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Tandem electric field force aircraft propelling device

A technology of propulsion device and electric field force, which is applied in the field of tandem electric field force aircraft propulsion device, which can solve the problems of small thrust and aircraft detaching from the earth's surface, and achieve the effect of large thrust, low noise, and large ion wind flux

Pending Publication Date: 2015-12-02
CHINA JILIANG UNIV +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] However, the thrust generated by the current electric propulsion system is too small to keep the aircraft off the surface of the earth, and can only be applied to small adjustments in the attitude and position of satellites in space

Method used

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  • Tandem electric field force aircraft propelling device
  • Tandem electric field force aircraft propelling device
  • Tandem electric field force aircraft propelling device

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Embodiment Construction

[0026] Below in conjunction with accompanying drawing, the present invention will be further described, see figure 1 with figure 2 , a tandem electric field force aircraft propulsion device, which includes an ion generator array layer frame 1, a negative ion generator 2, and a positive ion generator 7. Both the negative ion generator 2 and the positive ion generator 7 are fixed on the ion generator array layer frame 1 . Inside the shell 3, negative ion generator 2, positive screen grid 4, positive neutralization layer 5, positive acceleration grid 6, positive ion generator 7, negative screen grid 8, negative neutralization layer are fixed sequentially from back to front 9. Negative accelerating grid 10, negative ion generator 2. The front end of the casing 3 is respectively fixed with the positive screen grid 4 , the neutralization layer 5 and the positive acceleration grid 6 by insulating fixing bolts 11 .

[0027] In particular, the surfaces of the positive screen grid ...

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Abstract

The invention provides a tandem electric field force aircraft propelling device which can be applied to various occasions inside and outside the atmosphere. The propelling device comprises positive and negative ion generator array layer frames, positive and negative ion generators, shells, positive and negative screen grids, positive and negative neutral layers, positive and negative accelerating grids and insulating fixing bolts. Air is ionized continuously through alternating current and the positive and negative ion generators to generate a large number of positive and negative ions, and the ions are immediately captured by oxygen molecules, nitrogen molecules, carbon dioxide molecules and the like in the air, so that weak positive ion wind and negative ion wind are generated. After multi-stage ionization and multi-stage acceleration, ion wind with a high speed and large flux is output from an accelerator; accordingly, the propelling device can provide large thrust force, and has the advantages of being stable in operation, free of noise, large in specific impulse and thrust force, wide in application occasion and the like.

Description

Technical field: [0001] The invention relates to a tandem electric field force aircraft propulsion device technology, in particular to a high-voltage ionized air to generate positive and negative ions, and adopts electric field force to spray a large number of high-speed particles after multi-stage acceleration to generate high thrust. Background technique: [0002] The electric propulsion system uses electrical energy to ionize the propellant, resulting in a jet velocity much higher than chemical propulsion, which can effectively reduce the demand for propellant. Compared with the traditional chemical propulsion system, the electric propulsion system has the characteristics of high specific impulse, small thrust, and high propellant utilization rate. is the internal energy of the propellant itself. Therefore, chemical propulsion will be limited by the internal energy per unit mass of propellant, thereby restricting the final exhaust velocity, while the electric propulsion ...

Claims

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Application Information

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IPC IPC(8): F03H1/00
Inventor 严天宏吴斌陈夏琨陈晓春
Owner CHINA JILIANG UNIV
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