A high lift system with a main wing and control flaps, wherein the respective guiding device are at least partially provided with a fairing, having a flow control device for purposes of controlling the flow around the high lift system with at least two inlet ducts running along the main wing chordwi
A high lift system with a main wing and control flaps, wherein the respective guiding device are at least partially provided with a fairing, having a flow control device for purposes of controlling the flow around the high lift system with at least two inlet ducts running along the main wing chordwise direction with in each case at least one inlet, which device is located on or underneath the lower surface of the high lift system, wherein at least one outlet duct for air is furthermore provided, which is connected with the inlet ducts in a fluid-communicating manner, and has at least one outlet, which is located on the upper surface of at least one regulating flap and/or with respect to the main wing chordwise direction in the rear third of the main wing of the high lift system.
대표청구항▼
1. A high lift system comprising a main wing, control flaps, and guiding devices for the positioning of the control flaps, wherein the guiding devices are at least partially provided with a fairing, the high lift system further comprising: a flow control device for purposes of influencing the flow a
1. A high lift system comprising a main wing, control flaps, and guiding devices for the positioning of the control flaps, wherein the guiding devices are at least partially provided with a fairing, the high lift system further comprising: a flow control device for purposes of influencing the flow around the main wing and the control flaps, with at least one inlet duct running along the main wing chordwise direction each with at least one inlet, which is located on or underneath a lower surface of the main wing, and at least one outlet duct, which is connected with the at least one inlet duct in a fluid-communicating manner, and has at least one outlet so that fluid which is streaming into the inlet duct can be discharged through the outlet, wherein the outlet is located on at least one of an upper surface of the at least one control flap and on an upper side of the main wing, on the main wing in the rear third of the length of the main wing with respect to the main wing chordwise direction;wherein the flow control device is arranged at least partially within the fairing, and the inlet of the at least one inlet duct is facing in opposition to the main wing chordwise direction; andwherein at least one inlet per inlet duct is arranged in a range starting from the front of the fairing with respect to the main wing chordwise direction and extending to over one third in the direction of the main wing chordwise direction. 2. The high lift system in accordance with claim 1, wherein the fairing comprises at least two inlet ducts, each comprising at least one inlet, wherein two inlets of the inlets are respectively disposed on flow surfaces, the flow surfaces extending in directions diverging from each other. 3. The high lift system in accordance with claim 1, wherein at least one outlet duct is provided per inlet duct, which is connected with the respective inlet duct in a fluid-communicating manner, and the outlet ducts run along the main wing chordwise direction. 4. The high lift system in accordance with claim 1, wherein the inlets are respectively designed as openings directly in the fairing. 5. The high lift system in accordance with claim 1, wherein at least one of inlet shut-off devices is provided for the inlets and an outlet shut-off device is provided for at least one outlet. 6. The high lift system in accordance with claim 5, wherein at least one control flap comprises at least one outlet which is located on the upper surface of the respective control flap, wherein at the at least one outlet an inlet shut-off device is disposed, and the at least one outlet shut-off device is coupled, either one or both of, kinematically and functionally with the position of the control flap, such that the status of the respective shut-off device is determined by the setting of the control flap. 7. The high lift system in accordance with claim 5, wherein at least one control flap comprises at least one outlet which is located on the upper surface of the respective control flap, wherein at the at least one outlet an inlet shut-off device is disposed, and the at least one inlet shut-off device is coupled, either one or both of, kinematically and functionally with the position of the control flap, such that the status of the respective shut-off device is determined by the setting of the control flap. 8. The high lift system in accordance with claim 6, wherein the degree of opening of the respective shut-off device is a function of the setting of the control flap such that a predetermined opening state of the respective shut-off device is assigned to each of several settings. 9. The high lift system in accordance with claim 1, wherein in, at least one of, each inlet duct and each outlet duct at least one control valve or at least one pump is provided to control the volumetric flow within the flow control device. 10. The high lift system in accordance with claim 1, wherein in each inlet duct at least one flow variator for the systematic variation of the flow of air through the inlet duct is provided so that the discharge flow of the fluid being discharged through the respective outlet can be varied. 11. The high lift system in accordance with claim 10, wherein the flow variators are embodied as passively operating valves, or as a pump. 12. The high lift system in accordance with claim 1, wherein an activation device is provided for the receipt of flight state data and generation of control signals, such that the flow control device can be activated and deactivated under particular flight conditions. 13. The high lift system in accordance with claim 10, wherein the activation device is functionally coupled to at least one of the at least one shut-off device and the at least one flow variator for controlling the respective one in dependency of the position of the control flap on which the respective shut-off device is positioned. 14. The high lift system in accordance with claim 12, wherein the activation and deactivation takes place by switching of at least one of an inlet shut-off device and an outlet shut-off device. 15. The high lift system in accordance with claim 1, wherein a distribution duct is provided between the at least one inlet duct and the at least one outlet duct. 16. The high lift system in accordance with claim 1, wherein the at least one the inlet duct is configurable to be in fluid-communicating contact with further systems of an aircraft, the further systems of the aircraft being selected from the group consisting of air conditioning systems, hydraulic systems, and pneumatic systems of the aircraft. 17. The high lift system in accordance with claim 1, wherein the ducts are modifiable at least partially in their axial projection. 18. The high lift system in accordance with claim 1, wherein the at least one outlet is arranged along the main wing spanwise direction. 19. The high lift system in accordance with claim 1, wherein the at least one outlet is arranged along at least two lines in the main wing spanwise direction, and the at least one outlet of one line is arranged displaced relative to each of the at least one outlet of the adjacent line in the main wing spanwise direction. 20. The high lift system in accordance with claim 1, wherein at least one of load sensors and flow sensors are provided behind the in the main wing chordwise direction. 21. The high lift system in accordance with claim 20, wherein the load sensors and the flow sensors are arranged alternately in the main wing spanwise direction. 22. An aircraft having at least one high lift system of claim 1.
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이 특허에 인용된 특허 (14)
Reckzeh, Daniel; Schlipf, Bernhard; Andreani, Luc; Sutcliffe, Mark, Advanced trailing edge control surface on the wing of an aircraft.
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