Negative step force generation system and device and method for calibrating dynamic characteristics of thrust measurement

A technology for generating systematic, negative step force, applied in measuring devices, force/torque/work measuring instrument calibration/testing, instruments, etc. The structure is simple and novel, the accuracy is guaranteed, and the data processing process is simple.

Pending Publication Date: 2018-05-04
西安航天计量测试研究所
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Generally, the dynamic signal of the thrust measuring device is relatively complex and has many influencing factors. It is difficult to accurately describe its dynamic characteristics by using theoretical calculation method

Method used

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  • Negative step force generation system and device and method for calibrating dynamic characteristics of thrust measurement
  • Negative step force generation system and device and method for calibrating dynamic characteristics of thrust measurement
  • Negative step force generation system and device and method for calibrating dynamic characteristics of thrust measurement

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Embodiment Construction

[0048] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0049] from figure 1 It can be seen that the negative step force generating system in this embodiment includes a power supply module and a capacitor module;

[0050] The power supply module includes a power supply and a power supply indicating circuit; the capacitor module includes a capacitor charging circuit, a discharging circuit and a fuse circuit;

[0051] The output terminals of the power supply are respectively connected with the input terminals of the power supply indicating circuit and the capacitor charging circuit;

[0052] The power indicating circuit includes a first resistor R1 and a second light-emitting diode D2 connected in series in sequence, the output end of the power supply is connected to the input end of the first resistor R1, and the output end of the second light-emitting diode D2 is grounded;

[0053] The capacitor cha...

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PUM

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Abstract

The invention belongs to the field of laboratory dynamic thrust sensor measurement testing, and particularly relates to a negative step force generation system and a device and method for calibratingdynamic characteristics of thrust measurement. The negative step force generation system is mainly used for supplying a calibrated step force to a force measurement system during the initial verification and regular calibration of a thrust measuring device. A current pulse is used to burn out a loop of an electromechanical circuit breaker, and it is ensured that a standard weight used for dynamiccalibration is quickly and controllably dropped in the electromechanical form to form a standard weight disconnect signal that can be recorded in a data processing unit. It can be ensured that a standard force source for dynamic calibration can be quickly and controllably dropped in the electromechanical form, and a signal acquisition unit can collect a voltage signal at the time of the return line fuse, which can effectively ensure the accuracy of a negative step force value.

Description

technical field [0001] The invention belongs to the field of measurement and testing of laboratory dynamic thrust sensors, and in particular relates to a negative step force generation system used for calibration of a dynamic thrust measurement device and a calibration device for calibrating the dynamic characteristics of a thrust measurement device with the negative step force generation system and method. Background technique [0002] In the field of aerospace, the attitude control engine usually works in pulse mode in space, and the thrust generated is a series of pulse forces with different durations, which are used to correct the attitude deviation of spacecraft such as satellites in a timely and accurate manner. The pulse width varies from a few milliseconds to tens of seconds. During the high-altitude simulation test run on the ground, it is necessary to use the thrust measurement system to accurately provide the dynamic thrust technical indicators of the attitude co...

Claims

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Application Information

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IPC IPC(8): G01L25/00
CPCG01L25/00
Inventor 张建斌郑显锋张攀史玮强张海飞张婧
Owner 西安航天计量测试研究所
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