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A kind of slurry for micro engine thrust chamber and its preparation method and application

A thrust chamber and engine technology, which is applied in the field of micro engine thrust chamber slurry and its preparation and application, can solve the problem that the performance and life of micro nozzles cannot meet the service requirements, the difficulty of coating slurry, coating thickness, Nozzle throat coating is easy to accumulate and other problems, to achieve the effect of low cost, high work efficiency, and meet the requirements of working conditions

Active Publication Date: 2018-02-06
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] Due to the small size of the micro nozzle, especially the diameter of the throat is below 1mm, when using the existing nozzle coating formula and preparation process to prepare the micro nozzle, the throat coating of the nozzle is easy to accumulate and cause blockage, or The coating is difficult to paste. The coating cannot reach the required thickness, and it is difficult to prepare the silicide coating on the inner and outer surfaces of the micro-nozzle, so that the performance and life of the micro-nozzle cannot meet the service requirements.

Method used

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  • A kind of slurry for micro engine thrust chamber and its preparation method and application
  • A kind of slurry for micro engine thrust chamber and its preparation method and application
  • A kind of slurry for micro engine thrust chamber and its preparation method and application

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Embodiment

[0035] A kind of preparation method of thrust chamber of 1N two-component attitude orbit control engine, described thrust chamber nozzle comprises straight section, convergent section, throat and exit section, such as figure 1 As shown; the straight line section is a hollow cylinder with a length of 4.2mm, an inner diameter of 3.2mm and an outer diameter of 4.4mm; the converging section is a hollow circular platform with a length of 2.8mm, the inner diameter of the small end is 0.9mm, and the outer diameter of the small end is 2.2mm , the inner diameter of the large end is 3.2mm, and the outer diameter of the large end is 4.4mm; the throat is a hollow cylinder with a length of 0.5mm, an inner diameter of 0.9mm, and an outer diameter of 2.2mm; the outlet section is a hollow circular table with a length of 0.5mm, and the small The inner diameter of the end is 0.9mm, the outer diameter of the small end is 2.2mm, the inner diameter of the big end is 1.04mm, and the outer diameter o...

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Abstract

The invention relates to a slurry for a thrust chamber of a micro-engine and its preparation method and application, and belongs to the technical field of bicomponent liquid rocket rail / attitude control engines. The thrust of the micro-engine is 0.1-5N, and the micro-engine The diameter of the throat of the thrust chamber is 0.3-1.0mm, and the material of the nozzle on the thrust chamber of the microengine is niobium-tungsten alloy. The slurry of the present invention has stable performance and uniform composition. By adjusting the concentration of the slurry, when the slurry is used to coat the micro nozzle with a throat diameter of 1 mm or less, the throat is not easy to be blocked, and at the same time The coating thickness can be ensured; the slurry of the present invention can be used to dip-coat the inner and outer surfaces of the micro-thrust chamber nozzle with a throat diameter of less than 1 mm, while ensuring the high-temperature oxidation resistance of the nozzle, it can also make the nozzle The throat diameter of the pipe meets the design requirements.

Description

technical field [0001] The invention relates to a slurry for a thrust chamber of a micro engine and its preparation method and application, and belongs to the technical field of bicomponent liquid rocket orbit / attitude control engines. The thrust of the micro engine is 0.1-5N, and the micro engine The diameter of the throat of the thrust chamber is 0.3-1.0mm, and the material of the nozzle on the thrust chamber of the micro engine is niobium-tungsten alloy. Background technique [0002] The micro propulsion system is mainly used for precise attitude adjustment and orbit positioning of micro space vehicles such as micro satellites. It has low cost, small size, low power consumption, light weight, small thrust (generally 0.1-5N), and high integration At the same time, this type of engine needs to have the ability to start multiple times, the number of pulses can reach tens of thousands, and the working life in orbit is long. It usually needs to run in orbit for several to ten ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B22F1/00C23C24/08B23P15/00
Inventor 李海庆张绪虎陈道勇徐方涛何开民贾中华
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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