Semi-strapdown air-to-air missile guidance method based on sliding mode variable structural theory

Abstract

The invention discloses a semi-strapdown air-to-air missile guidance method based on a sliding mode variable structural theory. The semi-strapdown air-to-air missile guidance method comprises the following steps of 1, acquiring a missile-target line-of-sight turn rate differential model under a line-of-sight coordinate system; 2, acquiring a motion tracking sliding mode guidance rule; and 3, acquiring an expected line-of-sight turn rate xd. According to the method, a sigmoid function is applied to the sliding mode surface design of the motion tracking sliding mode guidance rule, the missile-target line-of-sight angular rate is improved at the initial guidance stage, the estimation to the target motion state is improved, the missile-target line-of-sight angular rate is made to be zero at the last guidance stage, the miss distance is lowered, and the missile hit precision is improved.

Description

technical field [0001] The invention belongs to the field of weapon technology and guidance methods, and relates to the research on air-to-air missile guidance methods, in particular to a semi-strapdown infrared imaging short-range combat air-to-air missile guidance method. Background technique [0002] With the continuous enhancement of target maneuverability in future air combat, further requirements are put forward for the guidance capability of missiles. In order to quickly find and track the target, and realize the rapid acquisition and precise tracking of the target, the seeker of the missile is changed from the traditional stable platform type to the semi-strapdown mode. Due to the change of the seeker, the missile can obtain the relative motion of the target. The state mode has changed, and the traditional guidance law can no longer meet the guidance requirements, and a new guidance law needs to be designed. [0003] Traditional guidance laws, such as proportional g...

AI Technical Summary

Problems solved by technology

In order to quickly find and track the target, and realize the rapid acquisition and precise tracking of the target, the seeker of the missile is changed from the traditional stable platform type to the semi-strapdown mode. Due to the change of the seeker, the missile can obtain the relative motion of the target. The state mode has changed, the traditional guidance law can no longer meet the guidance requirements, and a new guidance law needs to be designed

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