Guidance method based on sight angle nonlinear anti-saturation and uncertainty compensation

A technology of uncertainty and sight angle, applied in non-electric variable control, vehicle position/route/height control, attitude control, etc., can solve problems such as weak robustness and poor adaptability, and achieve improved guidance Accuracy, improved fitness and robustness, and high engineering application value

Active Publication Date: 2020-11-10
NAVAL AVIATION UNIV
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Problems solved by technology

[0006] The purpose of the present invention is to provide a guidance method based on line-of-sight angle nonlinear anti-saturation and uncertainty compensation, and then at least to a certain extent overcome the problems of poor robustness and poor adaptability of traditional guidance methods

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  • Guidance method based on sight angle nonlinear anti-saturation and uncertainty compensation
  • Guidance method based on sight angle nonlinear anti-saturation and uncertainty compensation
  • Guidance method based on sight angle nonlinear anti-saturation and uncertainty compensation

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Embodiment Construction

[0047] Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete and fully convey the concept of example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. In the following description, numerous specific details are provided in order to give a thorough understanding of embodiments of the invention. However, those skilled in the art will appreciate that the technical solution of the present invention may be practiced without one or more of the specific details, or other methods, components, devices, steps, etc. may be adopted. In other instances, well-known technical solutions have not been shown or descr...

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Abstract

The invention discloses a guidance method based on sight angle nonlinear anti-saturation and uncertainty compensation, belongs to the technical field of aircraft flight guidance, and is characterizedin that approximate differential signals are obtained by only measuring sight angle information of an aircraft and constructing a third-order inertia nonlinear filter to provide damping required by aircraft guidance; a corresponding nonlinear signal is obtained through nonlinear anti-saturation transformation; and finally, by constructing a guidance interference and uncertainty compensator, a compensation signal of uncertainty interference of the guidance system is obtained, so that a good foundation is laid for improving the precision and fitness of the whole guidance design. Finally, the compensation signal, the sight angle signal, the anti-saturation nonlinear transformation signal and the integral signal are integrated to form a guidance integrated signal. The novel guidance method based on interference estimation compensation has the advantages of being simple in measurement information, high in guidance precision, good in robustness and wide in adaptability.

Description

technical field [0001] The invention belongs to the field of aircraft flight guidance, and in particular relates to a guidance method for nonlinear anti-saturation and uncertainty compensation of aircraft line-of-sight angles. Background technique [0002] The traditional aircraft guidance method generally uses the seeker to measure the line-of-sight angular velocity, but it is not easy to accurately measure the angular velocity. Moreover, the line-of-sight angular rate will increase when it reaches the end of the target, causing the line-of-sight angular rate to saturate. Such as proportional guidance, when using the line-of-sight angular rate to form the final guidance signal, there will be a problem that the signal will enter saturation prematurely at the end, resulting in an increase in the amount of miss. [0003] At the same time, because the high-speed aircraft dynamics model is very complex, although the wind tunnel data model used in the design is as accurate as po...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08B64G1/24
CPCG05D1/0825B64G1/24B64G1/244B64G1/245
Inventor 雷军委李恒晋玉强王瑞奇李辉于进勇
Owner NAVAL AVIATION UNIV
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