火箭推进2024，Vol.50Issue(6)：69-77,9.DOI:10.3969/j.issn.1672-9374.2024.06.005
一体化姿控火箭发动机小推力测量方法
Small thrust measurement method for integrated attitude control rocket engine
摘要
Abstract
In the process of measuring the low thrust of liquid attitude control rocket engines,due to the influence of high-frequency alternating loads,the vibration of the propellant supply pipeline and its constraints will have a great impact on the accuracy of thrust measurement.The traditional adhesive strain gauge has low sensitivity and will produce creep during the measurement process,resulting in inaccurate measurement results.To address this problem,proposes a new thrust test method.This method adopts a spoke-type integrated rocket thrust measurement structure,integrates the pipeline and the sensitive beam on the thrust measurement structure,and greatly reduces the measurement error caused by pipeline vibration.The strain unit is prepared on a stainless steel substrate by glass micro-melting technology to achieve high-precision in-situ measurement of thrust.The sensor test results show that the nonlinear performance of the device is±0.45%FS,the repeatability performance is±0.16%FS,the hysteresis performance is±0.40%FS,and the basic measurement error reaches±0.62%FS,which meets the actual test requirements of low thrust engines and provides a new method and approach for low thrust measurement under constraints and wide temperature range thrust measurement.关键词
姿控发动机/小推力测量/玻璃微熔/结构一体化/集成式Key words
attitude control engine/small thrust measurement/glass micro-melting/structural integration/integrated分类
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赵阳,赵立波,寇鑫,张诚,李大海,李广会,单王珍,张中柱,乔智霞,韩香广..一体化姿控火箭发动机小推力测量方法[J].火箭推进,2024,50(6):69-77,9.基金项目
国家重点研发计划(2023YFB3209103) （2023YFB3209103）
陕西省自然科学基金(2022JQ-554) （2022JQ-554）
"两链"融合重点专项(2023-LL-QY-35) （2023-LL-QY-35）
