A non-linear self-adaptive flight control method

A flight control, self-adaptive technology, applied in the direction of self-adaptive control, general control system, control/regulation system, etc., can solve problems such as unfavorable engineering realization, control effect influence, lack of engineering practical significance, etc., to achieve the effect of good stability

Inactive Publication Date: 2016-04-06
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

Foreign Sigthorsson et al. proposed a method of robust linear output feedback control to achieve good speed and altitude tracking of air-breathing aircraft with uncertainty under multi-flight conditions, but the method used is based on linear control. The large envelope flight of the aircraft has great limitations and lacks engineering practical significance
Zhang et al. proposed a method combining terminal sliding mode and second-order sliding mode to solve the problem of hypersonic vehicle parameter uncertainty and achieve better results, but in this method, uncertain disturbances ar

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  • A non-linear self-adaptive flight control method
  • A non-linear self-adaptive flight control method
  • A non-linear self-adaptive flight control method

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Embodiment Construction

[0032] The invention will be further described in detail below in conjunction with the accompanying drawings.

[0033] A nonlinear adaptive flight control method proposed by the present invention is figure 1 As shown, the sliding mode surface S=[S V ,S h ] T , Where S V Is the sliding surface of speed V, S h Is the sliding mode surface with height h. Select this sliding mode surface as the fuzzy input of the type 2 fuzzy logic controller. After steps of fuzzy inference, reduction and defuzzification, the clear output U of the type 2 fuzzy logic controller can be obtained. f (t)=[β cf (t),δ ef (t)] T , Where β cf (t) is the second type fuzzy output of the setting value of the engine throttle valve, δ ef (t) is the second type fuzzy output of the elevator, compensation control law U n (t)=[β cn (t),δ en (t)] T Used to compensate the difference between the output of the type 2 fuzzy controller and the optimal solution of the control law, where β cn (t) is the compensation contr...

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Abstract

The invention relates to a non-linear self-adaptive flight control method belonging to the technical field of near-space aircraft flight control. According to the invention, with regard to problems of indeterminate parameters in vertical control of near-space aircrafts, and with consideration given to advantages of sliding-mode control over non-linear system control and the feature that interval second-type fuzzy control with nondeterminacy fuzzy sets is especially suitable for solving problems of nondeterminacy, a second-type fuzzy control system is combined with sliding-mode control and self-adaptive control to design a flight controller to enable the flight controller to have better control performance. The stability and robustness of the near-space aircrafts are raised.

Description

Technical field [0001] The invention relates to a nonlinear adaptive flight control method, belonging to the technical field of flight control methods for near-space aircraft. Background technique [0002] With the development of the aerospace industry, research in aircraft-related fields has been increased at home and abroad. As an important part of aircraft, flight control systems have attracted the attention and attention of scholars from various countries. The diversity and variability of flight missions has led to the derivation of various new types of high-complexity aircraft, which in turn imposes higher and higher requirements on flight performance. The flight environment of the near-space vehicle and its own complex and changeable aerodynamic characteristics have brought many technical difficulties to the design of the flight control system. [0003] Many experts and scholars at home and abroad have conducted in-depth research on the uncertainty of near-space vehicles and...

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Application Information

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IPC IPC(8): G05B13/02
CPCG05B13/0275
Inventor 焦鑫江驹孟宏鹏
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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