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Related Experiment Video

Updated: Jun 8, 2026

Optimization, Test and Diagnostics of Miniaturized Hall Thrusters

Optimization, Test and Diagnostics of Miniaturized Hall Thrusters

Published on: February 16, 2019

Thrust stand for low-thrust liquid pulsed rocket engines.

Qin Xing¹, Jun Zhang, Min Qian

¹Key Laboratory for Precision and Nontraditional Machining Technology of Ministry of Education, Dalian University of Technology, Dalian 116024, People's Republic of China.

The Review of Scientific Instruments

|October 5, 2010

Summary

This summary is machine-generated.

A new thrust stand accurately measures pulsed thrust from low-thrust liquid pulsed rocket engines. This system is crucial for precise on-orbit vehicle control using its advanced thrust dynamometer.

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Last Updated: Jun 8, 2026

Optimization, Test and Diagnostics of Miniaturized Hall Thrusters

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Published on: February 16, 2019

Laboratory Scale Slow Cook-Off Testing of Rocket Propellants: The Combustion Rate Analysis of a Slowly Heated Propellant (CRASH-P) Test

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Published on: February 6, 2021

Area of Science:

Aerospace Engineering
Mechanical Engineering
Sensor Technology

Background:

Accurate measurement of pulsed thrust is critical for controlling low-thrust liquid pulsed rocket engines.
Existing methods may lack the precision required for fine on-orbit adjustments.
Development of specialized instrumentation is necessary for advanced spacecraft propulsion systems.

Purpose of the Study:

To develop and validate a novel thrust stand for measuring pulsed thrust generated by low-thrust liquid pulsed rocket engines.
To ensure accurate thrust measurement for fine control of on-orbit vehicles.
To characterize the performance of the developed thrust stand.

Main Methods:

A thrust stand was designed, incorporating a core thrust dynamometer with shear mode piezoelectric quartz sensors.
The dynamometer utilizes an integral shell structure with sensors fitted into double-elastic-half-ring grooves, transferring thrust via static friction.
Calibration was performed both statically (using a standard force sensor) and dynamically (using a pendulum-typed steel ball impact technique).

Main Results:

The thrust stand demonstrated a sensitivity of 25.832 mV/N, a linearity error of 0.24% FSO, and a repeatability error of 0.23% FSO.
The first natural frequency of the thrust stand was determined to be 1245 Hz.
The system accurately measured thrust waveforms for firings in the 5-20 N range at a 50 Hz pulse frequency.

Conclusions:

The developed thrust stand is capable of accurately measuring pulsed thrust from low-thrust liquid pulsed rocket engines.
The system's performance characteristics (sensitivity, linearity, repeatability, natural frequency) are suitable for its intended application.
This technology enables precise control of on-orbit vehicles requiring fine thrust adjustments.