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Multi-directional thrust integrated micro thruster and its control method

A control method and thruster technology, applied in the direction of aerospace vehicle propulsion system devices, etc., can solve the problems of low versatility and interchangeability, long production cycle, high product cost, etc., achieve convenient installation, reduce development costs, and compact structure Effect

Active Publication Date: 2019-11-01
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The system configuration of this method is relatively flexible, but the disadvantage is that the versatility and interchangeability are low. When the system requirements change, new thruster products need to be re-developed, the production cycle is long, and the product cost is high.

Method used

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  • Multi-directional thrust integrated micro thruster and its control method
  • Multi-directional thrust integrated micro thruster and its control method

Examples

Experimental program
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Effect test

Embodiment 1

[0026] Such as figure 1 As shown, Embodiment 1 of a multi-directional thrust integrated micro-thruster is disclosed. The thruster includes: a first housing 110 , a miniature solenoid valve 120 , a connecting fastening device 130 , a second housing 140 and a nozzle 150 .

[0027] The first housing 130 is provided with a first air passage, and the first air passage is provided with an air inlet and several air outlets. The gas path at the air inlet of the first gas path is connected to the thrust source, and is used to receive the working fluid output by the thrust source. In this embodiment, the first gas path is provided with four gas outlets, and the working fluid input into the first gas path through one gas inlet is divided into four paths for output.

[0028] The gas path at the inlet end of the miniature solenoid valve 120 is connected to the gas outlet of the first gas path. In this embodiment, four miniature electromagnetic valves 120 are arranged, and the air inlet e...

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Abstract

The invention discloses a multi-directional thrust integrated type micro-thruster. The micro-thruster comprises a first shell body, micro-electromagnetic valves, a second shell body and nozzles, wherein the first shell body is internally provided with a first gas path, a gas path of the gas inlet end of each micro-electromagnetic valve is connected with a gas outlet of the first gas path; a second gas path is arranged in the second shell body, and a gas inlet of the second gas path is connected with the gas outlet end of each micro-electromagnetic valve; and a gas path of the gas inlet end of each nozzle is connected with a gas outlet of the second gas path. According to the multi-directional thrust integrated type micro-thruster, by adopting the micro-electromagnetic valves, the nozzles with different output directions are controlled correspondingly, various system thrust requirements can be met, universality and interchangeability of the micro-thruster are improved greatly, and the micro-thruster is compact in structure and convenient to install.

Description

technical field [0001] The invention relates to the technical field of space micro-propulsion, in particular to a multi-directional thrust integrated micro-thruster and a control method thereof. Background technique [0002] Standardized and modular design and manufacturing technology enable micro-nano-satellites to be mass-produced and stored on the assembly line for easy mobile launch, which is the current development trend of micro-satellite technology and micro-propulsion technology. At present, the relatively mature propulsion technology is the cold gas propulsion system, which stores the propellant in a liquid state in the storage tank. When the system is working, the liquid propellant is vaporized and injected from the thruster to generate thrust. Domestic cold air propulsion systems are mostly composed of separate components. Each component is assembled and connected in the system separately according to needs. Each thruster is equipped with a nozzle, which only gene...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/40
CPCB64G1/40
Inventor 王晓露鲜亚平金理郭加利王玥
Owner SHANGHAI AEROSPACE CONTROL TECH INST