System and method for control of aeroelasticity effects
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G06F-019/00
출원번호
US-0117010
(2008-05-08)
등록번호
US-8155794
(2012-04-10)
발명자
/ 주소
Mangalam, Arun S.
Mangalam, Siva M.
출원인 / 주소
Tao of Systems Integration, Inc.
대리인 / 주소
Hunton & Williams LLP
인용정보
피인용 횟수 :
3인용 특허 :
23
초록▼
A system is provided for control of a structure immersed in a fluid flow regime. The system comprises a plurality of flow sensors disposed on a surface of the structure, the flow sensors including at least one flow bifurcation point sensor. The system further comprises at least one structural sensor
A system is provided for control of a structure immersed in a fluid flow regime. The system comprises a plurality of flow sensors disposed on a surface of the structure, the flow sensors including at least one flow bifurcation point sensor. The system further comprises at least one structural sensor attached to the structure for measurement of a structural parameter. A data processor in communication with the flow sensors and the at least one structural sensor is configured for processing the data signals and for generating and transmitting one or more actuator command signals to effect a desired flow and structural state for the structure. The system also comprises at least one actuator in communication with the data processor. Each of the at least one actuator is configured for effecting, in response to an actuator command signal, one of the set consisting of a structural deformation in at least a portion of the structure, a change in configuration of a control surface of the structure, and an operational change in a flow control device embedded in the structure.
대표청구항▼
1. A system for control of a structure immersed in a fluid flow regime, the system comprising: a plurality of flow sensors disposed on a surface of the structure, the plurality of flow sensors including at least one flow bifurcation point sensor;at least one structural sensor attached to the structu
1. A system for control of a structure immersed in a fluid flow regime, the system comprising: a plurality of flow sensors disposed on a surface of the structure, the plurality of flow sensors including at least one flow bifurcation point sensor;at least one structural sensor attached to the structure for measurement of a structural parameter;a data processor in communication with the flow sensors and the at least one structural sensor for receiving data signals therefrom, the data processor being configured for processing the data signals and for generating and transmitting one or more actuator command signals to effect a desired flow and structural state for the structure; andat least one actuator in communication with the data processor, each of the at least one actuator being configured for effecting, in response to receiving an actuator command signal from the data processor, one of the set consisting of a structural deformation in at least a portion of the structure, a change in configuration of a control surface of the structure, and an operational change in a flow control device embedded in the structure. 2. A system according to claim 1 wherein the data processor is further configured for receiving an active control command and for using the control command in combination with the data signals to generate the one or more actuator command signals. 3. A system according to claim 1 wherein the data processor is further configured for processing the data signals using at least one of the set consisting of summing, shaping, filtering, switching, gain scheduling, limiting, conditioning, and converting. 4. A system according to claim 1 wherein the flow bifurcation point sensor is a hot-film sensor. 5. A system according to claim 1 wherein the flow bifurcation point sensor is a shear stress sensor. 6. A system according to claim 1 wherein the flow bifurcation point sensor is a heat flux sensor. 7. A system according to claim 1 wherein the at least one structural sensor includes at least one of the set consisting of an accelerometer and a strain gage. 8. A system according to claim 1 wherein the data processor is configured to determine the actuator command signal based on a real-time estimate of the energy transfer from the fluid to the structure as determined from the data signals. 9. A system according to claim 1 wherein the structure comprises at least a portion of an aircraft. 10. A system according to claim 9 wherein the at least one flow bifurcation point sensor is disposed on a wing surface. 11. A method for controlling the flow and structural state of a structure immersed in a fluid flow regime, the method comprising: receiving flow data from a plurality of flow sensors disposed on a surface of the structure, the plurality of flow sensors including at least one flow bifurcation point sensor;receiving structural data from at least one structural sensor attached to the structure for measurement of a structural parameter;processing the flow and structural data to determine one or more actuator command signals;transmitting the one or more actuator command signals to at least one actuator configured for effecting in response one of the set consisting of a structural deformation in at least a portion of the structure, a change in configuration of a control surface of the structure, and an operational change in a flow control device embedded in the structure. 12. A method according to claim 11 further comprising the action of receiving an active control command and wherein the active control command is used with the flow and structural data to determine the one or more actuator command signals. 13. A method according to claim 11 wherein the actions of receiving flow data, receiving structural data, processing the flow and structural data and transmitting the one or more actuator commands are carried out by a data processor in communication with the flow sensors, the at least one structural sensor, and the at least one actuator. 14. A method according to claim 11 wherein the action of processing the flow and structural data includes at least one of the set consisting of summing, shaping, filtering, switching, gain scheduling, limiting, conditioning, and converting at least a portion of the flow and structural data. 15. A method according to claim 11 wherein the flow bifurcation point sensor is a hot-film sensor. 16. A method according to claim 11 wherein the flow bifurcation point sensor is a shear stress sensor. 17. A method according to claim 11 wherein the at least one structural sensor includes at least one of the set consisting of an accelerometer and a strain gage. 18. A method according to claim 11 wherein the action of processing the flow and structural data to determine one or more actuator command signals includes determining the actuator command signal based on a real-time estimate of the energy transfer from the fluid to the structure as determined from the flow and structural data. 19. A method according to claim 11 wherein the structure comprises at least a portion of an aircraft. 20. A method according to claim 19 wherein at least one flow bifurcation point sensor is disposed on a wing surface.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (23)
Maestrello Lucio (Newport News VA), Active control of boundary layer transition and turbulence.
Holmes Bruce J. (Newport News VA) Carraway Debra L. (Norfolk VA) Holmes Harlan K. (Newport News VA) Moore Thomas C. (Poquoson VA), Crossflow vorticity sensor.
Ryutaro Yoshino JP, Drag control system for flying machine, process for estimating drag of flying machine, boundary layer control system, and boundary layer control process.
Mangalam Siva M. (17 Mile Course Kingsmill on the James ; Williamsburg VA 23185), Method and instrumentation system for measuring airspeed and flow angle.
Stephen A. Huyer ; John R. Grant ; James S. Uhlman ; Jeffrey S. Marshall, Method for computing three dimensional unsteady flows by solution of the vorticity equation on a Lagrangian mesh.
Agarwal Naval K. (Yorktown VA) Maddalon Dal V. (Yorktown VA) Mangalam Siva M. (Kingsmill on the James VA), Method of measuring cross-flow vortices by use of an array of hot-film sensors.
Lind Richard C. ; Brenner Martin J., On-line .mu. method for robust flutter prediction in expanding a safe flight envelope for an aircraft model under flight test.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.