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Control method of high-lift device of airplane

The technology of a lift-increasing device and a control method, which is applied in the field of aviation flight control, can solve the problems of mismatching flight speed, heavy workload, and inability to quickly adjust, and achieve the effect of avoiding the deflection angle of high-lift devices

Active Publication Date: 2013-09-11
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

During the whole process, the high-lift device is completely controlled by the pilot referring to the flight status provided by the current flight instrument, and the workload is heavy. Once the pilot mismanages, the configuration of the high-lift device will not match the flight speed, and it cannot be quickly adjusted to Reasonable deflection angle affects flight safety

Method used

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  • Control method of high-lift device of airplane
  • Control method of high-lift device of airplane
  • Control method of high-lift device of airplane

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Embodiment Construction

[0058] Below in conjunction with accompanying drawing and example the present invention is described in further detail, please refer to Figure 1 to Figure 3 .

[0059] The principle of the present invention is: the retraction and retraction of the aircraft lift device is limited by the flight speed: at high speed, if the lift device maintains a large deflection angle, it will exceed the structural strength limit of the wing, causing structural damage; at low speed, If the high-lift device maintains a small deflection angle, it will cause insufficient lift of the aircraft, and even cause the aircraft to stall. Therefore, when controlling the high-lift device, the structural strength requirements of high speed and stall requirements of low speed are used as restrictions. These two speed limit requirements are given in multiples of the stall speed, and the stall speed is a value that changes with the flight state and the configuration of the high-lift device. It is impossible to...

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Abstract

The invention belongs to the field of aviation flying control, and particularly relates to a control method of a high-lift device of an airplane. According to the invention, on the basis of a traditional simple control method of a high-lift device, the detection on the matching between the deviation angle of the high-lift device and the current flying speed of an airplane is added, so that the incorrect deviation angle of the high-lift device is avoided. The control method has the advantages that a pilot can control the high-lift device without worry at the take-off and landing stage with large load; even though wrong operation occurs, the operation of the pilot also can be automatically corrected in time, so that the flying load of the pilot is reduced, the flying performance is improved and the condition of endangering the flying safety of the airplane is avoided; the algorithm can be directly added in a high-lift device controller without any modification to a control mechanism or the high-lift device of the airplane, so that the modification cost is saved and the research and development period is shortened.

Description

technical field [0001] The invention belongs to the field of aviation flight control, and in particular relates to a method for controlling an aircraft lift increase device. Background technique [0002] The high-lift device, that is, the high-lift device, is mainly composed of leading edge slats and trailing edge flaps. Its main function is to increase lift and increase drag during take-off and landing, especially to provide a larger lift-to-drag ratio during take-off. Therefore, its operation in the take-off and landing phase is particularly important. The manipulation of the high-lift device needs to correspond exactly to the flight state and meet the speed requirements of the aircraft, otherwise catastrophic accidents may occur. For example, the take-off process: before take-off, the high-lift device should be put down to the take-off angle to increase the wing area and increase the lift of the aircraft. After reaching a certain take-off height and speed, it is allowed ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C13/00B64C9/28
Inventor 朱妍安刚
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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