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Ejection additional load simulation test system

A technology for simulating test system and additional load, applied in the field of weapons, can solve problems such as structural optimization of launchers, and achieve the effects of structural optimization, load reduction, and simple structure

Active Publication Date: 2014-09-17
BEIJING INST OF SPACE LAUNCH TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, there is no relevant technology at home and abroad, which can simulate and analyze the size of the additional load of the ejection and obtain accurate data before designing the launch platform. Timely load on the launch platform, improving ejection safety and stability

Method used

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  • Ejection additional load simulation test system

Examples

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Embodiment Construction

[0021] like figure 2 Shown is the first embodiment of the present invention, a static simulation test system for ejection additional load, including an outer frame 100 composed of a horizontally arranged upper cover plate 11, a lower cover plate 12, and vertically arranged straight pull rods 13. The shape of the cover plate 11 and the lower cover plate 12 is generally circular, of course, it can also be designed as a square according to actual needs. The positions of the upper cover plate 11 and the lower cover plate 12 are symmetrical up and down, and the outer peripheries of the upper cover plate 11 and the lower cover plate 12 are fixedly connected with several straight pull rods 13. Preferably, the upper cover plate 11 and the lower cover plate 12 are provided with Several screw holes, the upper and lower ends of the straight pull rod 13 respectively penetrate the screw holes on the upper cover plate 11 and the lower cover plate 12, and then fix them with bolts, so that w...

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PUM

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Abstract

The invention provides an ejection additional load simulation test system, and relates to a missile or torpedo launcher. The ejection additional load simulation test system comprises an outer frame which is internally provided with a guide cylinder, a sliding cylinder and a flexible base, wherein the sliding cylinder is arranged above the flexible base; the guide cylinder is sheathed in the sliding cylinder; a tension sensor is arranged between the guide cylinder and the sliding cylinder; pressure is applied into a closed inner cavity formed by the guide cylinder, the sliding cylinder and the flexible base, so that the flexible base is expanded and is contacted with the ground; an ejection additional load can be tested by the tension sensor. The invention aims at providing the ejection additional load simulation test system which is simple in structure, low in cost and simple and convenient to operate and is capable of conveniently and accurately testing the additional load, so that the structure of the launcher can be optimized, the load of a launch platform can be reduced during ejection, and ejection safety and stability are improved.

Description

technical field [0001] The invention relates to the technical field of weapons, in particular to a missile or torpedo launching device. Background technique [0002] Common missile launching devices adopt flexible base suspension launch technology, such as figure 1 As shown, when the missile is ejected, the flexible base 105 transfers most of the ejection internal pressure load F to the ground 101, and the rest is transferred to the launch platform 104 through the rotating lug 103 on the launch tube 102. This part of the ejection load is called the ejection additional load. Its size directly affects the ejection safety and stability of the launch platform. At present, there is no relevant technology at home and abroad, which can simulate and analyze the size of the additional load of the ejection and obtain accurate data before designing the launch platform. Timely load on the launching platform, improving ejection safety and stability. Contents of the invention [0003...

Claims

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Application Information

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IPC IPC(8): F41A31/00
Inventor 邢春鹏高原吴新跃张国栋赵衡柱王华吉张罗刘懿敏申鹏胡文俊
Owner BEIJING INST OF SPACE LAUNCH TECH
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