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Spacecraft structural potential active control system and control method

A technology of potential active control and spacecraft structure, applied in electrical components, aerospace safety/emergency devices, plasma, etc., can solve the problems that the control system cannot be well satisfied, and achieve high working stability, long life, and average The effect of low power consumption

Active Publication Date: 2014-05-14
LANZHOU INST OF PHYSICS CHINESE ACADEMY OF SPACE TECH
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AI Technical Summary

Problems solved by technology

[0007] Existing control systems cannot meet the above requirements well

Method used

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  • Spacecraft structural potential active control system and control method
  • Spacecraft structural potential active control system and control method
  • Spacecraft structural potential active control system and control method

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Embodiment Construction

[0048] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of embodiments of the present invention, but not all embodiments. Elements and features described in one drawing or one embodiment of the present invention may be combined with elements and features shown in one or more other drawings or embodiments. It should be noted that representation and description of components and processes that are not related to the present invention and known to those of ordinary skill in the art are omitted from the drawings and descriptions for the purpose of clarity. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the ar...

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Abstract

The invention discloses a spacecraft structural potential active control system and a control method. The control system comprises a structural potential monitoring probe, a hollow cathode, a power supply unit, a storage and supply unit and a control unit. The structural potential monitoring probe is used for acquiring spacecraft structural potential and sending back to the ground in real time; the hollow cathode is used for emitting electron beam currents; the power supply unit is used for converting spacecraft primary busbar power supply into voltage required by operation of the hollow cathode and respectively supplying to the hollow cathode, the control unit and the storage and supply unit; the storage and supply unit is used for providing working media required by operation of the hollow cathode; the control unit is used for acquiring potential monitoring signals and providing power and gas supply conditions required by operation of the hollow cathode, and the control unit is respectively connected with the structural potential monitoring probe, the power supply unit and the storage and supply unit through signal circuits. The spacecraft structural potential can be lowered quickly by using the hollow cathode and an anode to emit electrons; the spacecraft structural potential is kept in a range of 0-5V; the spacecraft structural potential active control system is low in average power consumption, long in service life and high in operation stability.

Description

technical field [0001] The invention relates to the field of spacecraft space environment effect protection, in particular to a spacecraft structure potential active control system and a control method. Background technique [0002] The interaction between the spacecraft and the space plasma during orbital operation will cause the potential drift of the structure, and the measurement and measurement and control equipment that require high stability of the ground potential will be affected. By actively sending electrons into space, the structural potential of the spacecraft can be effectively controlled to ensure that it is within the scope of the spacecraft design requirements. [0003] The control system of the potential of the spacecraft structure must meet the following three conditions: [0004] (1) Emission current I beam Large enough to allow the potential of the spacecraft structure to drop rapidly in a short period of time; [0005] (2) The power consumption is sm...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/52H05H1/46
Inventor 史亮李得天秦晓刚陈益峰汤道坦杨生胜
Owner LANZHOU INST OF PHYSICS CHINESE ACADEMY OF SPACE TECH
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