A kind of rubber plugging cover of missile launching tail nozzle

A tail nozzle and rubber plugging technology, which is applied in the direction of machines/engines, rocket engine devices, jet propulsion devices, etc., can solve problems such as low reliability, difficult process control, complex structure, etc., to ensure the safety of ground equipment and simplify the design Structure, the effect of ensuring the safety of equipment

Active Publication Date: 2017-04-19
SHANGHAI XINLI POWER EQUIP RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The main problems of the double rubber plugging structure are: the structure is relatively complex, the process control is difficult, and the reliability is relatively low
The main problems with the structure of the aluminum plug cover are: the aluminum plug cover cannot be completely melted at the beginning of the engine operation, and the ejection is relatively large, which may cause damage to the equipment on the gas rudder and other bombs.

Method used

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  • A kind of rubber plugging cover of missile launching tail nozzle

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Embodiment Construction

[0013] The invention will be described in more detail hereinafter with reference to the accompanying drawings showing embodiments of the invention. However, this invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0014] Such as figure 1 Shown is the structural representation of the rubber plugging cover of the missile launching tail nozzle of the present invention.

[0015] The throat liner 1 is made of felt carbon / carbon composite material, and the throat liner 1 and the front and rear rubber layer assemblies are bonded at the expansion section of the throat liner 1 with 730 glue, and the thickness of the glue layer is not greater than 0.1; the assembly is made of The front rubber layer 2 and the rear rubber layer 3 are bonded an...

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Abstract

The invention discloses a rubber blanking cap of a guided missile engine exhaust nozzle, which comprises a throat liner, a front rubber layer, a rear rubber layer and blanking cap clamp cloth. The throat liner is made of a felt-carbon / carbon composite; the throat liner, and an assembly of the front rubber layer and the rear rubber layer are bonded at an expansion section of the throat liner; the assembly is formed by bonding and solidifying the front rubber layer and the rear rubber layer in a mold; the blanking cap clamp cloth is sandwiched in the middle for reinforcement; the front rubber layer and the rear rubber layer are made of a butyronitrile rubber material; and the blanking cap clamp cloth is butyronitrile oil-proof rubberized fabric. With the adoption of the structure of the rubber blanking cap of the exhaust nozzle, compared with the prior art, the rubber blanking cap has the advantages and benefits that the rubber blanking cap can bear internal and external pressure; the original double rubber blanking cap design structure is simplified; the technological operation is convenient; ejection substance of an engine during operation is decreased; and the safety of missile equipment such as a gas vane is guaranteed.

Description

technical field [0001] The invention relates to a shell structure of a solid rocket motor, in particular to a rubber plugging cover for a missile launch tail nozzle. Background technique [0002] The tail nozzle is one of the important parts in the engine structure. As the energy conversion device of the engine, it converts the thermal energy of the high-temperature gas into the kinetic energy of the gas, thereby generating thrust. At the same time, it is also a gas flow control device, which can establish a certain working pressure in the combustion chamber. In the design of the engine tail nozzle, in order to make the engine have better performance, on the premise of meeting the overall requirements, at the same time, considering the requirements of ignition pressure buildup, combustion chamber sealing and bearing the internal and external pressure of the launch box, it is necessary to focus on solving the blocking cover Adaptability of structural design. [0003] Existi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/97
Inventor 孙福合贾春宁刘乡芸乐浩
Owner SHANGHAI XINLI POWER EQUIP RES INST
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