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High-speed aircraft self-adaptation control method based on movement state comprehensive identification

A high-speed aircraft, adaptive control technology, applied in the direction of adaptive control, general control system, control/regulation system, etc., can solve problems such as long convergence time

Inactive Publication Date: 2013-07-10
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

In practical engineering applications, the identification method has the disadvantage of long convergence time, and at the same time, the offline pre-booked controller parameters are insufficient when the control system of high-speed aircraft is faced with the requirements of variable parameters, fast response and high-efficiency control

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  • High-speed aircraft self-adaptation control method based on movement state comprehensive identification

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Embodiment Construction

[0044] refer to Figure 1~3 . The specific steps of the high-speed aircraft adaptive control method based on the comprehensive identification of the motion state of the present invention are as follows:

[0045] Step 1: Establish a high-speed aircraft model, and perform small disturbance linearization to obtain a characteristic model of the high-speed aircraft's motion state.

[0046] Considering the high-speed aircraft as a rigid body, the longitudinal motion model is

[0047]

[0048] Small disturbance linearization is performed on the longitudinal motion model to obtain a low-order disturbance model of attitude in a short time period. Take a ballistic point V 0 ,θ 0 , h 0 The linearization reference point at is α 0 and its trim rudder deflection δ z0 , the pitch rate then there is

[0049] α · = ω ...

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Abstract

The invention discloses a high-speed aircraft self-adaptation control method based on movement state comprehensive identification. The high-speed aircraft self-adaptation control method based on the movement state comprehensive identification is used for solving the technical problem that an existing hypersonic aircraft robust control method based on a characteristic model is long in convergence time. The high-speed aircraft self-adaptation control method based on the movement state comprehensive identification comprises the steps of firstly building a high-speed aircraft model, conducting small perturbation linearization, and obtaining a characteristic model of high-speed aircraft movement states; then on-line building characteristic state quantity of the control oriented characteristic model quickly and measurably; and then designing a self-correcting and self-adaptation control method according to the obtained characteristic model. Due to the fact that the characteristic state quantity of the control oriented characteristic model is quickly obtained through a method of the movement state comprehensive identification, on-line identification is needless, on-line generation of controller parameters can be conducted directly according to real-time dynamic characteristics of an object through a self-correcting and self-adaptation control strategy, and thus the parameters of a controller are enabled to be adjusted in time according to actual situations in an actual fly process.

Description

technical field [0001] The invention relates to an adaptive control method for a high-speed aircraft, in particular to an adaptive control method for a high-speed aircraft based on comprehensive identification of motion states. Background technique [0002] Compared with traditional aircraft, the coupling between airframe, propulsion system and structural dynamics of high-speed aircraft is stronger. At the same time, due to the characteristics of hypersonic flow, there is a complex nonlinear relationship between the aerodynamic characteristics and attitude angle of high-speed aircraft, and the aerodynamic modeling is complicated. For this kind of high-order nonlinear object model, it is difficult to design the controller directly. Therefore, the control system design of high-speed aircraft is faced with the problems of variable parameters, fast response and high-efficiency control (Cui Erjie, Research and Development Status and Key Technical Issues of Near Space Vehicles, Pr...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
Inventor 林鹏周军王立祺王霄婷葛振振
Owner NORTHWESTERN POLYTECHNICAL UNIV
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