Thrust measurement system for micro thrustor in simulated vacuum environment

Abstract

The invention discloses a thrust measurement system for a micro thrustor in a simulated vacuum environment. The system includes a vacuum thrust measurement device (1), a data processor (2), a high pressure gas cylinder (3), a vacuum pump (4), a thrust sensor (9) and a micro thrustor (20). The thrust sensor (9) is fixed on the bottom part of the vacuum thrust measurement device (1) and a right-angle adapter (10) is fixedly mounted on the thrust sensor (9). The top end of the micro thrustor (20) is perpendicularly fixed on one end of the right-angle adapter (10). A hose (19) is connected with ahigh pressure gas cylinder (3). The other end of the hose extends into the right-angle adapter (10) so as to connect with the micro thrustor (20). The micro thrustor (20) ejects gas and generates a thrust. The thrust sensor (9) measures a thrust data and transmits the data to the data processor (2). Through measuring thrust values of the micro thrustor (20) and environment pressure values in different vacuum degrees and after function fitting deduction on test data, a practical thrust value in a vacuum condition can be obtained and measurement results become more accurate and objective.

Description

Technical field [0001] The invention belongs to the technical field of micro-thrust measurement, in particular to a micro-thruster thrust measurement system under simulated vacuum environment. Background technique [0002] Micro thruster is a small thrust attitude control power device used in aerospace and other fields. Generally, compressed gases such as air, nitrogen, and helium are used as propellants. In the process of research and development of micro thrusters, thrust measurement technology has played a vital role. Among them, the thrust measurement system under simulated vacuum environment can most objectively and accurately measure the thrust of micro thrusters under real working conditions. . [0003] At present, the micro-thruster thrust measurement system generally adopts a balance type or a fully elastic structure to measure the micro-thrust. For example, the Chinese Invention Patent (Patent No. CN200610089041) discloses a thrust measurement system suitable for space ...

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Problems solved by technology

For example, the Chinese invention patent (Patent No. CN200610089041) discloses a thrust measurement system suitable for space micro-thrust engines. It uses a fully elastic structure to measure the thrust of the arc micro-thruster. The propellant pipeline uses stainless steel pipes to interfere with the micro-thrust measurement. Larger, and the system structure is complex and inconvenient to operate

Chinese invention patent (patent number CN200910312194) discloses a micro thrust measuring device, which uses a balance structure to overcome the influence of the deformation of the gas supply pipeline in the propulsion system on thrust measurement, but does not have a structural design for thrust measurement in a vacuum environment , cannot accurately measure the thrust in a vacuum environment

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