Variable-expansion-ratio spray pipe of single-chamber double-thrust solid rocket engine

A solid rocket, dual-thrust technology, applied in rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of complicated nozzle design process, affecting missile range, increasing missile bottom resistance, etc., to achieve rapid reduction in structural strength, The effect of low density and increased thrust

Active Publication Date: 2022-03-29
北京中科宇航技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the design process of this type of nozzle is complicated, and the rear section of the nozzle with a large expansion ratio section is completely inert structure

Method used

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  • Variable-expansion-ratio spray pipe of single-chamber double-thrust solid rocket engine
  • Variable-expansion-ratio spray pipe of single-chamber double-thrust solid rocket engine
  • Variable-expansion-ratio spray pipe of single-chamber double-thrust solid rocket engine

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Embodiment Construction

[0034] The technical solutions in the embodiments of the present application are clearly and completely described below in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of them. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without making creative efforts belong to the scope of protection of this application.

[0035] like figure 1 As shown, the application provides a single-chamber double-thrust solid rocket motor variable expansion ratio nozzle, including a nozzle body 1, the nozzle body 1 has a nozzle outlet, and the nozzle body 1 is close to the nozzle outlet. The nozzle expansion section is fixedly connected at the position, and the nozzle expansion section includes the front section 2 of the nozzle expansion section and the rear section 3 of the nozzle expansion section. The rear sec...

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Abstract

The invention provides a variable-expansion-ratio spray pipe of a single-chamber double-thrust solid rocket engine. The variable-expansion-ratio spray pipe comprises an engine rear end socket, a rear end socket inner heat insulation layer, a long tail pipe, a long tail pipe inner heat insulation layer, a spray pipe shell, a throat liner assembly and a spray pipe expansion section. The nozzle expansion section is of a segmented structure with a front section and a rear section, and the rear section is made of a metal material which is easy to ablate. When the high pressure intensity of the single-chamber double-thrust engine is converted into the low pressure intensity, the expansion ratio of the spray pipe is automatically converted to adapt to the change of the pressure intensity of an outlet of the spray pipe, and the expansion ratio requirement for complete expansion of the single-chamber double-thrust solid rocket engine under different thrust sections is met.

Description

technical field [0001] The present application relates to the technical field of solid rockets, in particular to a variable expansion ratio nozzle of a single-chamber double-thrust solid rocket motor. Background technique [0002] The flight trajectory of a solid rocket motor for a tactical missile generally consists of flight stages such as a speed-up stage and a cruise stage. In order to meet the power requirements of each flight segment, two engines are often used in parallel or in series. This power system has been widely used in advanced missiles equipped at home and abroad. Single-chamber dual-thrust solid rocket motors have been used as a new type of advanced tactical missile power propulsion system. Compared with single-stage single-thrust or multi-stage tandem engine thrust systems, single-chamber dual-thrust solid rocket motors have the advantages of compact structure, light weight and high propulsion efficiency. [0003] The single-chamber dual-thrust solid roc...

Claims

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Application Information

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IPC IPC(8): F02K9/97F02K9/08
CPCF02K9/97F02K9/08
Inventor 张翔郑才浪赖谋荣
Owner 北京中科宇航技术有限公司
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