Aircraft with wings and a system for minimizing the influence of unsteady flow states
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-021/00
B64C-013/16
B64C-021/04
B64C-021/08
출원번호
US-0734522
(2013-01-04)
등록번호
US-9656740
(2017-05-23)
우선권정보
DE-10 2010 026 162 (2010-07-06)
발명자
/ 주소
Gölling, Burkhard
출원인 / 주소
Airbus Operations GmbH
대리인 / 주소
Jenkins, Wilson, Taylor & Hunt, P.A.
인용정보
피인용 횟수 :
1인용 특허 :
23
초록▼
An aircraft and system for minimizing the influence of unsteady flow states, wherein the wing has a respective main wing and at least one control flap adjustably arranged relative thereto, an adjusting drive for activating the at least one control flap, and a sensor arrangement for acquiring the set
An aircraft and system for minimizing the influence of unsteady flow states, wherein the wing has a respective main wing and at least one control flap adjustably arranged relative thereto, an adjusting drive for activating the at least one control flap, and a sensor arrangement for acquiring the setting position of the control flap. The system exhibits at least one arrangement of flow-influencing devices for influencing the fluid flow over the surface segment, a detection device for detecting unsteady flow states acting on the aircraft, and an actuating function connected with the flow-influencing devices to influence the flow in the different segments of a wing, designed so that the latter, based on the unsteady flow states detected by the detection device and setting position of the control flap acquired by the sensor arrangement, actuates the flow-influencing devices so as to minimize the influence of unsteady flow states on the aircraft.
대표청구항▼
1. An aircraft comprising: wings, wherein each wing comprises: a respective main wing,at least one control flap adjustably arranged relative to the respective main wing,an adjusting drive that activates the at least one control flap, anda sensor arrangement configured to acquire a setting position o
1. An aircraft comprising: wings, wherein each wing comprises: a respective main wing,at least one control flap adjustably arranged relative to the respective main wing,an adjusting drive that activates the at least one control flap, anda sensor arrangement configured to acquire a setting position of the at least one control flap,a system that minimizes an influence of unsteady flow states;a presetting device that generates desired parameters corresponding to flight states of the aircraft;a flight state sensor arrangement configured to generate flight state data; anda flight control device, which is functionally connected with the flight state sensor arrangement, the presetting device, the adjusting drive, and the sensor arrangement, and that acquires the setting position of the at least one control flap, so as to adjust the aircraft to the flight states corresponding to the desired parameters; wherein the system that minimizes the influence of the unsteady flow states comprises: at least one arrangement of flow-influencing devices functionally connected with the flight control device and incorporated in at least one surface segment of each main wing of each wing extending in a respective wingspan direction or the at least one control flap, anda detection device for detecting unsteady flow states acting on the aircraft, wherein the detection device is functionally connected with the flight control device,wherein the flight control device is programmed with an actuating function that influences the flow in the at least one segment of each main wing or the at least one control flap of each wing, the flight control device being designed in such a way that the flight control device programmed with the actuating function, based on the unsteady flow states detected by the detection device and setting position of the at least one control flap acquired by the sensor arrangement, actuates the flow-influencing devices so as to minimize the influence of the unsteady free flow states on the aircraft. 2. An aircraft comprising wings, each of which comprises: a respective main wing,at least one control flap adjustably arranged relative to the respective main wing,an adjusting drive that activates the at least one control flap,a sensor arrangement configured to acquire a setting position of the at least one control flap, andat least one trailing edge flap;a system that minimizes an influence of unsteady flow states;a presetting device that generates desired parameters corresponding to flight states of the aircraft;a flight state sensor arrangement configured to generate flight state data; anda flight control device, which is functionally connected with the flight state sensor arrangement, the presetting device, the adjusting drive, and the sensor arrangement, and that acquires the setting position of the at least one control flap, so as to set the aircraft to the flight states corresponding to the desired parameters;wherein the system that minimizes the influence of the unsteady flow states comprises: at least one arrangement of flow-influencing devices functionally connected with the flight control device and incorporated in at least one surface segment of each of the at least one trailing edge flap of each wing extending in a respective wingspan direction that influence fluid flow over the at least one surface segment, anda detection device that detects the unsteady flow states acting on the aircraft, wherein the detection device is functionally connected with the flight control device,wherein the flight control device is programmed with an actuating function that influences the flow in the at least one surface segment of each of the at least one trailing edge flap of each wing, the flight control device being designed in such a way that the flight control device programmed with the actuating function, based on the unsteady flow states detected by the detection device and setting position of the at least one control flap acquired by the sensor arrangement, actuates the flow-influencing devices so as to minimize the influence of the unsteady flow states on the aircraft. 3. The aircraft according to claim 2, wherein the system for minimizing the influence of the unsteady flow states comprises: at least one arrangement of the flow-influencing devices for influencing the fluid flow over at least one surface segment of the main wing, which are functionally connected with the flight control device, and incorporated in the at least one surface segment of the main wing of each of the wings extending in the respective wingspan direction or the at least one control flap;wherein the flight control device is programmed with an actuating function that influences the fluid flow in the at least one surface segment of the main wing, the flight control device being designed in such a way that the flight control device programmed with the actuating function, based on the unsteady flow states detected by the detection device and setting position of the control flap acquired by the sensor arrangement, actuates the flow-influencing devices so as to minimize the influence of the unsteady free flow states on the aircraft. 4. The aircraft according to claim 2, wherein the flight control device programmed with the actuating function is configured so that commands for the flow-influencing devices are taken into account with respect to controlling the aircraft according to the commands for the at least one control flap. 5. The aircraft according to claim 2, wherein at least one surface segment of the main wing of each wing extending at least in the respective wingspan direction incorporates an arrangement of flow-influencing devices for influencing the fluid flow over the at least one surface segment of the main wing and at least one flow state sensor arrangement configured to measure the flow state in the respective surface segment, which is functionally connected with the actuating device, wherein the actuating device for each segment determines actual values for the flow state in the respective segment from the flow state sensor arrangement respectively accompanying the latter, and actuates the flow-influencing devices in such a way that the desired values ascertained by the actuating device are desired for minimizing the influence of unsteady free flow states. 6. The aircraft according to claim 2, wherein the detection device for detecting unsteady flow states acting on the aircraft is functionally connected with the flight state sensor arrangement and the detection device is programmed with a filter function that performs a function used to identify unsteady flow states; and the detection device is programmed with the actuating function for influencing the fluid flow in the at least one surface segment of the at least one trailing edge flap of the wing that is designed to use the identified unsteady flow states to actuate the flow-influencing devices in such a way as to influence the flow of the fluid flowing over the surface segment to reduce the effects of the unsteady free flow states on the aircraft. 7. The aircraft according to claim 2, wherein: the detection device for detecting unsteady flow states acting on the aircraft is functionally connected with the flow state sensor arrangement;the detection device is programmed with a filter function that performs a function used to identify unsteady flow states; andthe detection device is programmed with the actuating function for influencing the flow in the different segments of a wing that is designed to use the identified unsteady flow states to actuate the flow-influencing devices in such a way as to influence the flow of the fluid flowing over the surface segment to reduce the effects of the unsteady flow states on the aircraft. 8. The aircraft according to claim 2, wherein: the detection device exhibits sensors for detecting loads and/or displacements of turbulences acting on the aircraft; andthe actuating function for influencing the flow in the different segments of a wing is functionally connected with the detection device and designed to use the identified unsteady flow states to actuate the flow-influencing devices in such a way as to influence the flow of the fluid flow over the surface segment to reduce the effects of the unsteady flow states on the aircraft. 9. The aircraft according to claim 2, wherein the detection device is functionally connected with the flight state sensor arrangement, and wherein the detection device is designed in such a way as to ascertain desired values for the flow state on the surface segments as a function of the flight state data transferred by the flight state sensor arrangement in order to set a distribution of lift over the span of the main wing, and use the flow state data ascertained by the respective flow state sensor arrangements to find deviations, and from that to derive unsteady flow states acting on the aircraft. 10. The aircraft according to claim 2, wherein the detection device exhibits acceleration sensors, which are arranged on the wing for measuring accelerations that locally arise on the wing due to unsteady flow states acting on the aircraft. 11. The aircraft according to claim 2, wherein the arrangement of flow-influencing devices is comprised of flow passage openings situated in one segment or several segments, and of a flow-generating device situated in each wing for exhaust or aspiration purposes, through which fluid is purged from the flow passage openings, so as to influence the lift coefficient locally arising at the segment. 12. The aircraft according to claim 11, wherein the flow-generating device is designed to generate a continuous volumetric flow in order to reduce the effects of unsteady flow states on the aircraft when it is activated by the flight control device programmed with the actuating function. 13. The aircraft according to claim 11, wherein the flow-generating device is designed in such a way as to generate a pulsed volumetric flow in order to reduce the effects of unsteady flow states on the aircraft when it is activated by the flight control device programmed with the actuating function. 14. The aircraft according to claim 13, wherein the flight control device programmed with the actuating function performs a function that generates the frequency of the pulsed volumetric flow depending on the values for unsteady flow states ascertained by the detection device in order to reduce the influence of unsteady flow states on the aircraft. 15. The aircraft according to claim 11, wherein the flow-generating device, in order to reduce the effects of the unsteady flow states on the aircraft, is designed to generate an aspiration and purging of a volumetric flow, which is drawn by an actuator into an actuator chamber, or which is ejected from the actuator chamber. 16. The aircraft according to claim 2, wherein the arrangement of flow-influencing devices comprises flow passage openings arranged in a segment or several segments, and a suction device situated in the wing and flow-connected with aspirating openings, through which fluid is aspirated from the flow passage openings to influence the lift coefficient locally arising at the segment. 17. The aircraft according to claim 2, wherein the arrangement of flow-influencing devices consists of loudspeaker devices situated in the at least one surface segment or several segments, which, when activated, generate air oscillations that influence the lift coefficient locally arising at the at least one surface segment. 18. The aircraft according to claim 2, wherein the arrangement of flow-influencing devices comprises piezo actuators situated on the surface of the wing, which are arranged in the at least one surface segment or several segments, and, when activated, generate air oscillations that influence the lift coefficient locally arising at the at least one surface segment. 19. The aircraft according to claim 18, wherein the arrangement of flow-influencing devices further comprises an adjustable flap and actuator that adjusts the adjustable flap, wherein the desired commands for the flow-influencing devices are comprised of desired commands for the flow-generating device and desired commands for an actuator for adjusting the adjustable flap. 20. The aircraft according to claim 2, wherein the at least one surface segment of the at least one trailing edge flap of each wing comprises several segments arranged one in back of the other as viewed in the wingspan direction.
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.
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.
Larramendy Panxika,FRX ; Delgado Daniel,FRX, Method and device for detecting vertical gusts of wind and application thereof to the pitch-attitude control of an airc.
Larramendy Panxika,FRX ; Delgado Daniel,FRX, Method for protecting an aircraft against vertical gusts of wind and pitch-attitude control device employing this method.
Walton, Vincent M.; Borland, Christopher J.; Siu, Tze L.; Najmabadi, Kioumars; Coleman, Edward E.; Marquis, David P.; McMullin, Dianne L.; Milligan, Kevin H., Vertical gust suppression system for transport aircraft.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.