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Tangent linearization method of flight control system nonlinear tracking controller design

A flight control system, non-linear control technology, used in general control systems, control/regulation systems, adaptive control, etc.

Active Publication Date: 2013-12-18
PLA SECOND ARTILLERY ENGINEERING UNIVERSITY
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Problems solved by technology

But so far, there are few results in controller design using tangent linearization method in the existing literature

Method used

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  • Tangent linearization method of flight control system nonlinear tracking controller design
  • Tangent linearization method of flight control system nonlinear tracking controller design
  • Tangent linearization method of flight control system nonlinear tracking controller design

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Embodiment

[0050] A design method of a nonlinear tracking controller for a flight control system based on the tangent linearization method, comprising the following steps:

[0051] Step 1: According to formula (1), (2), (3), (4), (5) to expand the state of the nonlinear control system of the aircraft

[0052] Step 2: Calculate the state differential equation of the tangent linearization system according to formulas (6), (7), (8,) (9), (10), (11), (12);

[0053] Step 3: Design the time-varying linear system feedback stabilization gain according to equations (13), (14), and (15);

[0054] Step 4: Substitute the feedback control gain obtained in formula (13) into formula (11), and solve the nonlinear control law u(t) in real time through the given initial conditions and simultaneous system state equation (5) , and then form a closed-loop system with the control law u(t) and the original aircraft control system, and solve the differential equation to obtain the tracking control law of the n...

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Abstract

The invention relates to a tangent linearization method of an aircraft nonlinear control tracking control system. Regarding nonlinear tracking controllers of a flight control system, the tangent linearization method of the aircraft nonlinear tracking control system is characterized by including the steps that state extension is conducted on the aircraft nonlinear control system, a state differential equation of a tangent linearization system is calculated; time varying linear system feedback stabilization gains are designed; the differential equation is solved to obtain four steps of a nonlinear flight control system tracking control law. Compared with the prior art, the method for designing the aircraft control system tracking controller based on tangent linearization is provided, complete equivalent linearization modeling can be conducted on the complex flight control system, and the tracking controller design can be conducted on the control system, an effective analysis tool is provided for implementing the control system in real time, the powerful theoretical basis and the technical support are further provided for meeting high requirements in the flight control system design aspects, and the method has good engineering application value.

Description

technical field [0001] The invention belongs to the technical field of automatic control, and relates to a tangent linearization method of a non-linear control tracking control system of an aircraft. Background technique [0002] Modern aircraft have a wide range of flight altitudes and flight Mach numbers, and the flight environment is complex. During the flight, the aerodynamic and aerothermal characteristics of the aircraft change drastically. It is difficult to keep the aircraft flying stably under equilibrium conditions, which causes the aircraft to deviate from the expected flight trajectory. . Therefore, it is necessary to seek methods for non-equilibrium state-based linearization and trajectory-following control systems. [0003] In the traditional flight control modeling, the modeling method adopts the traditional Jacobian linearization method. However, the prerequisite for the use of the Jacobian linearization method is that the system state is based on small dis...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
Inventor 胡昌华蔡光斌何华锋周涛马清亮扈晓翔
Owner PLA SECOND ARTILLERY ENGINEERING UNIVERSITY
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