Aircraft with an arrangement of flow-influencing devices
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0491629
(2012-06-08)
|
등록번호 |
US-8645007
(2014-02-04)
|
우선권정보 |
DE-10 2009 057 405 (2009-12-08) |
발명자
/ 주소 |
- Gölling, Burkhard
- King, Rudibert
- Heinz, Ulrich Notger
- Nitsche, Wolfgang
|
출원인 / 주소 |
|
대리인 / 주소 |
Jenkins, Wilson, Taylor & Hunt, P.A.
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
6 |
초록
▼
An aircraft, which has a respective arrangement of flow-influencing devices in at least one surface segment of each wing extending in the wingspan direction in order to influence the fluid flow over the surface segment, and of flow condition sensor devices for measuring the flow condition on the res
An aircraft, which has a respective arrangement of flow-influencing devices in at least one surface segment of each wing extending in the wingspan direction in order to influence the fluid flow over the surface segment, and of flow condition sensor devices for measuring the flow condition on the respective segment, and a flight control device, wherein the flight control device has a flow-influencing target parameter setting device connected with the arrangement of flow-influencing devices for generating target parameters for the flow-influencing devices of the at least one surface segment, wherein the flow-influencing devices are designed in such a way as to use the target parameters to change the local lift coefficients or correlations between the drag and lift coefficients in the segment where respectively located.
대표청구항
▼
1. An aircraft, comprising: a respective arrangement of flow-influencing devices in at least one surface segment of each wing extending in the wingspan direction in order to influence the fluid flow over the surface segment, and of flow condition sensor devices for measuring the flow condition on th
1. An aircraft, comprising: a respective arrangement of flow-influencing devices in at least one surface segment of each wing extending in the wingspan direction in order to influence the fluid flow over the surface segment, and of flow condition sensor devices for measuring the flow condition on the respective segment, and a flight control device,wherein the flight control device has a flow-influencing target parameter setting device connected with the arrangement of flow-influencing devices for generating target parameters for the flow-influencing devices of the at least one surface segment,wherein the flow-influencing target parameter setting device comprises an autopilot device that generates the target parameters based on a predetermined operating mode, andwherein the flow-influencing devices are designed in such a way as to use the target parameters to change the local lift coefficients or correlations between the drag and lift coefficients in the segment where respectively located. 2. The aircraft according to claim 1, wherein the flight control device has a flight condition control device and a flow condition control device;the flight condition control device is designed in such a way as to use the target parameters of the flow-influencing target parameter setting device and sensor signals of the flight condition sensor device to transmit input signals to the flow condition control device functionally connected with the flight control device;the flow condition control device uses the input signals of the flight condition control device and sensor signals of the flow condition sensor device of each segment to generate flow condition adjustment commands for actuating the flow-influencing device of each segment, and transmits them to the flow-influencing device of each segment, in order to control the aircraft based on the target parameters of the flow-influencing target parameter setting device. 3. The aircraft according to claim 2, wherein the flight condition control device comprises a segment actuation function designed in such a way that the same generates one or more of adjustment commands for sending the same to the flow-influencing device of each segment adjustment commands for sending the same to an actuator of an adjusting flap for moving the same relative to the wing, wherein the generation of the adjustment commands is based on the adjustment signals of the flight condition control device by means of an optimization taking into account one or more of the power or dynamics of the flow-influencing device or of the actuator of the adjustment flap available at the time in question. 4. The aircraft according to claim 1, wherein the arrangement of flow-influencing devices comprises exhaust openings situated in one segment or several segments and a flow generating device for one or more of exhausting or sucking purposes situated in the wing, through which the fluid is blown out from the exhaust openings, so as to influence the lift coefficient arising locally on the segment. 5. The aircraft according to claim 4, wherein the arrangement of flow-influencing devices additionally comprises suction openings situated in one segment or several segments, and a suction device situated in the wing and connected in terms of flow with the suction openings, through which fluid is aspirated from the suction openings, so as to influence the lift coefficient arising locally on the segment. 6. The aircraft according to claim 1, wherein the arrangement of flow-influencing devices comprises loudspeaker devices, which are situated in one segment or several segments, and when activated can influence the lift coefficient arising locally on the segment by generating air fluctuations. 7. The aircraft according to claim 1, wherein the arrangement of flow-influencing devices comprises piezo-actuators situated on the surface of the wing, which are arranged in one segment or several segments, and when activated can influence the lift coefficient arising locally on the segment by generating air fluctuations. 8. The aircraft according to claim 7, wherein the arrangement of flow-influencing devices has an adjustment flap and an actuator for regulating the latter, wherein the target parameters for the flow-influencing devices comprise target parameters for the flow-generating device and target parameters for an actuator for regulating the adjustment flap. 9. The aircraft according to claim 1, wherein the at least one segment can comprise several segments, which are situated one in back of the other viewed in the wingspan direction of the wing.
이 특허에 인용된 특허 (6)
-
Younkin,James R., Dual channel fail-safe system and method for adjusting aircraft trim.
-
Valdis Kibens ; Ganesh Raman, High frequency excitation apparatus and method for reducing jet and cavity noise.
-
Hassan, Ahmed A.; JanakiRam, Ram D., Method and device for altering the separation characteristics of air-flow over an aerodynamic surface via intermittent suction.
-
Lurz Werner (Hamburg DEX), Method of and apparatus for controlling the boundary layer flow over the surface of a body.
-
Hassan Ahmed A. ; Tadghighi Hormoz ; Janakiram Ram D., Oscillating air jets for reducing HSI noise.
-
James C. Hayes CA, Vehicle with vertical wings and a stabilizing torque system of jets to use fluid energy for forward motion.
이 특허를 인용한 특허 (2)
-
Gölling, Burkhard, Aircraft with wings and a system for minimizing the influence of unsteady flow states.
-
Baruzzini, Dan J.; Miller, Daniel N.; Domel, Neal D.; Hakes, Jeff G., Suprression of shock-induced airflow separation.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.