A micro thrust measurement device based on magnetic levitation

A measuring device, magnetic levitation technology, applied in the direction of measuring device, force/torque/power measuring instrument, measuring vehicle traction/propulsion power, etc., can solve the problem of circuit cable interference thrust measurement, etc., to prevent overflow and easy installation Effect

Active Publication Date: 2022-07-19
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0012] 2. Design the circuit bridging device to ensure the power supply and at the same time, there is no direct contact between the connectors, and solve the problem that the circuit cable interferes with the thrust measurement;

Method used

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  • A micro thrust measurement device based on magnetic levitation
  • A micro thrust measurement device based on magnetic levitation
  • A micro thrust measurement device based on magnetic levitation

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Embodiment Construction

[0041] In order to make the purposes, 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 with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments These are some embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative efforts shall fall within the protection scope of the present invention.

[0042] like Figure 1-3 As shown, a micro-thrust measurement device based on magnetic levitation includes a static support structure at the bottom, a rotating platform 7 suspended above the static support structure, and a bushing-type bridging device 3;

[0043] The static support structure includes a base platform 1, a base terminal 2, and ...

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Abstract

The invention is a micro thrust measuring device based on magnetic levitation, in particular: a static support structure includes a base platform, a base terminal, and magnetic suspension guide rails installed on both sides above the base platform; the base platform is provided with a power supply base terminal on the side; The moving magnet is placed under the platform, and the size and shape are adapted to the magnetic suspension guide rail; the bushing-type bridging device is arranged between the base and the center of the rotating platform, including the air supply outlet pipeline of the electric thruster, the bushing-type multi-stage plug, The rubber anti-overflow ring arranged on the periphery of the funnel-shaped pipe opening of the air supply outlet pipeline, the bushing-type multi-stage joint bridged with the electric thruster circuit, and the air supply inlet pipeline bridged with the electric thruster gas circuit; the base terminal and the shaft The sleeve-type multi-stage joints are connected correspondingly. The device can eliminate the influence of environmental noise on the measurement, and the interference of the thruster power cable and gas supply pipeline to the rotation of the swing arm.

Description

technical field [0001] The invention belongs to the field of micro-thrust measurement of space thrusters, in particular to a micro-thrust measurement device based on magnetic levitation. Background technique [0002] With the development of the international aerospace industry, the demand for thrusters in the fields of satellite attitude and orbit control, interstellar navigation, and deep space aerospace is increasing, and the performance requirements are also constantly improving. Electric thrusters with smaller resolution and higher specific impulse have become The focus of current research. [0003] Accurately measuring the thrust of the space electric thruster is the most important parameter to evaluate the working performance of the electric thruster. The space electric thruster generates plasma through high-voltage discharge. After the plasma is accelerated by the ion optical system, the high-speed ejection produces a thrust in the range of 0 to 100 mN. between. Sin...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01L5/13
CPCG01L5/133
Inventor 王伟宗王海波付宸聪刘伟张金瑞刘思远
Owner BEIHANG UNIV
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