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[1]赵阳,寇鑫,张诚,等.一体化姿控火箭发动机小推力测量方法[J].火箭推进,2024,50(06):69-77.[doi:10.3969/j.issn.1672-9374.2024.06.005]
　ZHAO Yang,KOU Xin,ZHANG Cheng,et al.Small thrust measurement method for integrated attitude control rocket engine[J].Journal of Rocket Propulsion,2024,50(06):69-77.[doi:10.3969/j.issn.1672-9374.2024.06.005]
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一体化姿控火箭发动机小推力测量方法

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 50 期数: 2024年06期 页码: 69-77 栏目: 目次 出版日期: 2024-12-25
Title:
Small thrust measurement method for integrated attitude control rocket engine
文章编号:
1672-9374(2024)06-0069-09
作者:
赵阳1; 寇鑫2; 张诚1; 李大海2; 李广会2; 单王珍1; 张中柱2; 乔智霞1; 韩香广1; 赵立波1
1.西安交通大学,陕西 西安 710049; 2.西安航天动力试验技术研究所,陕西 西安 710100
Author(s):
ZHAO Yang1; KOU Xin2; ZHANG Cheng1; LI Dahai2;  LI Guanghui2; SHAN Wangzhen1; ZHANG Zhongzhu2; QIAO Zhixia1; HAN Xiangguang1; ZHAO Libo1
1.Xi'an Jiaotong University, Xi'an 710049, China; 2.Xi'an Aerospace Propulsion Test Technology Institute, Xi'an 710100, China
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
Keywords:
attitude control engine;  small thrust measurement;  glass micro-melting;  structural integration;  integrated
分类号:
V434+.3
DOI:
10.3969/j.issn.1672-9374.2024.06.005
文献标志码:
A
摘要:
在液体姿控火箭发动机的小推力测量过程中,由于高频交变载荷的影响,推进剂供应管路的振动及其约束会对推力测量的准确性产生较大影响,而传统的黏结式应变片灵敏度低,在测量过程中会产生蠕变,导致测量结果不准确。针对这一问题,提出了一种新型的推力测试方法,该方法采用轮辐式一体化火箭推力测量结构,将管路与敏感梁集成在推力测量结构上,极大地减少了管路振动引起的测量误差。通过玻璃微熔技术在不锈钢基底上制备应变单元,实现推力的高精度测量。传感器测试结果表明该装置非线性性能为±0.45%FS,重复性性能为±0.16%FS,迟滞性能为±0.40%FS,基本测量误差达到±0.62%FS,满足小推力发动机的实际测试需求,为有约束条件下的小推力测量以及宽温区推力测量等提供了一种新的方法和途径。
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.

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备注/Memo

收稿日期:2024- 07- 22修回日期:2024- 11- 07
基金项目:国家重点研发计划(2023YFB3209103); 陕西省自然科学基金(2022JQ-554); “两链”融合重点专项(2023-LL-QY-35)
作者简介:赵 阳(1999—),男,硕士研究生,研究领域为MEMS集成式力学传感器。
通信作者:韩香广(1988—),男,博士,副研究员,研究领域为发动机推力测量技术与特种压力测量技术。

更新日期/Last Update: 1900-01-01