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The roll orientation of a thrust vector control (TVC) or other missile section is measured and used to compensate the operation of the control surface. A measurement of a roll orientation of the control surface relative to the missile is obtained from a detector, memory or other source. Compensated

The roll orientation of a thrust vector control (TVC) or other missile section is measured and used to compensate the operation of the control surface. A measurement of a roll orientation of the control surface relative to the missile is obtained from a detector, memory or other source. Compensated control commands are determined at least in part based upon the measurement to account for the roll orientation of the control surface relative to the missile, and the compensated control command is provided to thereby actuate the control surface during operation of the missile.

대표청구항 ▼

1. A method to operate a control surface of a projectile, the method comprising: obtaining a measurement of a roll orientation of the control surface relative to the projectile as an angular position of a structure that houses the control surface with respect to a roll axis of the projectile;generat

1. A method to operate a control surface of a projectile, the method comprising: obtaining a measurement of a roll orientation of the control surface relative to the projectile as an angular position of a structure that houses the control surface with respect to a roll axis of the projectile;generating a compensated control command to actuate the control surface, wherein the compensated control command is determined at least in part based upon the received measurement to account for the roll orientation of the control surface relative to the projectile; andproviding the compensated control command to thereby actuate the control surface during operation of the projectile. 2. The method of claim 1 wherein the obtaining comprises receiving an input from a detector that measures the roll orientation of the control surface relative to the projectile. 3. The method of claim 1 wherein the obtaining comprises determining the roll orientation of the control surface relative to the projectile by initially actuating the control surface and monitoring a reaction to the initial actuation by the projectile during flight of the projectile, and wherein the compensated control command is generated during subsequent flight of the projectile after the measurement is obtained. 4. The method of claim 1 wherein the obtaining comprises detecting an optical code on the structure that houses the control surface and that is coupled to the projectile. 5. The method of claim 1 wherein the structure is coupled to the projectile by a threaded joint. 6. The method of claim 1 wherein the projectile includes a rocket motor that is configured to produce thrust gases, said structure comprising a rocket motor exit cone that houses the control surface that is actuatable to extend into the thrust gases and thereby chance a heading of the projectile. 7. The method of claim 6 wherein the compensated control command is adjusted to compensate for the angular position of the exit cone relative to the projectile. 8. The method of claim 7 wherein the compensated control command is adjusted by performing a coordinate system transformation based upon the angular position of the exit cone relative to the projectile. 9. The method of claim wherein the obtaining, generating and providing, are performed by a digital controller located within the projectile. 10. The method of claim 1 further comprising storing the measurement of a roll orientation of the control surface relative to the projectile in a memory located within the projectile, and wherein the obtaining comprises retrieving the stored measurement from the projectile. 11. A missile comprising: a missile body housing a rocket motor that is configured to produce thrust gases;an exit cone coupled to the missile body and having a roll orientation relative to the missile body, wherein the exit cone comprises a control surface that is actuatable to extend into the thrust gases and thereby change a heading of the missile; anda controller configured to obtain a measurement of the roll orientation of the exit cone as an angular position of the exit cone with res sect to a roll axis of the missile body, to generate a control command to actuate the control surface that is compensated for the measured roll orientation of the exit cone, and to provide the compensated control command to thereby actuate the control surface and thereby change the heading of the missile. 12. The missile of claim 11 wherein the missile further comprises a detector configured to measure the roll orientation of the exit cone with respect to the missile body, and wherein the controller obtains the measurement of the roll orientation of the exit cone from the detector. 13. The missile of claim 11 wherein the exit cone is coupled to the missile body by a threaded joint, and wherein the measurement is obtained after the exit cone and missile body are coupled to each other by the threaded joint. 14. The missile of claim 11 Wherein the exit cone comprises a pattern on at least a portion of its outer surface, and wherein the missile further comprises an optical reader configured to provide an indication of the pattern as the measurement of the roll orientation of the exit cone. 15. The missile of claim 11 wherein the controller is further configured to initially actuate the control surface during operation of the missile, to detect a response to the initial actuation during flight, of the missile, and to determine the roll orientation of the exit cone based upon the detected response. 16. The missile of claim 11 further comprising a memory, and wherein the controller is configured to obtain the measurement of the roll orientation from the memory. 17. A missile comprising: a missile body housing an engine configured to produce thrust gases;an exit cone coupled to the missile body by a threaded joint and having roll orientation relative to the missile body that is dependent at least in part upon the threaded joint, and wherein the exit cone comprises a thrust control vector mechanism with a plurality of control surfaces that are each actuatable to extend into the thrust gases and thereby change a heading of the missile;a detector configured to provide a measurement of a roll orientation of the exit cone relative to the missile body as an angular position of the exit cone with respect to a roll axis of the missile body; anda controller configured to receive the measurement of the roll orientation of the exit cone from the detector, to generate a plurality of control commands to actuate each of the plurality of control surfaces, wherein each of the control commands is compensated at least in part based upon the measurement of the roll orientation of the exit cone, and to provide the compensated control commands to thereby actuate the control surfaces and thereby change the heading of the missile. 18. The missile of claim 17 wherein the exit cone comprises a pattern on at least a portion of its outer surface, and wherein the detector is an optical reader configured to provide an indication of the pattern as the measurement of the roll orientation of the exit cone. 19. The missile of claim 18 wherein the optical reader measures the roll orientation by determining a portion of the pattern that is proximate the optical reader. 20. The missile of claim 17 wherein the control commands are adjusted by performing a coordinate system transformation based upon the angular position of the exit cone relative to the missile body. 21. A method to operate a control surface of a projectile, the method comprising; obtaining a measurement of a roll orientation of the control surface relative to the projectile as an angular position of a structure that houses the control surface with respect to a roll axis of the projectile;generating a compensated control command to actuate the control surface, wherein the compensated control command is determined at least in part based upon the received measurement to account for the roll orientation of the control surface relative to the projectile;using a control function to produce a command signal for the control surface in response to applied commands;compensating the command signal with the compensated control command to produce a compensated command signal; andproviding the compensated command signal to thereby actuate the control surface during operation of the projectile. 22. A method to operate control surfaces of a projectile, said projectile having a rocket motor configured to produce thrust gases and a rocket motor exit cone comprising a plurality of control surfaces that are each actuable to extend into the thrust gases and thereby change a heading of the projectile, the method comprising: obtaining a measurement of a roll orientation of the control surfaces relative to the projectile as an angular position of the rocket motor exit cone with respect to a roil axis of the projectile;generating a compensated control command to actuate the control surface, wherein the compensated control command is determined at least in part based upon the received measurement to account fur the roll orientation of the control surface relative to the projectile;using a control function to produce command signals for the control surfaces in response to applied commands;compensating the command signals with the compensated control command to produce compensated command signals that account for angular misalignment of the rocket motor exit cone to the projectile; andproviding the compensated command signal to thereby actuate the control surfaces during operation of the projectile. 23. The method of claim 22 wherein the command signal is compensated by performing a coordinate system transformation based upon the angular position of the exit cone with respect to the roll axis of the projectile. 24. The method of claim 22, wherein the exit cone is threaded onto the projectile with an arbitrary roll orientation with respect to the roll axis of the projectile.