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Pulse plasma thruster with ceramic nozzles on the side wall

A technology of pulsed plasma and ceramic nozzles, applied in the direction of utilizing plasma, reverse thrust devices, mechanical equipment, etc., can solve the problems of reducing discharge current, reducing electromagnetic acceleration performance and thrust, increasing the discharge resistance of the main circuit, etc.

Inactive Publication Date: 2011-12-28
SHANGHAI JIAO TONG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

The disadvantage of this patent is that the insulating ceramic nozzle is set on the metal electrode, which will increase the discharge resistance of the main circuit and reduce the discharge current under the same discharge energy, thereby reducing the electromagnetic acceleration performance and thrust

Method used

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  • Pulse plasma thruster with ceramic nozzles on the side wall
  • Pulse plasma thruster with ceramic nozzles on the side wall
  • Pulse plasma thruster with ceramic nozzles on the side wall

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Embodiment Construction

[0019] The embodiments of the present invention are described in detail below in conjunction with the accompanying drawings: this embodiment is implemented on the premise of the technical solution of the present invention, and detailed implementation methods and specific operating procedures are provided, but the protection scope of the present invention is not limited to the following the described embodiment.

[0020] Such as figure 1 As shown, this embodiment includes: a high voltage power supply 1, an energy storage capacitor 2, a propellant 3, a side wall type ceramic nozzle 4, an anode 5, a cathode 6, a semiconductor spark plug 7, an ignition control circuit board 8, and a feed spring 9. The high-voltage power supply 1 is connected to the energy storage capacitor 2 through wires, charges the capacitor and stores the pulse discharge energy in the energy storage capacitor 2; the propellant 3 is fixed horizontally by the feed spring 9 and the boss of the anode 5, and t...

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Abstract

The invention relates to a pulse plasma thruster with a ceramic nozzle on the side wall, comprising: a high-voltage power supply, an energy storage capacitor, a propellant, a ceramic nozzle, an anode, a cathode, a semiconductor spark plug, an ignition control circuit board, and a feed spring. Wherein, the nozzles are wedge-shaped, and are installed in pairs on the side between the anode and the cathode on the inner wall of the thruster casing, and the installation position is as close as possible to the surface of the propellant. The end face of the ceramic nozzle near the electrode is designed to have a 45° chamfer. This type of nozzle can effectively improve the acceleration performance of the slow neutral gas during the working process of the thruster. At the same time, compared with the electrode-type nozzle, the side-wall nozzle can minimize the influence of the nozzle on the discharge channel, reduce the resistance of the main discharge circuit and obtain a higher discharge current. The new nozzle can reduce the loss of electromagnetic acceleration force and obtain higher thrust and work efficiency.

Description

technical field [0001] The invention relates to a functional assembly in the technical field of aerospace electric propulsion, in particular to a pulse plasma thruster with ceramic nozzles arranged on the side wall. Background technique [0002] With the development of emerging space technologies such as small satellites, planetary probes, and deep space exploration, aerospace electric propulsion systems are required to be lighter in weight, smaller in size, and consume less propellant. The traditional chemical propulsion method is increasingly difficult to meet the requirements of emerging space missions due to its low specific impulse and complex structure. Pulse Plasma Thruster (PPT) is a feasible solution for micro-satellite propulsion system. It has the advantages of high specific impulse, light weight, compact structure, small size, convenient and flexible control, etc. It can be used in micro-satellites Space tasks such as attitude control, orbit transfer and lifting...

Claims

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Application Information

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IPC IPC(8): F03H1/00
Inventor 康小明董磊赵万生
Owner SHANGHAI JIAO TONG UNIV
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