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Solid vector thrust device with continuously adjustable thrust and stable pressure intensity

A vector thrust and thrust technology, applied in the field of solid vector thrust devices, can solve the problems of scattered distribution of components, reduction of launch vehicle reliability and space utilization efficiency, etc.

Pending Publication Date: 2022-08-02
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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  • Abstract
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Problems solved by technology

[0003] The embodiment of the present application provides a solid vector thrust device with continuously adjustable thrust and stable pressure to solve the problem of scattered distribution of components in the traditional liquid launch vehicle attitude control power system in the related art, which requires a large amount of space reserved for the overall system design of the launch vehicle Accommodates the attitude control system, which reduces the problems of launch vehicle reliability and space utilization efficiency

Method used

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  • Solid vector thrust device with continuously adjustable thrust and stable pressure intensity
  • Solid vector thrust device with continuously adjustable thrust and stable pressure intensity
  • Solid vector thrust device with continuously adjustable thrust and stable pressure intensity

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Embodiment Construction

[0032] In order to make the purposes, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments It is a part of the embodiments of this application, but not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work shall fall within the protection scope of the present application.

[0033] The embodiment of the present application provides a solid vector thrust device with continuously adjustable thrust and stable pressure, which can solve the problem that the components of the traditional liquid launch vehicle attitude control power system in the related art are distributed and scattered, and the overall syste...

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Abstract

The invention relates to a solid vector thrust device with continuously adjustable thrust and stable pressure intensity, which comprises an attitude control thrust mechanism, the attitude control thrust mechanism comprises two groups of burners and two gas pipelines for forming the two groups of burners into an annular structure, each of the two gas pipelines is provided with three groups of Laval nozzles, an inlet of each Laval nozzle is provided with a second arc surface, and an outlet of each Laval nozzle is provided with a second arc surface; the outlet directions of the Laval nozzles on the two fuel gas pipelines jointly form a structure in the shape of a 'Trunk'; the attitude control adjusting valve comprises a valve body connected with an inlet of the Laval nozzle, the valve body is provided with a gas inlet pipeline communicated with a gas pipeline, the inlet of the Laval nozzle is communicated with the gas inlet pipeline, a valve rod is arranged in the valve body, and a first arc surface is arranged at the end, close to the inlet of the Laval nozzle, of the valve rod. When the valve rod moves in the direction close to an inlet of the Laval nozzle, the gap between the first arc surface and the second arc surface is gradually reduced, linear adjustment of 0-100% of fuel gas thrust is achieved, and the pressure intensity of a system is kept stable.

Description

technical field [0001] The present application relates to the technical field of launch vehicle attitude control power systems, in particular to a solid vector thrust device with continuously adjustable thrust and stable pressure. Background technique [0002] The attitude control power system of the launch vehicle plays an important role in the flight process of the launch vehicle, including controlling the launch vehicle to complete the pitch, yaw, roll, track maintenance, and speed correction. The components of the attitude control power system of traditional liquid launch vehicles are scattered, the transmission pipelines are interspersed with complex, the risk of airtight leakage is high, and there are many assembly and testing procedures, and a large amount of space needs to be reserved for the overall system design of the launch vehicle to accommodate the attitude control system, which reduces the carrying capacity. The reliability and space utilization efficiency of ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/08F02K9/34F02K9/30F02K9/97F02K9/86
CPCF02K9/08F02K9/34F02K9/30F02K9/97F02K9/86
Inventor 赵启扬丁杰王刚周杨梓胡胜云周子翔余明敏王善金钟志文刘丹吴继华周律张培喜张周周王少恒
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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