System for measuring center of mass of missile

A measurement system and missile technology, applied in the direction of measurement devices, ammunition, ammunition testing, etc., can solve problems such as low accuracy

Inactive Publication Date: 2017-02-15
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The existing centroid measurement method of a certain type of missile is realized by the traditional lever principle. This measurement method requires multiple adjustments to obtain the approximate position of the missile centroid, and the accuracy is relatively low.

Method used

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  • System for measuring center of mass of missile
  • System for measuring center of mass of missile
  • System for measuring center of mass of missile

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Experimental program
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Embodiment Construction

[0012] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0013] The missile center of mass measurement system of the present invention comprises a measuring instrument, two bridge-type weighing sensors 12, two support brackets 13 and a connecting rod 14, and the measuring instrument includes an upper sealing plate 1, an instrument box 2, a control board 3, and an intelligent display card 4. Operation panel 5, data interface 6, charging interface 7, main control unit 8, mV unit 9, digital electrical unit 10 and analog electrical unit 11.

[0014] figure 1 Among them, the control board 3 and the smart display card 4 are stacked together through the pin socket, and are fixed in the instrument box 2 by bolts, and the upper sealing plate 1 is used for mechanical sealing and electrical isolation, and the data interface 6 realizes data collection interaction, charging Interface 7 charges the battery.

[0015] figure 2...

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PUM

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Abstract

The invention discloses a system for measuring the center of mass of a missile. The system comprises a measuring instrument, two bridge type weighing sensors, two supporting brackets and connecting rods; the two supporting brackets are connected through the connecting rods and are used for supporting the missile; the two bridge type weighing sensors are arranged on the two supporting brackets and are used for weighing the missile; graduated scales are arranged on the connecting rods; the connecting rods can connect and fix the two supporting brackets at different distances; and the measuring instrument is connected with the two bridge type weighing sensors, is used for acquiring and processing data and is used for displaying the position of the center of mass of the missile. With the system, out-field targeting hanging point test work of the missile is facilitated, the hanging point can be positioned quickly, the system is high in integrity and simple to operate, and the reliability and the practicability of out-field application are sufficiently guaranteed.

Description

technical field [0001] The invention relates to a missile centroid measurement system, which is suitable for the test environment of the missile's outfield target shooting and hanging point. Background technique [0002] As a kind of strategic material, missiles can be used to strike targets including tanks, armored vehicles, ground fortifications, etc. Recently, with the rapid development of drones, more and more air-to-surface missiles are equipped on drones for target detection. Strike, the handling of the position of the missile hanging point plays an important role in the balance of the UAV and the missile. The optimal position of the missile hanging point is the position of the center of mass of the missile. The existing centroid measurement method of a certain type of missile is realized by the traditional lever principle. This measurement method requires multiple adjustments to obtain the approximate position of the missile centroid, and the accuracy is relatively lo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B35/00G01M1/12
CPCF42B35/00G01M1/122
Inventor 牛志朝郑飞嵇治刚丛晖吕松天梁凤麒
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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