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

A sliding mode variable structure, air-to-air missile technology, applied in the field of guidance and weapon technology, can solve the problem that the guidance law cannot meet the guidance requirements, and achieve the effect of guaranteeing the guidance accuracy of the missile

Active Publication Date: 2016-11-09
BEIHANG UNIV +2
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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 ...

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

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Embodiment Construction

[0019] The present invention will be further described in detail with reference to the accompanying drawings and embodiments.

[0020] The present invention is a semi-strapdown air-to-air missile guidance method based on the sliding mode variable structure theory, the process is as follows figure 1 shown, including the following steps:

[0021] Step 1: Obtain the differential model of bullet eye sight turn rate in the line of sight coordinate system;

[0022] In three-dimensional space, the relative motion relationship between the missile and the target is established as figure 2 shown, where: ox G the y G z G is the inertial space coordinate system, ox S the y S z S is the line-of-sight coordinate system of the projectile, the interceptor missile coincides with the origin of the coordinate system, the subscripts M and T represent the missile and the target respectively, and ox S It is LOS (line-of-sight).

[0023] In the line of sight coordinate system, according to...

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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...

Claims

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Application Information

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IPC IPC(8): F41G3/00
CPCF41G3/00
Inventor 易科陈建任章李清东晏涛贾晓洪吴军彪周卫文
Owner BEIHANG UNIV
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