IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0326751
(2002-12-20)
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발명자
/ 주소 |
- Malmuth, Norman D.
- Fedorov, Alexander
- Shalaev, Vladimir
- Zharov, Vladimir
- Shalaev, Ivan
- Maslov, Anatoly
- Soloviev, Victor
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인용정보 |
피인용 횟수 :
17 인용 특허 :
24 |
초록
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The present invention provides a system and method for rapidly and precisely controlling vortex symmetry or asymmetry on aircraft forebodies to avoid yaw departure or provide supplemental lateral control beyond that available from the vertical tail surfaces with much less power, obtrusion, weight an
The present invention provides a system and method for rapidly and precisely controlling vortex symmetry or asymmetry on aircraft forebodies to avoid yaw departure or provide supplemental lateral control beyond that available from the vertical tail surfaces with much less power, obtrusion, weight and mechanical complexity than current techniques. This is accomplished with a plasma discharge to manipulate the boundary layer and the angular locations of its separation points in cross flow planes to control the symmetry or asymmetry of the vortex pattern. Pressure data is fed to a PID controller to calculate and drive voltage inputs to the plasma discharge elements, which provide the volumetric heating of the boundary layer on a time scale necessary to adapt to changing flight conditions and control the symmetry or asymmetry of the pressures and vortices. In the case of yaw departure avoidance, the PID controller controls the plasma to adjust the separation points to angular locations around the forebody that provide a robustly stable symmetric vortex pattern on a time scale that the asymmetries develop. In the case of lateral control, the PID controller controls the plasma to adjust the separation points to angular locations around the forebody that provide an asymmetric vortex pattern that produces the desired supplementary lateral force and rolling moment.
대표청구항
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1. An aircraft, comprising:a forebody, andplasma discharge elements located to starboard and port on the forebody, said plasma discharge elements being adapted to generate a plasma to control a yawing moment on said forebody. 2. The aircraft of claim 1, wherein during flight a boundary layer separat
1. An aircraft, comprising:a forebody, andplasma discharge elements located to starboard and port on the forebody, said plasma discharge elements being adapted to generate a plasma to control a yawing moment on said forebody. 2. The aircraft of claim 1, wherein during flight a boundary layer separates at two points S + and S − as the air flow moves past the forebody and feeds itself into a pair of vortices, said plasma discharge elements being adapted to generate the plasma to control an angular location of separation points S + and S − to control the yawing moment on the forebody. 3. The aircraft of claim 2, wherein when maneuvering at sufficiently steep angles of attack said boundary layer may feed itself into a pair of asymmetric vortices causing yaw departure, said plasma discharge elements being adapted to generate the plasma to move the angular location of separation points S + and S − away from a line of symmetry in the forebody and towards an equatorial line to reduce the asymmetry of the vortices and mitigate against yaw departure. 4. The aircraft of claim 3, wherein the plasma discharge elements are adapted to generate the plasma to move the angular location of separation points S + and S − away from the line of symmetry in the forebody and towards the equatorial line to angular locations that provide a robustly stable symmetric vortex pattern that avoids yaw departure. 5. The aircraft of claim 2, further comprising a vertical tail with a rudder that is adapted to provide lateral control of the aircraft when maneuvering, said plasma discharge elements being adapted to generate the plasma to move the angular location of separation points S + and S − to control the asymmetry of the vortices to produce an additional yawing moment to supplement the lateral control provided by the vertical tail. 6. The aircraft of claim 5, wherein the plasma discharge elements are adapted to generate the plasma to move the angular location of separation points S + and S − toward the line of symmetry in the forebody and away from the equatorial line to angular locations that provide an asymmetric vortex pattern that produces a yawing moment. 7. The aircraft of claim 2, wherein the plasma discharge elements are adapted to generate the plasma to create a thermal gradient between the port and starboard sides of the forebody to control the angular locations of the separation points. 8. The aircraft of claim 2, wherein the plasma discharge elements are adapted to generate the plasma to produce a volumetric heating of the boundary layer on and above the surface of the forebody. 9. The aircraft of claim 2, wherein the plasma discharge elements are adapted to generate the plasma to heat the boundary layer on a time scale at least commensurate with changes in flight conditions to stabilize the angular locations of the separation points. 10. The aircraft of claim 2, further comprising additional plasma discharge elements adapted to generate a plasma that turbulizes the airflow about the forebody to further stabilize the vortices. 11. The aircraft of claim 10, wherein the additional plasma discharge elements are spark discharge elements. 12. The aircraft of claim 2, wherein the plasma discharge elements are selected from at least one of glow, corona, sliding, slipping or spark discharge elements. 13. The aircraft of claim 2, further comprising;pressure sensors located to starboard and port on the forebody that sense a pressure distribution around the forebody; anda closed-loop controller that controls the plasma discharge elements in response to the sensed pressure distribution to control the yawing moment. 14. The aircraft of claim 13, wherein the closed-loop controller estimates the required plasma by initially sensing the asymmetry from the pressure distribution and then manipulating the asymmetry by heating according to the solution of the compressible boundary layer equations wit h the plasma discharge elements to move the separation points. 15. The aircraft of claim 13, further comprising;sensors on the forebody that sense whether the flow is laminar or turbulent, andadditional plasma discharge elements adapted to generate a plasma that turbulizes the airflow about the forebody on both port and starboard sides, said closed-loop controlling selectively controlling the additional plasma discharge elements as needed to further stabilize the yawing moment. 16. An aircraft, comprising:a forebody wherein during flight a boundary layer separates at two points S + and S − as the air flow moves past the forebody and feeds itself into a pair of vortices, andplasma discharge elements located to starboard and port on the forebody, said plasma discharge elements being adapted to generate a plasma that volumetrically heats the boundary layer on and above the surface of the forebody on a time scale at least commensurate with changes in flight conditions to create a thermal gradient between the port and starboard sides of the forebody to control an angular location of separation points S + and S − and control a yawing moment on the forebody. 17. The aircraft of claim 16, wherein when maneuvering at sufficiently steep angles of attack said boundary layer may feed itself into a pair of asymmetric vortices causing yaw departure, said plasma discharge elements being adapted to generate the plasma to move the angular location of separation points S + and S − away from a line of symmetry in the forebody and towards an equatorial line to reduce the asymmetry of the vortices and mitigate against yaw departure. 18. The aircraft of claim 16, further comprising a vertical tail with a rudder that is adapted to provide lateral control of the aircraft when maneuvering, said plasma discharge elements being adapted to generate the plasma to move the angular location of separation points S + and S − to control the asymmetry of the vortices to produce an additional yawing moment to supplement the lateral control provided by the vertical tail. 19. The aircraft of claim 16, further comprising additional plasma discharge elements adapted to generate a plasma that turbulizes the airflow about the forebody to further stabilize the vortices. 20. The aircraft of claim 16, further comprising;pressure sensors located to starboard and port on the forebody that sense a pressure distribution around the forebody; anda closed-loop controller that controls the plasma discharge elements in response to the sensed pressure distribution to control the yawing moment. 21. An aircraft, comprising:a forebody wherein during flight a boundary layer separates at two points S + and S − as the air flow moves past the forebody and feeds itself into a pair of vortices,pressure sensors located to starboard and port on the forebody that sense a pressure distribution around the forebody,plasma discharge elements located to starboard and port on the forebody, anda closed-loop controller that controls the plasma discharge elements in response to the sensed symmetries or asymmetries in said pressure distribution to manipulate an angular location of separation points S + and S − and produce a yawing moment on the forebody. 22. The aircraft of claim 21, further comprising;heat transfer gauges located to starboard and port on the forebody to sense the flow, andadditional plasma discharge elements adapted to generate a plasma that turbulizes the flow about the forebody to further stabilize the vortices. 23. The aircraft of claim 22, wherein when maneuvering at sufficiently steep angles of attack said boundary layer may feed itself into a pair of asymmetric vortices causing yaw departure, said plasma discharge elements being adapted to generate the plasma to move the angular location of separation points S + and S − away from a line of symmetry in the forebody and towards an equatorial line to reduc e the asymmetry of the vortices and mitigate against yaw departure. 24. The aircraft of claim 22, further comprising a vertical tail with a rudder that is adapted to provide lateral control of the aircraft when maneuvering, said plasma discharge elements being adapted to generate the plasma to move the angular location of separation points S + and S − to control the asymmetry of the vortices to produce an additional yawing moment to supplement the lateral control provided by the vertical tail. 25. An aircraft, comprising:a forebody wherein during flight a boundary layer separates at two points S + and S − as the air flow moves past the forebody and feeds itself into a pair of vortices,a vertical tail with a rudder that is adapted to provide lateral control of the aircraft when maneuveringpressure sensors located to starboard and port on the forebody that sense a pressure distribution around the forebody,plasma discharge elements located to starboard and port on the forebody, said plasma discharge elements being adapted to generate a plasma that volumetrically heats the boundary layer on and above the surface of the forebody on a time scale at least commensurate with changes in flight conditions to create a thermal gradient between the port and starboard sides of the forebody, anda closed-loop controller that controls the plasma discharge elements in response to the sensed pressure distribution to move the angular location of separation points S + and S − to produce an additional yawing moment to supplement the lateral control provided by the vertical tail. 26. An aircraft, comprising:a forebody wherein when maneuvering at sufficiently steep angles of attack a boundary layer separates at two points S + and S − as the air flow moves past the forebody and feeds itself into a pair of asymmetric vortices causing yaw departure,pressure sensors located to starboard and port on the forebody that sense a pressure distribution around the forebody,plasma discharge elements located to starboard and port on the forebody, said plasma discharge elements being adapted to generate a plasma that volumetrically heats the boundary layer on and above the surface of the forebody on a time scale at least commensurate with changes in flight conditions to create a thermal gradient between the port and starboard sides of the forebody, anda closed-loop controller that controls the plasma discharge elements in response to the sensed pressure distribution to move the angular location of separation points S + and S − away from a line of symmetry in the forebody and towards an equatorial line to reduce the asymmetry of the vortices and mitigate against yaw departure. 27. The aircraft of claim 26, further comprising;heat transfer gauges located to starboard and port on the forebody to sense the flow, andadditional plasma discharge elements adapted to generate a plasma that turbulizes the flow about the forebody to further stabilize the vortices. 28. A method of producing a yawing moment on the forebody of an aircraft, in which during flight a boundary layer separates at two points S + and S − as the air flow moves past the forebody and feeds itself into a pair of vortices, comprising:sensing a pressure distribution around the forebody, anddischarging a plasma around the forebody to control the angular location of separation points S + and S − to control the yawing moment on the forebody. 29. The method of claim 28, wherein during flight a boundary layer separates at two points S + and S − as the air flow moves past the forebody and feeds itself into a pair of vortices, said plasma being discharged to control an angular location of separation points S + and S − to control the yawing moment on the forebody. 30. The method of claim 29, wherein when maneuvering at sufficiently steep angles of attack said boundary layer may feed itself into a pair of asymmetric vort ices causing yaw departure, said plasma being discharged to move the angular location of separation points S + and S − away from a line of symmetry in the forebody and towards an equatorial line to reduce the asymmetry of the vortices and mitigate against yaw departure. 31. The method of claim 29, wherein the aircraft comprises a vertical tail with a rudder that is adapted to provide lateral control of the aircraft when maneuvering, said plasma being discharged to move the angular location of separation points S + and S − to control the asymmetry of the vortices to produce an additional yawing moment to supplement the lateral control provided by the vertical tail. 32. The method of claim 29, wherein the plasma is discharged to volumetrically heats the boundary layer on and above the surface of the forebody on a time scale at least commensurate with changes in flight conditions to create a thermal gradient between the port and starboard sides of the forebody to control an angular location of separation points S + and S − and control a yawing moment on the forebody. 33. The method of claim 29, further comprising discharging additional plasma that turbulizes the airflow about the forebody to further stabilize the vortices.
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