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Gas injection and electro-injection integrated hybrid drive device

A gas jet and hybrid drive technology, which is applied to the propulsion system devices of aerospace vehicles, motor vehicles, transportation and packaging, etc., can solve the problems of inability to meet the launch requirements of micro aircraft, poor propulsion precision, and low thruster specific impulse, etc. Achieve the effect of increasing the order of magnitude range, high precision and high injection efficiency

Active Publication Date: 2021-07-27
SOUTHEAST UNIV
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  • Description
  • Claims
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Problems solved by technology

[0003] Purpose of the invention: The purpose of the invention is to provide a hybrid driving device integrated with gas injection and electro-injection, which solves the problems of low specific impulse, poor injection efficiency, and poor propulsion precision of existing propellers, which cannot meet the launch requirements of micro-aircrafts.

Method used

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  • Gas injection and electro-injection integrated hybrid drive device
  • Gas injection and electro-injection integrated hybrid drive device
  • Gas injection and electro-injection integrated hybrid drive device

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Embodiment Construction

[0014] The present invention will be further described below in conjunction with the accompanying drawings.

[0015] Such as figure 1 , figure 2 As shown, the gas injection and electro-spray integrated hybrid driving device includes several thruster bodies arranged in an array. Using the Cartesian three-dimensional coordinate system as a reference, the thruster body 1 is arranged in arrays in three different directions. A water inlet 2 and an injection port 3 are provided, and an injection channel is provided between the water inlet 2 and the injection port 3 in the main body of the propeller, and a resistance metal heating sheet 4 and an injection electrode 5 are bonded in the injection channel, and the injection port 3 is set. A ground electrode 6 is bonded to the end of the thruster body 1 . Wherein, the position corresponding to the heater 4 in the injection channel is coated with an insulating layer to ensure that the current passes through the heater 4 to achieve the ...

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Abstract

The invention discloses an integrated hybrid driving device of gas jet and electric jet, which is characterized in that it comprises a plurality of propeller bodies arranged in an array, the propeller main body is provided with a water inlet and a jet port, and the propeller main body has a water inlet and a jet port inside. A jetting channel is arranged between the water port and the jetting port, a heating plate and a jetting electrode are arranged in the jetting channel, and a ground electrode is provided at the end of the main body of the propeller where the jetting port is provided. The invention has high specific impulse, high injection efficiency, long service time, low power consumption, and high propulsive force precision, and can achieve sufficiently high propulsion force while achieving sufficiently high precision.

Description

technical field [0001] The invention relates to an injector, in particular to an integrated hybrid drive device for gas injection and electric injection. Background technique [0002] Miniaturization is one of the important directions of the development of modern industrial technology. Micro-electro-mechanical systems also have considerable practicability, and are widely used in aerospace, energy, biology, chemical and other technical fields. With the development of modern aerospace technology, MEMS technology has been gradually integrated into the field of aerospace technology, and the miniaturization of spacecraft has become one of the mainstream directions of technological development. The development of satellite miniaturization is expected to reduce the number of launches to reduce mission costs and greatly increase the launch rate. Launch costs for a typical interstellar mission can be as high as 30% of the overall mission cost, and these costs could be significantly...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/40
CPCB64G1/405
Inventor 莫景文丁耀寰陈云飞沙菁倪中华曾嘉莹
Owner SOUTHEAST UNIV
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