A dual-component attitude control thruster injector with a micro-channel liquid collection chamber

An injector and two-component technology, applied in the direction of machines/engines, jet propulsion devices, rocket engine devices, etc., can solve problems such as incomplete isolation of oxygen and fuel channels, interference of propellant atomization quality, explosion, etc., to achieve Excellent mechanical properties, light weight and small volume design, and the effect of improving pulse performance

Active Publication Date: 2021-06-11
BEIJING INST OF CONTROL ENG
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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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  • A dual-component attitude control thruster injector with a micro-channel liquid collection chamber
  • A dual-component attitude control thruster injector with a micro-channel liquid collection chamber
  • A dual-component attitude control thruster injector with a micro-channel liquid collection chamber

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Embodiment Construction

[0037] An exemplary embodiment of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although the exemplary embodiments of the present disclosure are shown in the drawings, it is understood that the present disclosure can be implemented in various forms and should not be restricted herein. Instead, it is provided to provide more thoroughly understood the present disclosure, and can communicate the scope of the disclosure to those skilled in the art. It should be noted that the features in the present invention in the present invention can be combined with each other in the case of an unable conflict. The present invention will be described in detail below with reference to the drawings.

[0038] figure 1 It is a schematic structural diagram of a two-component post-liquid lifting thruster that has a tiny flowway set liquid chamber according to an embodiment of the present invention. Such as figure 1As shown, the two-component...

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Abstract

The invention discloses a dual-component attitude control thruster injector with a micro flow channel liquid collection chamber, comprising: an oxygen circuit joint, a combustion line joint, an injector structure and a thrust chamber docking interface; wherein, The oxygen circuit nozzle, the fuel circuit nozzle and the thrust chamber docking interface are integrally connected with the injector structure; the oxygen circuit nozzle is located on the side of the upstream end face of the injector structure; The other side of the upstream end face of the injector body; the butt joint of the thrust chamber is located on the downstream end face of the injector structure; One end of the flow path of the injector is connected with the nozzle of the oxygen path, and the other end of the flow path of the oxygen path of the injector is connected with the interface of the thrust chamber; The other end of the flow path of the burner is connected with the butt joint of the thrust chamber. The present invention produces high-quality atomization that enables efficient mixing and combustion of oxidant and combustion agent within the thrust chamber.

Description

Technical field [0001] The present invention belongs to the attitude control, position retention, momentum wheel unloading technology of space aircraft, and more particularly to a two-component post-controlled thrust inductor having a tiny flowway concentration liquid chamber. Background technique [0002] The two-component post-controlled thrusters achieve the spray of oxygen and burning two-way propellant by the injection. After the pressure reduction can make the propellant after the spray of high speed, the extension of the external force is quickly realized. The atomization of the droplets, evaporated, so that the two propellants are quickly carried out to gas phase spontaneous combustion reactions. [0003] For post-controlled thrusters, it is desirable to have the characteristics of light and fast response, so that the injection is small as small as possible, the structure is simple, and the channel is small. The existing concilier thrustor consists of inner flow paths in ...

Claims

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Application Information

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Patent Type & Authority Patents(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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