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Dual-component attitude-controlled thruster injector with micro-flow-channel liquid collecting cavity

An injector, two-component technology, applied in the directions of jet propulsion, machine/engine, rocket engine, etc., can solve the problems of incomplete isolation of oxygen and combustion channels, interference of propellant atomization quality, explosion, etc. Excellent mechanical properties, lightweight and small volume design, and the effect of improving pulse performance

Active Publication Date: 2020-07-31
BEIJING INST OF CONTROL ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, this structure also has some disadvantages
First of all, once there is a problem with the quality of diffusion welding, the oxygen and combustion channels are not completely isolated, which will lead to catastrophic consequences of explosion
In addition, the deformation of the flow channel during the diffusion welding process, or the misalignment between the laminates, will also bring serious interference and hidden dangers to the atomization quality of the propellant

Method used

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  • Dual-component attitude-controlled thruster injector with micro-flow-channel liquid collecting cavity
  • Dual-component attitude-controlled thruster injector with micro-flow-channel liquid collecting cavity
  • Dual-component attitude-controlled thruster injector with micro-flow-channel liquid collecting cavity

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Embodiment Construction

[0037] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided for more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that, in the case of no conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0038] figure 1 It is a schematic structural diagram of a dual-component attitude control thruster injector provided by an embodiment of the present inventio...

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Abstract

The invention discloses a dual-component attitude-controlled thruster injector with a micro-flow-channel liquid collecting cavity. The dual-component attitude-control thruster injector comprises an oxygen path connecting nozzle, a combustion path connecting nozzle, an injector structure body and a thrust chamber butt joint interface; the oxygen path connecting nozzle, the combustion path connecting nozzle and the thrust chamber butt joint interface are integrally connected with the injector structure body; the oxygen path connecting nozzle is located on one side of the upstream end face of theinjector structure; the combustion path connecting nozzle is located on the other side of the upstream end face of the injector structure; the thrust chamber butt joint interface is located on the downstream end face of the injector structure; one end of an injector oxygen path flow channel communicates with the oxygen path connecting nozzle, and the other end of the injector oxygen path flow channel communicates with the thrust chamber butt joint interface. The dual-component attitude-controlled thruster injector produces high quality atomization, and enables an oxidant and a combustion agent to be efficiently blended and combusted in a thrust chamber.

Description

technical field [0001] The invention belongs to the technical field of attitude control, position maintenance, and momentum wheel unloading of aerospace vehicles, and in particular relates to a dual-component attitude control thruster injector with a micro flow channel liquid collection chamber. Background technique [0002] The two-component attitude control thruster realizes the injection of oxygen and combustion propellant through the injector, and the propellant can be quickly realized under the disturbance of internal and external forces after the propellant is ejected at high speed through the pressure drop potential energy. The atomization and evaporation of the liquid droplets make the two propellants undergo a rapid gas-phase spontaneous combustion reaction. [0003] For the attitude control thruster, it is hoped to have the characteristics of light weight and fast response, so it is hoped that the size of the injector should be as small as possible, the structure i...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/52
CPCF02K9/52
Inventor 张榛蔡坤陈君汪凤山毛晓芳胡羽王文平王国华尹兆刚郑然董志强刘鹏飞李新光冉鹏
Owner BEIJING INST OF CONTROL ENG
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