Helicon plasma induction thruster

A plasma and helicon wave technology, applied in the field of space exploration, can solve the problems of incompatibility of on-board power supply, high IPPT electric power, limited working life, etc., to achieve miniaturization, long service life, system size and weight reduction Effect

Active Publication Date: 2016-10-12
NAT UNIV OF DEFENSE TECH
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  • Abstract
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Problems solved by technology

[0005] The present invention provides a helical wave plasma induction thruster to solve the limitation of the working life of the existing ion thruster due to electrode corrosion and the high elect

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  • Helicon plasma induction thruster
  • Helicon plasma induction thruster
  • Helicon plasma induction thruster

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Embodiment Construction

[0048] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0049] refer to figure 1 , the preferred embodiment of the present invention provides a helicon wave plasma induction thruster, including a discharge chamber 1 for forming a helicon wave plasma in its inner cavity, and the outside of the discharge chamber 1 is sequentially arranged for the discharge chamber 1 The first magnet 2 forming the axial magnetic field inside, the second magnet 3 used to form the radial magnetic field in the discharge chamber 1; The helicon wave discharge antenna 4 for generating helicon wave plasma with medium ionization, and the inductive accelerator coil 5 for accelerating the helicon wave plasma in a radial magnetic field; the helicon wave plasma inductive thruster...

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Abstract

The invention discloses a helicon plasma induction thruster. The helicon plasma induction thruster comprises a discharge cavity, and first magnets and second magnets are sequentially arranged on the outer portion of the discharge cavity; a helicon discharge antenna and an induction acceleration coil are sequentially arranged on the outer wall of the discharge cavity in the axial direction; and the thruster further comprises a helicon discharge circuit, a pulse induction discharge circuit and a time sequence control circuit, wherein the helicon discharge circuit provides a work power source for the helicon discharge antenna. The pulse induction discharge circuit is connected with the induction acceleration coil and provides a pulse discharge voltage for the induction acceleration coil so as to drive helicon plasmas to be pushed out in an accelerated manner, and the time sequence control circuit is connected with the helicon discharge circuit and the pulse induction discharge circuit. The helicon plasma induction thruster has the beneficial effects of being free of electrode corrosion, large in ionization density and long in service life. Through efficient decoupling of the ionization level and the acceleration level, efficient separation of the ionization level and the acceleration level is achieved, voltage needed by a capacitor of the acceleration level is reduced, the system size and the system weight are greatly reduced, and miniaturization, lightweight and the solid state of the thruster are facilitated.

Description

technical field [0001] The invention relates to the field of space detection, in particular to a helicon wave plasma induction thruster for space detection. Background technique [0002] Electric propulsion has broad application prospects in space exploration. Compared with traditional chemical propulsion, it has the characteristics of high specific impulse, long life, and precise thrust control. Electric thrusters can be divided into electrothermal thrusters, electrostatic thrusters, and electromagnetic thrusters according to different thrust formation methods. Due to the limitation of Langmuir charge effect, it has a higher energy density, and has become a very promising new propulsion method. [0003] The ion thruster is a relatively mature electrostatic thruster. It uses the hollow cathode to emit thermal electrons to ionize the working medium gas, and then accelerates the ion ejection through the grid electric field to form a thrust. Electrode corrosion is inevitable ...

Claims

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Application Information

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IPC IPC(8): F03H1/00
CPCF03H1/00F03H1/0081
Inventor 杨雄程谋森王墨戈
Owner NAT UNIV OF DEFENSE TECH
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