Missile simulation launching device

Abstract

The invention relates to a missile simulation launching device. The missile simulation launching device comprises a test platform, a guide rail, a simulation missile, a missile mounting rack, an air pressure thrust system, an air pressure resistance system and an air compressor, wherein the test platform is a cubic structure frame; the guide rail is fixedly mounted on the test platform; the upperpart of the missile mounting rack is fixedly connected with the simulation missile, and the lower part of the missile mounting rack is slidably connected with the guide rail; the air pressure thrust system is arranged at the rear end of the simulation missile; the air pressure resistance system is arranged at the front end of the simulation missile; the air pressure thrust system and the air pressure resistance system are both connected with an air compressor air channel; and the simulation missile and the missile mounting rack do reciprocating motion between the air pressure thrust system andthe air pressure resistance system. The pressure of a power source of air is adjusted through the air pressure thrust system, the launching thrust of the simulation missile is specifically and accurately controlled in data, and the operation is more accurate than ejection; and the thrust action time can be controlled, and thus the requirement for simulating a real continuous high-overload environment is met.

Description

technical field [0001] The application relates to the technical field of simulation experiments of missiles and guided rockets, in particular to a missile simulation launching device. Background technique [0002] Exploring the motion state of missiles and guided rockets is a complex experimental project. In order to accurately simulate various parameters of missiles and guided rockets during launch, it is necessary to study the mechanical environment of missiles and guided rockets during launch. Carry out simulations to assess whether the strength, mechanical and electrical properties of missiles and guided rockets meet the requirements of large axial overload resistance during launch, especially when missiles and guided missiles are equipped with a seeker , Whether the seeker can reliably lock the target without losing the ability to sustain high overload during the launch process, etc. In addition, the strength of the main components including the seeker, such as detecto...

AI Technical Summary

Problems solved by technology

[0004] The defect of the existing method is: for ejection, the force of ejection is attenuated, the mechanical environment is quite different from the real launch process, and the duration of the overload capability is quite different from the real launch process, that is, the existing simulated pneumatic launch device The simulated conditions created have a large deviation from the actual situation

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