Self-catapulting launching device for guided missile

Abstract

The invention provides a self-catapulting launching device for a guided missile. The self-catapulting launching device comprises a flow-guiding cone, a limiting mechanism, a buffering device, a long guide rail, a short guide rail and adaptors; the flow-guiding cone is fixedly connected to the bottom end of a launching cylinder, the buffering device is fixedly connected to the outlet of the launching cylinder, the long guide rail and the short guide rail are fixed to the inner wall of the launching cylinder in the axis direction of the launching cylinder and are staggered and evenly distributed in the launching cylinder, grooves of the adaptors are slidingly matched with the long guide rail, gaps between two adjacent adaptors are slidingly matched with the short guide rail, the limiting mechanism is fixedly connected to the inner wall of the launching cylinder, the adaptors are limited to move to the interior of the cylinder in the axis direction of the launching cylinder, and after guided missile is filled, a closed space is defined by the bottoms of the adaptors, the bottom of the guided missile, the end face of the bottom of the long guide rail and the end face of the bottom of the short guide rail in the launching cylinder. The initial launching precision of the guided missile can be improved, and the manufacturing cost and the maintenance cost of the launching device are effectively lowered.

Description

technical field [0001] The invention belongs to the technical field of missile launching devices, and in particular relates to a missile self-catapulting launching device. Background technique [0002] At present, there are two commonly used missile launch technologies in the world. One is thermal launch, that is, the missile is launched directly from the launch tube by using the thrust of the main engine; Speed ​​and then the firing mode of the engine ignition. In the early ship-borne missile launch systems, the United States and other Western countries mostly used thermal launch technology, such as the MK41 vertical launch system in the United States; while Russia focused on ejection technology, such as the SA-N-6 vertical launch system. At the beginning of the 1990s, the United States demonstrated and compared the two launch technologies, and gradually began to pay attention to ejection technology. Western countries began to develop vertical ejection systems suitable for...

AI Technical Summary

Problems solved by technology

[0009] 1) The impact and ablation effect of the engine plume flow field on the ship deck is serious after the missile is ejected;

[0010] 2) If the missile fails to ignite, it is likely to explode, endangering the safety of ships and personnel

[0016] 1) The launching device has a complex structure and a large mass, making modular installation impossible;

[0017] 2) The missile is overloaded;

[0020] 5) The refilling process is complex and time-consuming

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