Second-order sliding mode guidance law considering second-order dynamic characteristics of autopilot

An autopilot, second-order sliding mode technology, applied in the directions of instruments, adaptive control, control/regulation systems, etc., can solve problems such as guidance performance degradation, and achieve the effect of improving global rapid convergence

Inactive Publication Date: 2019-06-18
ARMY ENG UNIV OF PLA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, in the design process of the guidance law, the autopilot is often regarded as an ideal link, and the influence of the dynamic characteristics of the autopilot on the guidance performance is ignored.
normally, the dynamic nature of the autopilot degrades guidance performance, especially when engaging maneuvering targets

Method used

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  • Second-order sliding mode guidance law considering second-order dynamic characteristics of autopilot
  • Second-order sliding mode guidance law considering second-order dynamic characteristics of autopilot
  • Second-order sliding mode guidance law considering second-order dynamic characteristics of autopilot

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Embodiment Construction

[0018] projectile relative motion model

[0019] figure 1 It shows the relative motion relationship of projectiles and targets established on the inertial coordinate system OXYZ. In the figure, M and T represent missile and target respectively, OX S Y S Z S is the projectile line of sight coordinate system, r is the relative distance of the projectile, q and η are the inclination angle and deflection angle of the projectile line of sight, respectively. v m and v t are the velocities of the missile and the target, respectively, θ m and are the inclination angle and deflection angle of the missile trajectory, θ t and are the track inclination and declination of the target, respectively.

[0020] According to the relative motion relationship of the projectile and the target, the relative motion equations of the projectile and the target can be obtained as follows:

[0021]

[0022] In the formula: a tr 、a tq 、a tη and a mr 、a mq 、a mη are the acceleration ...

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Abstract

The invention discloses a second-order sliding mode guidance law considering the second-order dynamic characteristics of an autopilot. According to the second-order sliding mode guidance law considering the second-order dynamic characteristics of the autopilot, a first object is guided to a second object; the autopilot of the first object is regarded as a second-order link; the second-order link and a relative motion model with an attack angle constraint are combined so as to obtain a guidance system state considering the second-order dynamic characteristic of the autopilot; and a second-ordersliding mode guidance law with an attack angle constraint and the guidance system state considering the second-order dynamic characteristics of the autopilot are combined, so that the second-order sliding mode guidance law considering the second-order dynamic characteristics of the autopilot can be obtained.

Description

technical field [0001] The invention relates to the field of motion control, in particular to a second-order sliding mode guidance law considering the second-order dynamic characteristics of an autopilot. Background technique [0002] In modern warfare, many missiles (such as some anti-ship missiles, anti-tank missiles, anti-aircraft missiles, etc.) need to hit the target at a certain angle of attack to increase the damage effectiveness of the warhead. Therefore, the attack angle constraint is a problem that needs to be considered in the design of the guidance law. After more than 40 years of development, research results on guidance laws with attack angle constraints mainly include optimal guidance laws, improved proportional guidance laws, and variable structure guidance laws. However, in the design process of the guidance law, the autopilot is often regarded as an ideal link, and the influence of the dynamic characteristics of the autopilot on the guidance performance is...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
Inventor 傅振华杨锁昌张宽桥魏保华赵慎柳鹏
Owner ARMY ENG UNIV OF PLA
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