Method and device for measuring pneumatic thrust indirectly

A measurement method and thrust technology, which is applied in the field of indirect measurement of aerodynamic thrust, can solve the problems of high debugging and calibration requirements, inability to estimate measurement errors, etc., and achieve the effects of avoiding disturbance, good operability, high sampling frequency and accuracy

Inactive Publication Date: 2010-08-18
INST OF MECHANICS - CHINESE ACAD OF SCI
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Problems solved by technology

[0004] The purpose of the present invention is to overcome the high requirements for equipment debugging and calibration in the above-mentioned thrust measuring device, and at the same time, the same dynamometer will cause inestimable changes due to small changes that are difficult to grasp when debugging each time for an engine with the same shape and weight. In order to solve the defect of measurement error, a simple method and device for indirect measurement of aerodynamic thrust are provided

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  • Method and device for measuring pneumatic thrust indirectly
  • Method and device for measuring pneumatic thrust indirectly
  • Method and device for measuring pneumatic thrust indirectly

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[0039] refer to figure 1 , figure 2 , making a measuring device for indirect measurement of rocket engine supersonic jet aerodynamic thrust, the device includes: 1 sampling hole, 21 water-gas isolation sleeve, 22 probe outer tube, 23 cooling water spacer, 24 cooling water outlet, 25 cooling water inlet , 3 Gas passage, 4 Insulator, 5 Differential pressure sensor sensing surface, 6 Differential pressure sensor, 7 Signal line, 8 Data acquisition system, 9 Data transmission line, 10 Data processing and analysis system, 11 Temperature adjustment system, 12 Probe support Parts, 13 movable platforms 1, 14 movable platforms 2.

[0040] In this embodiment, the diameter of the sampling hole 1 is 0.9mm, so that the measurement results can reach a higher spatial resolution; the cone angle of the conical head of the dynamic pressure probe is 24°, and the dynamic pressure probe connected to the conical head is straight The diameter of the section is 12mm to minimize the disturbance to t...

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Abstract

The invention discloses a method and a device for measuring pneumatic thrust indirectly, and the pneumatic thrust measuring device mainly comprises a dynamic pressure probe, a probe supporting part, a movable platform, a data acquisition system and a data processing and analysis system. The method is as follows: the dynamic pressure probe is fixed on the movable platform by the probe supporting part, and the dynamic pressure probe is regulated to enable the axis of the dynamic pressure probe and that of a rocket engine to be parallel and to be at the same height. When the movable platform moves at a uniform speed along the direction perpendicular to the axis of the engine to enable the dynamic pressure probe to sweep over a hypersonic jet flow which is ejected from an engine nozzle, a differential pressure transducer which is arranged at the back end of the dynamic pressure probe responds to the dynamic pressure signals of the hypersonic jet flow in real time, the data acquisition system acquires the dynamic pressure and the distribution signals in real time, and the data processing and analysis system obtains the pneumatic thrust by carrying out surface integral processing on the measured radial distribution signals of the dynamic pressure.

Description

technical field [0001] The present invention relates to a simple method and device for indirect measurement of aerodynamic thrust. Background technique [0002] With the development of the times, space control capabilities play an increasingly important role in a country's security. Advanced space propulsion technology is a necessary supporting technology for interstellar navigation and deep space scientific exploration. Carrying out a large number of performance research and reliability simulation experiments on the ground is a necessary step before the rocket engine can actually run in the sky. Among them, the measurement of thrust is essential. The rocket engine discharges the propellant backward at high speed, and the backward momentum increased by the propellant is equal to the forward thrust received by the thruster. [0003] Direct measurement of thrust is relatively simple in principle, that is, the rocket engine is directly placed on the force measuring frame, and...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/96
Inventor 潘文霞吴承康孟显
Owner INST OF MECHANICS - CHINESE ACAD OF SCI
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