A system for enhancing movement of a multi-engine flight vehicle about either of pitch or yaw axes. The engines are oriented relative the centerline of the flight vehicle and a portion of the engines have a positive tangential cant and the remaining engines have a negative tangential cant. The attit
A system for enhancing movement of a multi-engine flight vehicle about either of pitch or yaw axes. The engines are oriented relative the centerline of the flight vehicle and a portion of the engines have a positive tangential cant and the remaining engines have a negative tangential cant. The attitude of the flight vehicle about the pitch, yaw and roll axes is controlled by differentially throttling the multi-engine flight vehicle.
대표청구항▼
1. A system for providing enhanced control of a flight vehicle about either the pitch or yaw axes during flight, comprising: a first plurality of engines of the flight vehicle having a positive tangential cant such that a thrust line from each of the first plurality of engines is misaligned with a c
1. A system for providing enhanced control of a flight vehicle about either the pitch or yaw axes during flight, comprising: a first plurality of engines of the flight vehicle having a positive tangential cant such that a thrust line from each of the first plurality of engines is misaligned with a centerline of the flight vehicle in a tangential direction with respect to a circumference of the flight vehicle; anda second plurality of engines of the flight vehicle having a negative tangential cant such that a thrust line from each of the second plurality of engines is misaligned with the centerline of the flight vehicle in a tangential direction with respect to a circumference of the flight vehicle and opposite to the first plurality of engines, wherein the first and second plurality of engines are spaced equidistant from one another and from the centerline of the flight vehicle, each of the first plurality of engines alternately positioned relative to each of the second plurality of engines, and the first and second plurality of engines configured for differential throttling to control attitude of the flight vehicle about pitch, yaw and roll axes wherein the positive and negative tangential cants of the first and second plurality of engines enhance movement of the flight vehicle about one of the pitch and yaw axes. 2. The system of claim 1, wherein the positive and negative tangential cants of the first and second plurality of engines diminish movement of the flight vehicle about the other one of the pitch and yaw axes due to the positive and negative tangential cants of the first and second plurality of engines. 3. The system of claim 1, wherein at least one of the first plurality of engines and at least one of the second plurality of engines are configured to operate at a first thrust level and at least one other of the first plurality of engines and at least one other of the second plurality of engines are configured to operate at a second thrust level that is different from the first thrust level. 4. The system of claim 3, wherein the flight vehicle performs at a level of maneuverability about one of the pitch and yaw axes with the first and second plurality of engines having the positive and negative tangential cants, and wherein more thrust than at least one of the first thrust level and the second thrust level would be required for the flight vehicle to perform at the level of maneuverability about one of the pitch and yaw axes without the first and second plurality of engines having the positive and negative tangential cants. 5. The system of claim 1, wherein engine centerlines of both the first and second plurality of engines are misaligned by about 2 degrees to about 10 degrees relative to the centerline of the flight vehicle. 6. The system of claim 1, wherein engine centerlines of both the first and second plurality of engines are misaligned by about 5 degrees relative to the centerline of the flight vehicle. 7. The system of claim 1, further comprising a moment partially defined by a directional cosine relative to the centerline of the flight vehicle and an engine centerline of each of the first and second plurality of engines. 8. The system of claim 1, wherein the first plurality of engines includes two engines with the positive tangential cant and the second plurality of engines includes two engines with the negative tangential cant. 9. The system of claim 1, wherein the first and second plurality of engines are fixed relative the centerline of the flight vehicle. 10. The system of claim 1, wherein the first and second plurality of engines are not dynamically canted during flight. 11. The system of claim 1, wherein the flight vehicle is without gimbaling. 12. The system of claim 1, wherein a center of mass of the vehicle corresponds with the centerline of the flight vehicle. 13. The system of claim 1, wherein the first and second plurality of engines are forward of a center of mass of the flight vehicle. 14. The system of claim 1, wherein the first and second plurality of engines are behind a center of mass of the flight vehicle. 15. The system of claim 1, wherein the flight vehicle is an air launched vehicle. 16. The system of claim 1, wherein the flight vehicle is a ground launched vehicle. 17. The system of claim 1, wherein the vehicle is a symmetric flight vehicle. 18. A method for enhancing one of pitch and yaw control of a flight vehicle during flight, the method comprising: determining a preferred maneuver axis of the flight vehicle;in response to determining a preferred maneuver axis, configuring a first and second plurality of engines of the flight vehicle by: alternately positioning the first and second plurality of engines of the flight vehicle relative to one another;tangentially canting the first plurality of engines of the flight vehicle to have a positive tangential cant relative a circumference of the flight vehicle such that thrust lines of the first plurality of engines are not parallel to a centerline of the flight vehicle; andtangentially canting the second plurality of engines of the flight vehicle to have a negative tangential cant relative a circumference of the flight vehicle and opposite to the first plurality of engines such that thrust lines of the second plurality of engines are not parallel to the centerline of the flight vehicle; anddifferentially throttling the first and second plurality of engines to control attitude of the flight vehicle about pitch, yaw and roll axes. 19. The method of claim 18, further comprising diminishing movement of the flight vehicle about an axis other than the preferred maneuver axis. 20. The method of claim 18, wherein configuring the first and second plurality of engines further comprises eliminating roll about the centerline of the flight vehicle with the positive tangential cant of the first plurality of engines counteracting the negative tangential cant of the second plurality of engines. 21. The method of claim 18, wherein tangentially canting the first and second plurality of engines comprises misaligning thrust lines of the first and second plurality of engines by about 2 degrees to about 10 degrees relative to the centerline of the flight vehicle. 22. The method of claim 18, wherein tangentially canting the first and second plurality of engines comprises misaligning thrust lines of the first and second plurality of engines by about 5 degrees relative to the centerline of the flight vehicle. 23. The method of claim 18, further comprising operating at least one of the first plurality of engines and at least one of the second plurality of engines at a first thrust level and at least one other of the first plurality of engines and at least one other of the second plurality of engines at a second thrust level that is different from the first thrust level. 24. The method of claim 23, wherein the flight vehicle performs at a level of maneuverability about one of the pitch and yaw axes with the first and second plurality of engines having the positive and negative tangential cants, and wherein more than at least one of the first thrust level and the second thrust level would be required for the flight vehicle to perform at the level of maneuverability about one of the pitch and yaw axes without the first and second plurality of engines having the positive and negative tangential cants. 25. The method of claim 18, wherein tangentially canting the first and second plurality of engines comprises generating a moment partially defined by a directional cosine relative the centerline of the flight vehicle and an engine centerline of each of the first and second plurality of engines. 26. The method of claim 18, wherein tangential canting the first and second plurality of engines comprises generating a moment, relative the centerline of the flight vehicle, that is partially defined by a directional cosine, and that is greater than if the first and second plurality of engines were without tangential canting. 27. A system for providing enhanced control of a flight vehicle about one of pitch and yaw axes during flight, comprising: a first plurality of engines of the flight vehicle having a positive tangential cant relative a circumference of the flight vehicle such that thrust lines from the first plurality of engines are not parallel to a centerline of the flight vehicle; anda second plurality of engines of the flight vehicle having a negative tangential cant relative a circumference of the flight vehicle and opposite to the first plurality of engines such that thrust lines from the second plurality of engines are not parallel to the centerline of the flight vehicle, wherein the first and second plurality of engines are alternately positioned relative to one another,wherein the flight vehicle has a center of mass substantially corresponding with the centerline of the flight vehicle,wherein the tangential canting of the first and second plurality of engines generates a moment partially defined by directional cosines relative the centerline of the flight vehicle and an engine centerline of each of the first and second plurality of engines, andwherein the first and second plurality of engines are differentially throttled to control attitude of the flight vehicle about pitch, yaw and roll axes. 28. The system of claim 27, wherein the first and second plurality of engines are fixed relative to the centerline of the flight vehicle to preclude dynamic canting during flight.
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이 특허에 인용된 특허 (13)
Sackheim, Robert L.; Hutt, John J.; Anderson, William E.; Dressler, Gordon A., Axisymmetric, throttleable non-gimballed rocket engine.
Kiebles, Steven Louis; Lax, David Michael; Darias, Otto Y; Darnell, Mark Lawrence; Hwang, Sean Sanghyun; Holbert, Christopher Daniel; Mathews, Jr., Harry Kirk; Adibhatla, Sridhar; Bult, Jeffrey Russell; Swager, Thomas Charles, Controlling aircraft using thrust differential trim.
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