retracted position, and the movable element includes a circumferential bearing ring having an aperture therein for receipt of a distal end of the shaft, whereby upon rotation of the ring to align the aperture with the shaft, the biasing device will move the shaft into the aperture, thereby withdrawing the control vane from the path of the rocket exhaust plume. 9. A system as set forth in claim 8, wherein the bearing ring is driven by a prime mover connected to the bearing ring via a control arm extending from the bearing ring. 10. A system as set forth in claim 9, wherein the prime mover is an electric motor or an electro-explosive piston actuator or a solenoid. 11. A system as set forth in claim 1, wherein the control vane is mounted on a shaft that extends along the control axis, the shaft having a crank arm extending transverse to the control axis that is connected to the control assembly. 12. A system as set forth in claim 1, including a plurality of circumferentially spaced control vanes, wherein the control axis of each control vane extends along a radial axis. 13. A system as set forth in claim 12, including four control vanes. 14. A system as set forth in claim 1, wherein the control vane is rotatable about a control axis extending transverse to the expected direction of the exhaust plume. 15. A system as set forth in claim 1, further comprising an attitude control assembly connected to the control vane. 16. A missile having a rocket motor for propelling the missile that generates an exhaust plume, and a system as set forth in claim 1 mounted to the rocket motor. 17. A system as set forth in claim 1, wherein the control vane is mounted on a shaft that extends along the control axis, the shaft is supported by a pair of bearing towers, the shaft has a crank arm extending transverse to the control axis that is connected to the control assembly, and a spring is interposed between the crank arm and one of the bearing towers to bias the control vane toward the retracted position. 18. A method of operating a thrust vector control system, comprising the steps of controlling a plurality of control vanes extending into a path of a rocket motor exhaust plume by rotating the vanes along respective control axes, and retracting the control vanes along respective control axes to remove the control vanes from the path of the exhaust plume, wherein the control vanes are arranged circumferentially around the path of the exhaust plume and the retracting step includes rotating a ring that is radially outward of the control vanes. 19. A method as set forth in claim 18, including the step of stopping the control vanes at a retracted position out of the path of the exhaust plume. 20. A retractable thrust vector control system for a rocket motor that generates an exhaust plume, comprising a control vane connected to means for controlling the attitude of the control vane by rotating the control vane about a control axis, and means for withdrawing the control vane in a direction along the control axis from an extended position at least partially within a path of the rocket exhaust plume and a retracted position substantially out of the path of the rocket exhaust plume.