Power supply control system and method for Hall electric thruster of spacecraft

A technology of Hall electric propulsion and space vehicles, applied in the direction of aerospace vehicle propulsion system devices, etc., can solve the problems of weakening advantages, low reliability, and multiple power supply sources, and achieve the effect of improving system power supply control and power supply efficiency

Active Publication Date: 2016-02-03
NO 771 INST OF NO 9 RES INST CHINA AEROSPACE SCI & TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the different types of power required by each pole of the existing Hall electric propulsion power supply system

Method used

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  • Power supply control system and method for Hall electric thruster of spacecraft
  • Power supply control system and method for Hall electric thruster of spacecraft
  • Power supply control system and method for Hall electric thruster of spacecraft

Examples

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Example Embodiment

[0023] Such as figure 1 As shown, the power supply system of the present invention includes anode power supply I, anode power supply I sampling circuit, anode power supply II, anode power supply II sampling circuit, cathode heating power supply, cathode heating power sampling circuit, cathode heating power output switch, ignition power supply , Ignition power sampling circuit, ignition power output switch, control unit and filter circuit.

[0024] The output of the anode power supply module supplies power for the anode of the Hall electric thruster; the output of the cathode heating power supply module supplies power for the cathode heater of the Hall electric thruster; and the output of the ignition power supply supplies power for the cathode igniter of the Hall electric thruster.

[0025] The anode power supply module converts the primary power bus into the high-voltage constant voltage source required by the anode of the Hall electric thruster; the cathode heating power module co...

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Abstract

The invention provides a power supply control system for a Hall electric thruster of a spacecraft, and the power supply control system can be used for centralized power supply and centralized control and management. The power processing framework of the Hall electric thruster comprises an anode power module, a cathode power module and an ignition power module; each power module comprises an enable circuit; the working and turning-off of each power module are controlled through enable signals of a control unit which act on each power module in a centralized manner; the external enable signal acts on the enable control end of each power module, and the enable signal emitted under the centralized sequential control of the control unit controls each power module to work and be turned off sequentially; and therefore, the Hall electric thruster can ignite successfully, continuously and stably. Therefore, the operation control of the electric thrusting sub system can be finished under a preset timing sequence; redundancy switchover is performed by control commands, so that telemetry parameters are acquired, isolatedly-converted, and supplied to telemetering/telecontrol ports, and a telecontrol function is realized; and the power supply control and power supply efficiency of the system are effectively improved.

Description

technical field [0001] The invention relates to a power processing system of a Hall electric propulsion system, in particular to a power supply control system and method for a Hall electric propulsion device of a space vehicle. Background technique [0002] Electric propulsion technology is an advanced spacecraft propulsion technology that uses electric energy to accelerate the propellant to achieve high specific impulse. Electric propulsion has high specific impulse and consumes less working fluid, which can be 1 to 2 orders of magnitude lower than that of chemical propulsion. The use of electric propulsion technology can reduce the mass of the aircraft, improve the service life, and improve the payload capacity. Electric propulsion technology has great application prospects in geosynchronous orbit satellites and deep space exploration. [0003] The electric propulsion power supply control system is one of the main components of the electric propulsion system, and the elect...

Claims

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Application Information

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IPC IPC(8): B64G1/40
Inventor 成渭民康小录张建渝乔彩霞王波张萍张新平
Owner NO 771 INST OF NO 9 RES INST CHINA AEROSPACE SCI & TECH
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