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Robust Attitude Control Method for Tactical Missile Based on Disturbance Estimation and Compensation

A technology of attitude control and missiles, applied in the direction of attitude control, non-electric variable control, control/adjustment system, etc., can solve the problems that the performance index requirements cannot be reflected, and the unmeasurable state cannot be obtained more accurately, so as to be beneficial to engineering realization , the effect of strong applicability

Active Publication Date: 2018-09-18
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0006] The purpose of the present invention is to provide a method for robust attitude control of tactical missiles based on disturbance estimation and compensation. The index requirements are reflected in the design of the control law, and satisfactory time-domain performance can only be obtained by adjusting the parameters; and this method uses a disturbance observer, which is a technical problem that cannot obtain more accurate results for unmeasurable states

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  • Robust Attitude Control Method for Tactical Missile Based on Disturbance Estimation and Compensation
  • Robust Attitude Control Method for Tactical Missile Based on Disturbance Estimation and Compensation
  • Robust Attitude Control Method for Tactical Missile Based on Disturbance Estimation and Compensation

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[0091] The accompanying drawings constituting a part of this application are used to provide further understanding of the present invention, and the schematic embodiments and descriptions of the present invention are used to explain the present invention, and do not constitute an improper limitation of the present invention.

[0092] The systems in this paper refer to the bomb control system.

[0093] The flow chart of the missile robust attitude control method based on disturbance estimation and compensation proposed by the present invention is as follows: figure 1 shown, including the following steps:

[0094] Step S100: The vertical plane dynamic model established is:

[0095]

[0096] Among them, M, α, q and γ represent the Mach number, angle of attack, pitch rate and flight path angle, respectively, which are variables in the flight process. C n and C m are the normal force and pitch moment coefficients, respectively.

[0097] In step S200, the motion model is lin...

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Abstract

The invention provides a tactical missile robust attitude control method based on perturbation estimation and compensation. Nondeterminacy, perturbation and model nonlinear terms acting on a system are all regarded as equivalent input perturbation applied to an input channel, then real-time estimation and compensation are conducted on the perturbation by designing a linear generalized extended state observer, so that the nondeterminacy and perturbation acting on the system are reduced, and then the effect that a controller meets the requirements various performance indexes such as tracking performance, limiting control amount and robust stability of the closed-loop system can be designed through a robust control method. According to the tactical missile robust attitude control method, a precise system model and prior information about perturbation are not needed, the available total state of the system is not required, and high applicability is achieved. The tactical missile robust attitude control method is suitable for the field of aircraft attitude control.

Description

technical field [0001] The invention relates to the technical field of aircraft attitude control, in particular to a robust attitude control method for tactical missiles based on disturbance estimation and compensation. Background technique [0002] Short-range tactical ballistic missiles are widely used in modern high-tech local wars because of their fast flight speed, strong defense penetration capability, flexible use and high combat effectiveness. With the intensification of offensive and defensive confrontation between missile technology and anti-missile technology, short-range tactical ballistic missiles will develop towards the trend of full controllability, strong maneuverability, and diverse ballistic changes. The corresponding flight dynamics model has strong nonlinearity, strong coupling, and The characteristics of large parameter variation range, external interference and uncertain factors have brought great challenges to the design of the attitude control system...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F42B15/01G05D1/08
CPCF42B15/01G05D1/0825
Inventor 李健董毅杨晓骞郑伟
Owner NAT UNIV OF DEFENSE TECH
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