Active recycling control method of air-to-air missile experiment missile

A control method and technology for air-to-air missiles, which are applied in the test of ammunition, ammunition, self-propelled missiles, etc., can solve the problems of low recovery efficiency, incomplete missile wreckage, and restriction of missile flight parameter analysis work, so as to reduce development costs and accelerate Development progress, the effect of promoting failure analysis and failure reset work

Active Publication Date: 2008-11-05
CHINA AIR TO AIR MISSILE INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, the flight data in the air test can only be obtained through ground and air telemetry parameters, but due to the limited telemetry data, the analysis of missile flight parameters is greatly restricted
Moreover, at present, air-to-air missiles are usually recovere...

Method used

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  • Active recycling control method of air-to-air missile experiment missile
  • Active recycling control method of air-to-air missile experiment missile

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Embodiment Construction

[0017] Such as figure 1 , figure 2 As shown, the active recovery control method of the air-to-air missile test missile of the present invention, by adding an active recovery control module and a built-in parachute inside the missile, the active recovery control module is automatically started after the test fails or the flight test task is completed, and the control missile adopts high After the ballistic trajectory reaches the set goal of deceleration and attitude adjustment, a parachute opening control signal is given to open the deceleration parachute to complete the active recovery of the missile. Missile deceleration and attitude adjustment is the missile's flight trajectory, flight speed and attitude information calculated by the missile-borne strapdown inertial navigation system, and the missile's flight trajectory and speed are adaptively controlled through the autopilot to finally meet the set speed and attitude requirements. .

[0018] The deceleration and attitud...

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Abstract

The invention relates to an intiative reclaim control method of the air to air missile experiment missile. The method is added with an intiative reclaim control module and a built-in ballute in the inner of the missile, when the experiment occurs with fault or completes the flying test, the intiative reclaim control module is automatically started. The Control missile adopts the high dropping trajectory to reach the set deceleratatoin attitude-adjusting, then gives the parachute opening control signals, opens the deceleratatoin drag-parachute, completes the ntiative reclaim of the missile reclaim. After the missile reclaim control technology is adopted, the test personnel on the ground obtains the precious software working state and the flying test data in the flying, which realizes the effective utilization of the flying test missile. The technology advances the failure analysis and the zero adjustment work, which is of evident importance to accelerate the development speed of the missile.

Description

technical field [0001] The invention relates to an active recovery control method of an air-to-air missile test missile in the missile field flight test of an air-to-air missile weapon system. Background technique [0002] After the air-to-air missile fails in the test or completes the air flight test, it is generally destroyed in the air by self-exploding fuze, and the rest of the wreckage is damaged during the landing impact. Therefore, the flight data in the air test can only be obtained through the ground and air telemetry parameters, but due to the limited telemetry data, the analysis of the missile's flight parameters is greatly restricted. Moreover, at present, air-to-air missiles are usually recovered by picking up free-falling wreckage in the field flight test. The recovery efficiency is low and the recovered missile wreckage is incomplete due to the free-fall of the missile hitting the ground, which affects the accuracy of the flight test failure. Analysis and pos...

Claims

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Application Information

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IPC IPC(8): F42B15/01F42B35/00
Inventor 梁晓庚贾晓洪李友年王建琦陈星阳
Owner CHINA AIR TO AIR MISSILE INST
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