A method for obtaining plume parameters of electric propulsion spacecraft

A parameter acquisition, spacecraft technology, applied in the field of aerospace, to achieve the effect of improving sensitivity, stable and reliable test process, safe and reliable work

Active Publication Date: 2016-08-24
LANZHOU INST OF PHYSICS CHINESE ACADEMY OF SPACE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

At present, my country is still unable to monitor the plasma plume parameters of electric propulsion engines in situ

Method used

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  • A method for obtaining plume parameters of electric propulsion spacecraft
  • A method for obtaining plume parameters of electric propulsion spacecraft
  • A method for obtaining plume parameters of electric propulsion spacecraft

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Embodiment Construction

[0035] The electric propulsion spacecraft plume parameter acquisition method of the present invention, it comprises the following steps:

[0036] Step 1, such as figure 1As shown in the figure, the components of the electric propulsion spacecraft plume parameter acquisition device are assembled: the observation window 1 of the vacuum chamber is set at the head end of the vacuum chamber 2; The ignition control cabinet 8 is connected with the electric thruster 4, and the computer 7 is connected with the multi-parameter diagnostic equipment (3, 6) of the two electric thrusters respectively. A mounting plate is arranged inside the vacuum chamber 2, one end of the mounting plate is installed with the multi-parameter diagnostic equipment 3 of the first electric thruster, the other end is fixed with a movable bracket 5, and the electric thruster 4 is installed on the fixed movable bracket 5; The second electric thruster multi-parameter diagnosis device 6 is movably installed on the ...

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Abstract

The invention provides an electric propulsion spacecraft plume parameter acquisition method. In a condition of simulating a spacecraft orbit environment, plasma potential, plasma density, electron temperature, plasma ion energy spectrum, electric propulsion plume pollutant deposition and the like, and distribution of space parameters around a thruster are tested; due to use of an oil-free vacuum system, a thin gas atmosphere and a clean environment condition are provided for the method, accuracy of measured data during the test process is greatly enhanced, and an electric thruster test operation risk is reduced; and pollution data in electric thruster multi-parameter diagnosis equipment are measured and acquired, electric propulsion spacecraft plasma plume parameter distribution and a spacecraft in-orbit performance degradation condition in a simulated space environment condition can be estimated, and guidance and basis are provided for research on the electric propulsion spacecraft and service life estimation. The method of the invention is applied to electric propulsion spacecraft engine plume feature test and can be applied to scale test.

Description

technical field [0001] The invention belongs to the technical field of aerospace and is applied to the ground test and on-orbit monitoring of plume parameters of electric propulsion spacecraft, in particular to a method for obtaining plume parameters of electric propulsion spacecraft. Background technique [0002] With the continuous development of aerospace technology, various thrusters, such as Arcjet, Magnetoplasma Thruster (MPD), Steady State Plasma Thruster (SPT), Ion Thruster (IE), etc. More and more applications are on earth satellites and deep space probes. The plume ejected by the electric thruster is a high-temperature, high-energy plasma flow. However, due to its special plasma plume characteristics, electric propulsion technology causes changes in the plasma environment around the satellite, which induces a series of negative effects such as electrification on the satellite surface, deposition pollution, disturbance torque, and electromagnetic interference. At ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M15/14G01M15/02
Inventor 颜则东田恺马亚莉庄建宏孔风连
Owner LANZHOU INST OF PHYSICS CHINESE ACADEMY OF SPACE TECH
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