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Tangent Linearization Method for Nonlinear Tracking Controller Design of Flight Control System

A technology of tracking controller and tracking control, which is applied in the direction of general control system, control/regulation system, adaptive control, etc., to achieve the effect of good engineering application value

Active Publication Date: 2017-04-12
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 for Nonlinear Tracking Controller Design of Flight Control System
  • Tangent Linearization Method for Nonlinear Tracking Controller Design of Flight Control System
  • Tangent Linearization Method for Nonlinear Tracking Controller Design of Flight Control System

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Embodiment

[0050] The design method of a class of flight control system nonlinear tracking controller based on tangent linearization method includes the following steps:

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

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

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

[0054] Step 4: Substitute the feedback control gain obtained in Eq. (13) into Eq. (11), and the system state equation (5) is combined with the given initial conditions to solve the nonlinear control law u(t) in real time Then, the control law u(t) and the original aircraft control system are formed into a closed-loop system, and the differential equation is solved to obtain the tracking control law of the nonlinear flight cont...

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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 for a non-linear control tracking control system of an aircraft. Background technique [0002] Modern aircraft have a large range of flying altitude and flying Mach number, and the flying 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 a method for linearization and trajectory tracking control system based on unbalanced state. [0003] In traditional flight control modeling, the modeling method uses the traditional Jacobian linearization method. However, the precondition for the Jacobian linearization method to be used is that the system state is based on a small disturbance near t...

Claims

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Application Information

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Patent Type & Authority Patents(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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