Active control device and method for spacecraft structure potential

A potential active control, spacecraft structure technology, applied in aerospace safety/emergency devices, electrical components, plasma and other directions, can solve problems affecting the normal operation of satellite measurement systems and measurement and control systems, measurement results errors, measurement and control data disorder and other problems

Active Publication Date: 2014-05-07
LANZHOU INST OF PHYSICS CHINESE ACADEMY OF SPACE TECH
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Problems solved by technology

[0003] Structural potential drift will affect the normal operation of the satellite measurement system and the meas

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  • Active control device and method for spacecraft structure potential
  • Active control device and method for spacecraft structure potential

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Embodiment Construction

[0020] 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 an active control device and method for a spacecraft structure potential. The device comprises a Langmuir probe, a hollow cathode and an extraction electrode. The Langmuir probe is arranged on one side of the hollow cathode and arranged on the outer wall of a spacecraft structure, the hollow cathode is arranged outside the spacecraft structure, the hollow cathode is connected with a structure ground of the spacecraft, the extraction electrode is arranged opposite to a nozzle of the hollow cathode, and the extraction electrode is connected with a power source. The control method includes the steps that the Langmuir probe is started, the structure potential of the spacecraft is obtained, then the hollow cathode and the extraction electrode are controlled to emit electrons to space, and therefore the structure potential of the spacecraft is controlled. The active control device and method have the advantages that the structure potential of the spacecraft can be rapidly decreased; the structure potential of the spacecraft can be kept about 0V; by changing the gas flow and a potential of the extraction electrode, the requirements for controlling structure potentials of spacecrafts different in orbit and structure can be met.

Description

technical field [0001] The invention belongs to the field of spacecraft space environment effect protection, and in particular relates to an active control device and a control method for a spacecraft structure potential. Background technique [0002] When the spacecraft is in orbit, it will interact with the environment such as space plasma and high-energy electrons to accumulate electrostatic charges. In spacecraft design, its overall metal frame structure is generally regarded as the "ground" in the circuit, called "structural ground", and its potential is "ground potential". However, the "zero potential" in space generally refers to the potential of the plasma around the spacecraft, and since the spacecraft is suspended in space as a whole, the accumulation of charges in the structural ground will cause the structural ground potential to rise and deviate from the "zero potential". The potential of the spacecraft's structural ground relative to the space plasma is called...

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Application Information

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