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Double-pulse ignition method for actively suppressing swing of pulse force control missile body

A technology of active suppression and pulse force, applied to self-propelled missiles, projectiles, offensive equipment, etc., can solve the problems of reduced operational efficiency of pulse force control missiles, long intervals, and inability to achieve continuous ignition at the end

Active Publication Date: 2014-01-01
中国北方工业有限公司 +1
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AI Technical Summary

Problems solved by technology

The main problem of using the single-pulse ignition scheme is that the interval between two controls is long. When the terminal guidance time is fixed, the control times of the pulse engine are limited, and the terminal cannot achieve continuous ignition, which reduces the pulse force control missile. Correction ability and correction accuracy greatly reduce the operational effectiveness of pulse force control missiles

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  • Double-pulse ignition method for actively suppressing swing of pulse force control missile body
  • Double-pulse ignition method for actively suppressing swing of pulse force control missile body
  • Double-pulse ignition method for actively suppressing swing of pulse force control missile body

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Embodiment Construction

[0055] The present invention will be further described below in conjunction with the accompanying drawings.

[0056]The open-loop damping of the pulse force control missile body is very low, less than 0.1, so the dynamic characteristics of the projectile body are very poor after the pulse force is applied.

[0057] Such as figure 1 As shown, in order to achieve the purpose of reducing the cost of the projectile, no accelerometer and angular rate gyro are installed on the projectile, so the damping of the projectile cannot be artificially increased to form a damping loop; Poor, long system response time. During the trajectory correction process, the detector also follows the dynamic movement of the projectile, and the next target detection is only available after the transition process of the angle of attack is over, so the control period must also be greater than the dynamic response transition time of the projectile: t s ≤ T c (where T c is the control cycle of the contro...

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Abstract

The invention relates to a double-pulse ignition method for actively suppressing swing of a pulse force control missile body. The double-pulse ignition method is characterized by comprising the following steps of starting a control cycle, collecting a strap-down detector output signal and a tachometer output signal by a missile-borne computer; calculating delay time deltat1 by the missile-borne computer according to a pulse engine ignition control algorithm, and igniting a first pulse engine; starting timing by the missile-borne computer after the first pulse engine is ignited, and controlling a second pulse engine to be ignited in the same direction after the delay time deltat2 is delayed, wherein the second pulse engine and the first pulse engine are symmetrical in position about the axle of the missile body; ending the control cycle, judging whether a target is hit or not, ending guidance if the target is hit, otherwise, starting the next control cycle after time interval Td, and returning.

Description

technical field [0001] The invention relates to a method for actively suppressing the swing of a missile body, in particular to a dual-pulse ignition method for actively suppressing pulse force to control the swing of a missile body. Background technique [0002] Pulse thrust vector guidance control technology is a novel control technology, referred to as pulse force control, which mainly uses the pulse force generated by the small solid or liquid pulse engine as the control force, even in thin atmosphere or space, it can still produce effective Therefore, this technology is used in a variety of missiles, such as ground-based interceptors, standard SM-3 missiles and theater high altitude area defense system THAAD interceptors and Advanced Patriot advanced capability missiles. Since the action time of the small pulse engine is generally very short, about a few milliseconds to tens of milliseconds, it is required to respond very quickly to complete the rapid maneuvering of the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B15/00
Inventor 王江唐义平宋韬范世鹏
Owner 中国北方工业有限公司
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