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Electrothermal micro-thruster

A micro-thruster and electric heating technology, applied in the field of nano-satellite micro-propulsion system, to achieve high efficiency, strong adaptability, and good propulsion performance

Active Publication Date: 2018-05-01
NANJING UNIV OF SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In addition, due to the limitation of volume power consumption, conventional large heaters are no longer applicable

Method used

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  • Electrothermal micro-thruster
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Examples

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Embodiment Construction

[0021] The present invention is a nickel micro-heating device, comprising:

[0022] A Pyrex glass substrate 2; and a silicon chip 4 anodically bonded on the Pyrex glass substrate 2;

[0023] A runner groove 3 is provided on the symmetry axis of the silicon chip, and the runner groove 3 is provided with a Laval spout 5 and a fluid inlet 8;

[0024] The device also includes: on the silicon chip 4, a resistor buried groove 6 is symmetrically arranged around the flow channel groove 3 and the fluid inlet 8; an insulating layer and a nickel resistor 7 are sequentially arranged in the resistor buried groove 6 from the inside to the outside;

[0025] The Pyrex glass substrate is provided with a pad 1 connected to the nickel resistor 7, and has an intersection with the nickel thin film resistor to form an effective contact;

[0026] The bonded surface of the Pyrex glass substrate 2 and the silicon chip 4 is: the grooved surface of the resistance buried groove 6 on the silicon chip 4, ...

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Abstract

The invention discloses an electrothermal micro-thruster based on a nickel film resistor. The electrothermal micro-thruster comprises a Pyrex glass substrate, the nickel film resistor, a welding discand a silicon wafer. Joule heat produced by the nickel resistor is used to heat the silicon wafer, then a propellant fluid in a runner is heated, and then a high-temperature fluid generates a thrust through a nozzle; for a gas propellant, the electrothermal micro-thruster can effectively heat the gas in the runner so as to improve specific impulse of the electrothermal micro-thruster, and the total thrust of a propulsion system is improved accordingly; for propellants in liquid form such as water and butane, the liquids can be vaporized, and steam generates thrust through a Laval nozzle; and the electro-electric micro-thruster is applied to a micro-propulsion system of a micro-nano satellite, adjusting on single freedom degree of the micro-nano satellite can be completed, and attitude control and orbital elevation of the micro-nano satellite can also be achieved.

Description

technical field [0001] The invention relates to an electrothermal micro-thrust device based on a nickel film resistance, which is applied to a nano-satellite micro-propulsion system. Background technique [0002] Microsatellites are light in weight and small in size, so they also encounter many new challenges in the design of their subsystems, especially their propulsion system. The micro-propulsion system is the core component of the micro-nano-satellite, which is used to realize the attitude control, orbit transfer and maintenance of the micro-nano-satellite (attitude-orbit control for short). The development of micro-nano satellites urgently needs to be equipped with a micro-propulsion system that can provide high precision, small impulse, and simple structure. From the requirements of the micro-propulsion system, its thrust level should be 0.5-10mN, and the provided △V should not be less than 15m / s. [0003] Among the current micro propulsion systems, the cold gas prop...

Claims

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Application Information

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IPC IPC(8): F03H1/00
CPCF03H1/0093
Inventor 朱朋王峰陈楷侯刚穆云飞王悦听汪柯沈瑞琪叶迎华
Owner NANJING UNIV OF SCI & TECH
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