Aerodynamic control mechanism for thrust vector control

• US 4,272,040 A
• Filed: 07/14/1978
• Issued: 06/09/1981
• Est. Priority Date: 07/14/1978
• Status: Expired due to Term

• Current Assignee: Hughes Missile Systems Company
• Original Assignee: General Dynamics
• Inventors: Bastian, Thomas W., Lacy, Garry T., Vink, John J.
• Primary Examiner(s): BROWN, DAVID
• Application Number:
  US05/924,594
• Time in Patent Office: 1,061 Days
• Field of Search: 244/3.21, 244/3.22, 244/3.29, 244/3.1, 239/265.19, 60/230, 74/675
• US Class Current: 244/3.22
• CPC Class Codes: F02K 9/90 using deflectors F02K9/82 takes precedence
• CPC Class Codes: F05D 2200/11 Sum
• CPC Class Codes: F42B 10/665 characterised by using a nozzle provided with at least a deflector mounted within the nozzle

Abstract

A rocket thrust vector control system including jet tabs and aerodynamic control surfaces is disclosed. The control system removes roll information present in commands to the aerodynamic surfaces and provides only pitch and yaw information to the jet tabs for the thrust vector control. The roll information is removed by a geared summing mechanism. The resulting pitch and yaw output is used to drive the thrust vector control jet tabs. The same powered actuators are used for both the aerodynamic control surfaces and the jet tabs.

Claims

1. An attitude control system for a rocket propelled missile comprising:

a cylindrical missile body;

rocket propulsion means acting along the axis of the body to propel the missile;

a plurality of control elements pivotably mounted external to the body, each being pivotable about an axis normal to the cylindrical surface of the missile body for aerodynamically controlling direction of the missile in flight;

a servo motor associated with each control element for controlling the angular position of the control elements relative to the missile body;

control circuitry for activating the servo motors to control the flight of the missile;

a plurality of thrust vector control jet tabs for providing pitch and yaw moments by deflecting the rocket exhaust gas;

a plurality of geared summing actuators, each for rotating two of said tabs, each geared summing actuator including;

means for receiving pitch or yaw commands or combinations thereof and for receiving roll commands provided to said fins; and

gear means for removing the roll component from the commands while retaining the pitch and yaw components and actuating a selected one of said tabs with the resultant command.

2. The control system of claim 1 wherein said geared summing actuators further include delay means effective to delay the rotation of the selected tab until the associated control element has pivoted a fixed amount.

3. The control system of claim 2 wherein the delay means includes a keyed shaft cooperating with a slotted cylinder wherein the key moves within the slot prior to contacting an inner surface of the slot to effect rotation of the tab.

4. The control system of claim 1 wherein there are two pairs of control elements, each spaced equidistant around the missile body.

5. The control system of claim 4 wherein there are two actuators, and each actuator further includes a pair of driven gears, each pair of gears being driven by one of the opposed pair of control elements.

6. The apparatus of claim 5 wherein a third geared member is interspersed between said pair of driven gears, is driven thereby and is further interconnected with said tabs.

7. The control system of claim 5 wherein said actuators further include delay means effective to delay the actuation of said one tab until after pivoting of said control elements is effected through a predetermined arc.

8. The control system of claim 7 wherein the delay means includes a keyed shaft cooperating with a slotted cylinder wherein the keys move within the slot prior to contacting the surface of the slot to effect rotation of the tab.

9. An attitude control system for a rocket propelled missile conprising:

a cylindrical missile body;

rocket propulsion means acting along the axis of the body to propel the missile;

four fins pivotably mounted to and disposed symmetrically and exteriorly of the body and each being pivotable about an axis normal to the cylindrical surface of the missile body for aerodynamically controlling directions of the missile in flight, each pair of two fins being disposed opposite to each other;

a servo motor associated with each fin for controlling the angular position of the fin relative to the missile body;

control circuitry for commanding the servo motors to control the flight of the missile;

a plurality of thrust vector control jet tabs for providing pitch and yaw moments by deflecting rocket exhaust gas;

actuator means interconnected with said tabs including;

means for receiving commands from said circuitry;

two sets of ring gears arranged to turn in parallel planes, one of said sets receiving pitch commands and the other receiving yaw commands, and both receiving roll commands provided by said circuitry to said servo motors, each ring gear having gear teeth on the faces between the two ring gears and being connected to one of said pair of two opposite fins so that pitch or yaw servo commands cause said ring gears to rotate in the same direction, while roll commands cause the rotation of said ring gears in opposite directions;

a pair of summing rings arranged to turn in a plane parallel to the ring gear planes, one of each of said summing rings being disposed between each set of ring gears and having a plurality of planetary gears turning on axes radiating from the center of the summing ring, each planetary gear engaging gear teeth on the face of a ring gear, and arranged so that the summing ring does not rotate in response to equal but opposite rotation of said ring gears but does rotate in response to rotation of said ring gears in the same direction, said summing rings having gear teeth on their circumference; and

a tab shaft connected at one end to an associated tab and having a gear at the other end interconnecting with said circumferential gear teeth on one of said summing rings, whereby said tab is rotatable in and out of the missile exhaust gas flow in response to rotation of the summing ring.

10. The control system of claim 9 wherein each tab shaft has at least one key radiating from the shaft and mating with the associated tab, said associated tab having at least one key stop, said key being effective to rotate the tab into the missile exhaust flow when turned in one direction and not effective to rotate said tab into the aerodynamic air flow beyond the skin of the missile when rotated in the opposite direction.

11. The control system of claim 10 further including spring means effective to rotate the tab away from exhaust gas flow when not rotated thereinto by said key.

12. The control system of claim 11 wherein said key and key stop further includes delay means effective to delay the actuation of said one tab until after pivoting of said fins is effected through a predetermined arc.

13. The control system of claim 12 wherein the keys move adjacent the stop prior to contacting the stop to effect rotation of the tab.