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Method for controlling reentry vehicle self-adapting optimal sliding mode attitude based on SDRE (state dependence matrix Riccati equation)

A re-entry aircraft, optimal sliding mode technology, applied in the field of aircraft control, can solve the problems of weak resistance to interference, difficult to obtain, and poor robustness of the system

Inactive Publication Date: 2015-02-11
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

However, for the reentry vehicle control system, the system uncertain upper bound is not easy to obtain
If the value of the switching gain is too conservative, that is, choosing a large enough switching gain to ensure that the sliding mode reaches the condition, it will cause serious chattering problems; on the contrary, if the value of the switching gain is too small, the system’s ability to resist interference will become weak, and the robustness of the system will weaken. Poor sex

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  • Method for controlling reentry vehicle self-adapting optimal sliding mode attitude based on SDRE (state dependence matrix Riccati equation)
  • Method for controlling reentry vehicle self-adapting optimal sliding mode attitude based on SDRE (state dependence matrix Riccati equation)
  • Method for controlling reentry vehicle self-adapting optimal sliding mode attitude based on SDRE (state dependence matrix Riccati equation)

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Embodiment

[0146] The present invention carries out simulation verification under the environment of Matlab2009a. The initial state of the flight is as follows: the initial altitude is 28km, the speed is 2000m / s, and the initial attitude angle is [1°, 1°, 1°] T , the deflection angle of the rudder surface is limited to ±25°. Attitude angle given command is: [α c ,β c ,μ c ] T =[4°,0°,20°] T , further, in order to verify the robustness of the designed control law, in this embodiment, the atmospheric environment, aerodynamic force and aerodynamic moment coefficient are subjected to pull-out experiments to simulate the harsh re-entry flight environment, and the atmospheric density is positively pulled by 30%. , X, Y, Z aerodynamic coefficients are respectively applied with constant values ​​of 0.01, -0.1, -0.01 to pull the deflection, M x , M y , M z The constant values ​​of -0.001, -0.0001, and -0.001 are respectively applied to the aerodynamic moment coefficient to pull the deflec...

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Abstract

The invention relates to a method for controlling a reentry vehicle self-adapting optimal sliding mode attitude based on an SDRE (state dependence matrix Riccati equation)and belongs to the technical field of aircraft control. The method provided by the invention comprises following steps of converting non-linear dynamic and kinematic models of the reentry vehicle into a form of SDC, designing an optimal sliding mode surface based on SDRE and an aerodynamic moment self-adapting sliding mode control rule on the basis, thereby constricting the system state on the sliding mode surface in a limited time; and distributing the aerodynamic moment to an aerodynamic surface according to the self-adapting sliding mode control rule to obtain a surface deflection angle command demanded by attitude control to real-timely control the attitude. The method provided by the invention designs a controller by directly aiming at the non-linear model of the aircraft to avoid a modeling error introduced when linearizing the model, reduces calculated amount and improves controlling precision of the system through combining the SDRE method with the sliding-mode control, and improves self-adapting property of the system by introducing a switch gain adaptive adjustment algorithm.

Description

technical field [0001] The invention relates to an SDRE (State-dependent Ricccati equation, state-dependent matrix Riccati equation) based re-entry aircraft adaptive optimal sliding mode attitude control method, which belongs to the technical field of aircraft control. Background technique [0002] For the re-entry vehicle, the flight conditions (airspace and speed domain) change in a large range during the re-entry process, and the coupling between channels is serious, showing strong nonlinear dynamic characteristics. In addition, the existence of various uncertain external disturbances and the inability to accurately know the aerodynamic characteristics of the aircraft make its attitude control extremely complicated. The key problem to be solved in the design of the reentry vehicle control system is to suppress the influence of the above nonlinear, strong coupling and uncertainty on the system performance. [0003] At present, there are many nonlinear methods for the desi...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
Inventor 刘向东王亮盛永智
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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