Arcjet thruster capable of improving operation stability

An arc heating and engine technology, applied in the aviation field, can solve the problems of engine electrode ablation, low efficiency and poor reliability, and achieve the effects of avoiding excessive temperature, improving operation stability and reducing ablation

Inactive Publication Date: 2015-03-25
INST OF MECHANICS - CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In the running experiments of arc heating engines in my country, problems such as serious ablation of engine electrodes, poor sealing under hot conditions, unstable engine performance, poor reliability, short continuous and stable working time,

Method used

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  • Arcjet thruster capable of improving operation stability
  • Arcjet thruster capable of improving operation stability

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[0014] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the present invention, but not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0015] The main idea of ​​the present invention is to install a water-cooling jacket on the outer wall of the anode nozzle of the electric arc heating engine, and the distance between the outer wall of the anode nozzle and the water-cooling jacket is determined according to the expansion coefficient of the material of the anode nozzle and the pre-controlled temperature of the anode nozzle. To ensure that during the operation of the arc heating engine, wh...

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Abstract

The invention provides an arcjet thruster capable of improving operation stability. The arcjet thruster comprises a cathode, a sealing piece, an insulating piece, a metal sleeve and an anode spraying pipe which are sequentially connected. The cathode, the sealing piece and the insulating piece are fixedly connected in sleeving mode in sequence. One end of the metal sleeve is connected with the insulating piece in a sleeving mode. The other end of the metal sleeve is clamped to the anode spraying pipe. The arcjet thruster further comprises a water cooling sleeve adaptive to the anode spraying pipe. The water cooling sleeve is additionally arranged on the outer wall face of the anode spraying pipe. A through way allowing cooling water to pass through is arranged in the water cooling sleeve. According to the arcjet thruster, the water cooling sleeve is additionally arranged near the outer wall face of the anode spraying pipe of the arcjet thruster, it is avoided that the temperature of the anode spraying pipe is excessively high, ablation of the inner wall face of the anode spraying pipe is lowered accordingly, and the operation stability of the arcjet thruster is improved.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to an arc heating engine which can improve the running stability of the engine. Background technique [0002] With the increasing space activities aimed at the detection and utilization of space resources, and the development of commercial communications, scientific exploration, and national defense missions, higher requirements have been placed on the propulsion system used for satellite attitude and orbit adjustment. Traditional chemical propulsion is limited by the combustion temperature of the propellant, the specific impulse is already close to the limit, and the control accuracy for satellite positioning is low. The electric propulsion system can generate a much higher specific impulse than chemical propulsion, so on the premise of completing the same space mission, it can reduce the weight of propellant that the satellite needs to carry, increase the payload of the satellit...

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Application Information

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IPC IPC(8): F03H99/00F01P3/00
CPCF03H1/0031F03H1/0093
Inventor 潘文霞吴承康孟显
Owner INST OF MECHANICS - CHINESE ACAD OF SCI
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