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Low-ablation throat liner for solid rocket engine

A technology of solid rockets and engines, which is applied to rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of reduced nozzle structure quality, low reliability, and high ablation rate of solid rocket engine throat liners, and achieves a reduction in injection The quality of tube structure, reducing ablation, and satisfying the effect of low ablation rate

Pending Publication Date: 2021-08-10
内蒙动力机械研究所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The invention provides a low-ablation throat liner of a solid rocket motor, which solves the technical problems of high ablation rate and low reliability of the throat liner of the solid rocket motor and reduces the structural quality of the nozzle

Method used

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  • Low-ablation throat liner for solid rocket engine
  • Low-ablation throat liner for solid rocket engine

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Embodiment 1

[0021] Such as figure 1 As shown, the present invention provides a solid rocket motor low ablation throat lining, please refer to the attached figure 1 , the solid rocket motor low-ablation throat liner, comprising: a throat liner main body and a plurality of metal cooling rings. A plurality of grooves are arranged on the inner surface throat of the main body of the throat liner or the easily ablated part of the expansion section and its upstream; the plurality of metal cooling rings are embedded in the plurality of grooves on the main body of the throat liner, and are made The main body of the throat liner and the heat dissipation ring form an integral composite structure; wherein, the plurality of metal heat dissipation rings undergo a phase change in a high-temperature ablation environment to absorb heat, protect the main body of the throat liner, and reduce the ablation rate of the throat liner.

[0022] Specifically, the geometric configuration of the main body of the th...

Embodiment 2

[0029] Such as figure 2 As shown, on the basis of the principle of Embodiment 1, in order to further simplify the structure and assembly method, the main body of the throat liner is provided with a plurality of grooves along the axial direction on the straight section such as the throat and upstream. The geometric configuration of the cooling ring is a thin-walled cylinder, which is assembled and embedded in the main body of the throat liner along the axial direction. Through bonding, the main body of the throat liner and the heat dissipation ring form an integral composite structure, and the inner profile of the nozzle is kept continuous, and the material of the main body of the throat liner and the material of the heat dissipation ring are arranged at intervals.

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Abstract

The invention relates to a low-ablation throat liner for a solid rocket engine. The low-ablation throat liner comprises a throat liner main body and multiple metal heat dissipation rings. Multiple grooves are formed in a throat portion of an inner profile or an easy-ablation portion of an expansion section of the throat liner main body and the upstream of the throat liner main body. The multiple metal heat dissipation rings are embedded into the multiple grooves in the throat liner main body, and by means of bonding, the throat liner main body and a heat dissipation ring form an overall composite structure. The multiple metal heat dissipation rings are subjected to phase change in a high-temperature ablation environment to absorb heat, the throat liner main body is protected, and the ablation rate of the throat liner is reduced. According to the low-ablation throat liner, the technical problems of high ablation rate and low reliability of a throat liner for the solid rocket engine are solved, the structural mass of a spraying pipe is reduced, a throat liner main body material is protected, thus ablation to the throat liner portion of the spraying pipe of the engine is reduced greatly, meanwhile, the structural mass of the spraying pipe is reduced, and the technical needs of the high-performance solid rocket engine for low ablation rate and high reliability of the throat liner of the spraying pipe are met.

Description

technical field [0001] The invention relates to the field of solid rocket motor nozzles, in particular to a low-ablation throat liner for solid rocket motors. Background technique [0002] The nozzle throat liner is a key component of the solid rocket motor. Its working environment is extremely harsh, and it faces the extreme thermal load environment of high temperature, high pressure and high-speed airflow. Its anti-ablation performance directly affects the performance of the engine. Since the nozzle of the solid rocket motor adopts a passive thermal protection method, there is a certain ablation of the throat lining of the nozzle during the operation of the engine, resulting in the performance loss of the solid rocket motor. Especially as the working pressure of solid rocket motors continues to increase, the requirements for the mechanical properties and ablation resistance of throat lining materials are getting higher and higher. At present, the low-ablative throat linin...

Claims

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Application Information

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IPC IPC(8): F02K9/97F02K9/08
CPCF02K9/08F02K9/972F02K9/974
Inventor 徐朝启陈志安张瑞庭李薇王立民宋明纲
Owner 内蒙动力机械研究所