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Guided missile track and posture coordinated control system and method under side window detection conditions

A technology for missile trajectory and coordinated control, which is used in self-propelled missiles, offensive equipment, projectiles, etc.

Active Publication Date: 2017-05-24
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

There is no open literature at home and abroad to study the coordinated control of missile trajectory control and attitude control. This invention will conduct research on this technical problem and provide a missile trajectory and attitude coordinated control method under the condition of side window detection to determine the attitude. Control command of angle controller

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  • Guided missile track and posture coordinated control system and method under side window detection conditions
  • Guided missile track and posture coordinated control system and method under side window detection conditions
  • Guided missile track and posture coordinated control system and method under side window detection conditions

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Embodiment Construction

[0100] The present invention is described in further detail below in conjunction with accompanying drawing:

[0101] see figure 1 , the present invention builds the coordinated control system of missile trajectory and attitude under the condition of side window detection, including an initial roll angle command calculation module, an initial index angle calculation module, a roll angle command difference calculation module with feedback items, and an index under the condition of feedback items An angle calculation module and a final roll angle command calculation module, wherein the roll angle command difference calculation module with feedback items and the index angle calculation module with feedback items form a feedback control module.

[0102] Such as figure 2 As shown, the missile trajectory attitude coordination control method under the side window detection condition of the present invention comprises the following steps:

[0103] Step 1: According to the initial in...

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Abstract

The invention discloses a guided missile track and posture coordinated control system under side window detection conditions. The system comprises an initial roll angle command calculation module, an initial index angle calculation module, a roll angle command deviation calculation module with feedback items, an index angle calculation module under the condition providing the feedback items and a final roll angle command calculation module. A guided missile track and posture coordinated control method under the side window detection conditions is provided; and the problem about control commands of a roll angle controller is solved, a guided missile provided with a side window guide head can meet the side window detection posture control requirement and the guided missile guidance accuracy requirement at the same time.

Description

【Technical field】 [0001] The invention belongs to the technical field of guidance and control, and in particular relates to a missile trajectory and attitude coordination control system and method under the condition of side window detection. 【Background technique】 [0002] Supersonic missiles in the atmosphere have strong mobile penetration capabilities and are also an important weapon for intercepting various reentry warheads. The aerodynamic heating of missiles flying at supersonic speeds in the atmosphere will affect the detection accuracy of the seeker arranged at the head of the missile body. In order to solve this problem, the seeker is usually arranged on the side of the missile body to avoid the heat-flux-intensive area of ​​the missile head. This target detection method is side window detection. The side window detection technology can not only be applied to anti-aircraft missiles, but also for sea-skimming cruise missiles, the seeker is arranged on the side of th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B15/01
CPCF42B15/01
Inventor 余英侯明善刘柏均李雅君
Owner NORTHWESTERN POLYTECHNICAL UNIV
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