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Device for measuring micro thrust of engine

An engine and thrust technology, applied in measuring devices, force/torque/work measuring instruments, instruments, etc., can solve the problem of low measurement accuracy, and achieve the effect of eliminating influence and improving measurement accuracy

Active Publication Date: 2011-04-13
TSINGHUA UNIV
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  • Abstract
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Problems solved by technology

The NASA Lewis Research Center of the United States uses bending displacement electromagnetic force compensation and proportional calculus circuit control methods to measure the thrust of Arcjet; the Russian Institute of Atomic Energy and other institutions use the pendulum displacement electromagnetic force compensation method, and the micro-thrusters and micro-thrusts they developed measure the micro-thrust The device is world-leading, but the measurement accuracy of the device is not high

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  • Device for measuring micro thrust of engine
  • Device for measuring micro thrust of engine
  • Device for measuring micro thrust of engine

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Embodiment Construction

[0019] The fundamental reason why the micro-thrust is difficult to measure is that the work of developing the engine is carried out in the gravitational field of the earth, and the characteristic of the micro-thrust engine is that its own weight is much greater than the thrust it generates; in addition, the pipelines and The control circuit has a great influence on the thrust measurement. This is because after the thrust is generated, there will be a certain deformation, and the stress of the deformation will have a certain impact on the measurement results, but this part of the impact is difficult to directly measure, thus affecting the final result. measurement accuracy. The technical scheme provided by the invention can well solve the above problems, thereby achieving high measurement accuracy for mN-level thrust. In terms of implementation, the engine is placed on one end of the beam, and the counterweight is applied to the other end. Using the directionality of the moment...

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Abstract

The invention discloses a device for measuring micro thrust of an engine, and relates to force measurement equipment. The device comprises a pedestal, a vertical beam with a knife edge, a propellant storage box, a cross beam, a balance weight, the engine, an electric control box, a force transducer, a signal processing unit and a calculator, and is characterized in that: the dead weight of the engine is balanced by using a knife edge structure and the balance weight; and the influence of a propellant pipeline and a control line on measurement accuracy is eliminated through relation between force and force arm according to a mechanical principle. When the range of the force to be measured is at the scale of hundreds of millinewtons, zero drift of the force is less than + / -1 percent F.S. every hour, the stable state measurement error is less than + / -1 percent of a full range, and high repeatability is guaranteed. The device can meet the accuracy requirement of small satellite attitude control engine thrust measurement and has broad application prospect in micro thrust measurement of the engine.

Description

technical field [0001] The invention relates to a force measuring device, in particular to a high-precision micro engine thrust measuring device, which belongs to the technical field of force measurement. Background technique [0002] In recent years, with the development of science and technology, the development and development of international small satellites and microsatellites has been rapid, which in a sense represents the trend of spacecraft miniaturization. Small satellites are widely used in many fields such as data communication, data transmission, ground environment monitoring, space environment observation, navigation and positioning, and scientific experiments. Compared with medium and high-orbit satellites, small satellites have low investment and operating costs, strong emergency response capabilities and flexibility, and a short system construction period, with broad application prospects. Therefore, a "small satellite craze" appeared in the international a...

Claims

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Application Information

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IPC IPC(8): G01L5/00
Inventor 龚景松侯凌云赵文华
Owner TSINGHUA UNIV
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