Cold cathode structure capable of allowing space electric propulsion to be started quickly

A quick-start, cold-cathode technology, applied in the direction of discharge tube cold cathode, discharge tube main electrode, etc., can solve problems such as low reliability, difficult process, complex system, etc., to increase system reliability, improve response performance, simplify The effect of system structure

Inactive Publication Date: 2016-08-24
SHANGHAI INST OF SPACE PROPULSION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Preheating the emitter through the heater usually adopts direct or indirect methods, which generally takes 3 to 10 minutes, which seriously affects the rapid response capability of the electric propulsion system and limits the scope of application.
The working life of the electric propulsion system of the spacecraft requires tens of thousands of hours. The heater of the hot cathode has a complex structure and difficult process, and the heater is prone to short circuit or open circuit with the increase of the working life. Therefore, the heater restricts the life and reliability of the hot cathode. The key factor
In addition, the spacecraft propulsion system must be equipped with a set of low-voltage high-current heating power supply and a set of high-voltage low-current ignition power supply for the hot cathode. The system is more complicated and the reliability is lower.

Method used

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  • Cold cathode structure capable of allowing space electric propulsion to be started quickly

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0023] Emitter material selection 411 type barium tungsten emitter (BaO:Al 2 o 3 :CaO molar ratio 4:1:1), molybdenum is used for ignition electrode, cathode top and cathode tube, titanium is used for heat shield, and 95% Al is used for insulator 2 o 3 Ceramic, other materials choose stainless steel.

[0024] In a vacuum of 5 x 10 -4 In the Pa environment, the flow rate of the quick-start cold cathode assembly is 3-5 sccm (standard cubic centimeter per minute) xenon working fluid, the internal gas pressure reaches about 3800Pa, and a high voltage of 300-500V is applied between the ignition electrode and the cathode top. The cathode discharges within 20ms and can stably emit an electron current of 1.5-2.5A.

Embodiment 2

[0026] The emitter material is polycrystalline lanthanum hexaboride, the ignition electrode, cathode top, and cathode tube are made of molybdenum, the heat shield is made of titanium, and the insulator is made of 95% Al 2 o 3 Ceramic, other materials choose stainless steel.

[0027] In a vacuum of 5 x 10 -4 In the Pa environment, the flow rate of the cold cathode is 5-10sccm (standard cubic centimeters per minute) xenon working fluid, the internal gas pressure reaches about 4500Pa, and a high voltage of 600-1000V is applied between the ignition electrode and the top of the cathode. Internal discharge can stably emit electron current of 2.5-4.5A.

Embodiment 3

[0029] The emitter material is selectively doped scandate type 612 barium tungsten emitter (BaO:Al 2 o 3 :CaO molar ratio 6:1:2), molybdenum is used for ignition electrode, cathode top and cathode tube, molybdenum cylinder is used for heat shield, and 95% Al is used for insulator 2 o 3 Ceramic, other materials choose stainless steel.

[0030] In a vacuum of 5 x 10 -4 In the Pa environment, the flow rate of the cold cathode is 3-5sccm (standard cubic centimeters per minute) xenon working fluid, the internal gas pressure reaches about 3000Pa, and a high voltage of 300-500V is applied between the ignition electrode and the top of the cathode. Internal discharge can stably emit 1.5-4.5A electron current.

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Abstract

The invention discloses a cold cathode structure capable of allowing space electric propulsion to be started quickly. The cold cathode structure comprises a cathode tube, an emitter, a heat shield, a cathode top, an igniter electrode, an insulator, a housing and a flange. One end of the cathode tube is arranged to the flange, and the other end thereof is provided with the emitter, and is fixed by the cathode top; the cathode top is provided with a center hole; the emitter is in a hollow pipe shape, is arranged in the cathode tube and is closely contacted with the cathode top; the heat shield is arranged outside the cathode tube and is close to the cathode top, and covers the cathode tube portion equipped with the emitter; the igniter electrode is connected with the housing through the insulator; one end of the housing is connected with the insulator, and the other end thereof is connected with the flange; and the flange is provided with an installation hole. The cold cathode structure can start a cathode and an electric thruster to discharge quickly without pre-heating of a heater, and starting time of a spacecraft electric propulsion system is reduced from hundreds of seconds to one second and below, thereby greatly improving response performance of the electric propulsion system; and the cold cathode structure can be used in the field of space propulsion needing to be started quickly.

Description

technical field [0001] The invention belongs to the technical field of vacuum electronics and aerospace propulsion, and in particular relates to a cold cathode structure capable of rapidly starting space electric propulsion. Background technique [0002] The cathode is widely used in various electric vacuum devices, such as various electron guns, ion sources, and traveling wave tubes. The cathode is used as the electron source. The cathode has always been called the heart of vacuum electronic devices. In the propulsion system of a spacecraft, field emission thrusters and colloid thrusters require cathodes to provide electrons for plume neutralization; Hall thrusters, ion thrusters, and magnetoplasma thrusters also require cathodes to provide main discharge and plume Neutralized electrons. The cathode is a key component of the spacecraft electric propulsion system, which directly affects the performance and life of the propulsion system. [0003] At present, most of the cat...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H01J1/30
CPCH01J1/30
Inventor 康小录乔彩霞张志远张岩杭观荣薛伟华余水淋邱刚
Owner SHANGHAI INST OF SPACE PROPULSION
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