Design method of secondary-flow pintle engine

A design method and secondary flow technology, applied in design optimization/simulation, special data processing applications, geometric CAD, etc., can solve problems such as lack of design methods and processes, and achieve the effects of prolonging life and reducing ablation

Pending Publication Date: 2021-10-15
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] At present, although the concept and corresponding structure have been proposed for the secondary flow throat plug engine, there is a lack of specific design methods and processes. The present invention proposes a design method for the secondary flow throat plug engine

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  • Design method of secondary-flow pintle engine
  • Design method of secondary-flow pintle engine
  • Design method of secondary-flow pintle engine

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Embodiment Construction

[0041] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0042] In order to make the above objects, features and advantages of the present invention more comprehensible, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0043] In order to facilitate the realization of experimental research, that is, to verify the reliability of the secondary flow throat plug engine, such as dynamic seal, throat plug rod drive device and its contro...

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Abstract

The invention discloses a design method for a secondary-flow pintle engine. The design method comprises the following steps: carrying out engine propellant charging design according to the overall index requirement of the secondary-flow pintle engine; designing the movement range of a pintle; designing the basic profile of the secondary-flow pintle engine; selecting a pintle engine structure and a shell material; performing thermal protection design on a combustion chamber, a spray pipe and the pintle; designing a pintle servo mechanism and a track, and conducting sealing design on the pintle engine; selecting secondary-flow nozzle structure parameters and secondary-flow spouting parameters; designing a secondary-flow air source in the pintle; and estimating the thrust adjusting performance of the secondary-flow pintle engine and the structural quality of the pintle engine and the pintle servo mechanism. While the thrust of the engine is adjusted, a secondary-flow coating layer formed by secondary flow and main flow on the surface of the pintle can reduce the ablation of the pintle, the service life of the pintle is prolonged, and the ablation effect of the main flow on the pintle is relieved by changing the components and the state of a secondary-flow working medium.

Description

technical field [0001] The invention relates to the field of solid rocket motors, in particular to a design method of a secondary throat plug rocket motor. Background technique [0002] Adjusting the thrust by changing the throat area of ​​the engine nozzle is a research branch in the technical field of thrust adjustment of solid rocket motors. Under the condition that the engine nozzle profile is fixed, the throat area is mainly changed by mechanical means or fluid means. [0003] The throat plug engine is driven by the transmission system, so that the throat plug embedded in the combustion chamber moves back and forth along the centerline of the engine, and the geometric area of ​​the throat of the nozzle can be adjusted mechanically without changing the appearance of the engine. , thereby changing the magnitude of the thrust. By controlling the thrust of the solid rocket motor through the throat plug scheme, an ideal result with a thrust adjustment range of approximatel...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/20
CPCG06F30/15G06F30/20Y02T90/00
Inventor 李想谢侃杨正闫东峰李鸿瑾苗龙王宁飞
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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