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Hypersonic flight vehicle tracking control method based on nonlinear function

A non-linear function and hypersonic technology, applied in the direction of adaptive control, general control system, control/regulation system, etc., can solve the problems of complex control model and poor robustness, and achieve strong robustness and improved control accuracy Effect

Active Publication Date: 2018-08-21
HARBIN INST OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the problems of complex control models and poor robustness of existing aircraft, and propose a tracking control method for hypersonic aircraft based on nonlinear functions

Method used

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  • Hypersonic flight vehicle tracking control method based on nonlinear function
  • Hypersonic flight vehicle tracking control method based on nonlinear function
  • Hypersonic flight vehicle tracking control method based on nonlinear function

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specific Embodiment approach 1

[0047] Specific embodiment one: a hypersonic vehicle tracking control method based on a nonlinear function comprises the following steps:

[0048] Hypersonic Vehicle Model Description

[0049] In order to facilitate the design of hypersonic vehicle control system, the feedback linearization model (Sun H, Li S, Sun C. Finite time integral sliding mode control of hypersonic vehicles [J]. Nonlinear Dynamics, 2013, 73 (1-2): 229-244.):

[0050]

[0051] where φ c and δ e is the control input, f v , f h , b 11 , b 12 , b 21 and b 22 For specific definitions, see literature (Sun H, Li S, Sun C. Finite time integral sliding mode control of hypersonic vehicles [J]. Nonlinear Dynamics, 2013, 73(1-2): 229-244.).

[0052] remember Then formula (1) can be rewritten as:

[0053]

[0054] Among them, Δf v , Δf h , Δb 11 , Δb 12 , Δb 21 , Δb 22 is a bounded term resulting from parameter uncertainty and external disturbances. Let Δ 1 =Δf V +Δb 11 δ e +Δb 12 φ c ...

specific Embodiment approach 2

[0172] Embodiment 2: The difference between this embodiment and Embodiment 1 is that in the step 1, the hypersonic vehicle model is converted through the state feedback controller, and the specific process of obtaining the transformed hypersonic vehicle model is as follows:

[0173] The hypersonic vehicle model is:

[0174]

[0175] in for σ 1 derivative of for σ 2 derivative of σ 1 and σ 2 is a function with the speed error and height error of the hypersonic vehicle as independent variables, d is the system (hypersonic vehicle model) disturbance, u is the control input, B is the control gain matrix, and F is the intermediate function;

[0176]

[0177]

[0178] B=-b

[0179]

[0180] in is the third derivative of the reference speed signal, is the fourth derivative of the reference height, f V is a nonlinear function with the speed of the hypersonic vehicle as an independent variable, f h is a nonlinear function with the height of the hypersonic vehi...

specific Embodiment approach 3

[0186] Specific implementation mode three: the difference between this implementation mode and specific implementation mode one or two is: the expression of s in the said step two is:

[0187] s = σ 2 +k 2 σ 1

[0188] Other steps and parameters are the same as those in Embodiment 1 or Embodiment 2.

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Abstract

The invention discloses a hypersonic flight vehicle tracking control method based on a nonlinear function, and relates to a hypersonic flight vehicle tracking control method based on the nonlinear function. The technical purpose is to solve the problems that a control model of an existing flight vehicle is complicated and poor in robustness. The method comprises the steps of 1, transforming a hypersonic flight vehicle model through a state feedback controller to obtain the transformed hypersonic flight vehicle model; 2, designing a self-adaptive nonlinear robust controller u0 according to thehypersonic flight vehicle model transformed in step 1. By means of the hypersonic flight vehicle tracking control method based on the nonlinear function, on the basis of an input and output linearizedmodel, by introducing an auxiliary error variable, the model is transformed into a general multivariable second-order system. Aiming at the problem that system interference has an unknown upper limit, by introducing a new continuous differentiable nonlinear saturation function, and through the further utilization of a self-adaptive theory, the nonlinear robust controller is designed. The hypersonic flight vehicle tracking control method is applied to the field of flight vehicles.

Description

technical field [0001] The invention relates to a hypersonic vehicle tracking control method based on a nonlinear function. Background technique [0002] Hypersonic vehicles are highly forward-looking, strategic and driving, and have shown great development potential in both military and civilian aspects, so they have become a hot spot for research and development in various countries. Compared with conventional aircraft, hypersonic aircraft adopts a unique fuselage-engine integrated design, resulting in complex characteristics such as strong nonlinearity, strong coupling, and fast time-varying during flight, making the closed-loop control system of hypersonic aircraft robust. The device design faces many challenges. [0003] In recent years, a variety of control theories have been applied to the design of hypersonic vehicle controllers. Based on the control model, they are mainly divided into linearization-based models and nonlinear-based models. Literature (Sigthorsson D...

Claims

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Application Information

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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 宋申民孙经广王岩谭立国于志刚
Owner HARBIN INST OF TECH
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