火箭推进

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。

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.

引言
1 一体化推力测试架结构设计
2 敏感单元制备
3 测试与分析
4 结语

图1 现有推力测量装置<br/>Fig.1 Existing thrust measurement device

图1 现有推力测量装置
Fig.1 Existing thrust measurement device

图2 发动机推力与燃烧室压强对比<br/>Fig.2 Comparison of engine thrust and combustion chamber pressure

图2 发动机推力与燃烧室压强对比
Fig.2 Comparison of engine thrust and combustion chamber pressure

图3 发动机推力整体测试系统<br/>Fig.3 Overall testing system of engine thrust

图3 发动机推力整体测试系统
Fig.3 Overall testing system of engine thrust

图4 不同形状管路应力分布<br/>Fig.4 Stress distribution of pipelines with different shapes

图4 不同形状管路应力分布
Fig.4 Stress distribution of pipelines with different shapes

表1 不同管路形状下推力测试架性能<br/>Tab.1 Performance of thrust test stand under different pipeline shapes

表1 不同管路形状下推力测试架性能
Tab.1 Performance of thrust test stand under different pipeline shapes

图5 敏感梁宽度尺寸优化仿真<br/>Fig.5 Optimization simulation of the sensitive beam width

图5 敏感梁宽度尺寸优化仿真
Fig.5 Optimization simulation of the sensitive beam width

图6 应力集中区厚度尺寸优化仿真<br/>Fig.6 Optimization simulation of thickness and size of stress concentration area

图6 应力集中区厚度尺寸优化仿真
Fig.6 Optimization simulation of thickness and size of stress concentration area

图7 一体化推力测试架结构<br/>Fig.7 Integrated thrust test frame structure

图7 一体化推力测试架结构
Fig.7 Integrated thrust test frame structure

图8 不同结合技术结构对比 <br/>Fig.8 Comparison of different combination technology structures

图8 不同结合技术结构对比
Fig.8 Comparison of different combination technology structures

图9 金丝引线连接<br/>Fig.9 Gold wire lead connection

图9 金丝引线连接
Fig.9 Gold wire lead connection

图10 一体化推力测试架实物<br/>Fig.10 Integrated thrust test stand

图10 一体化推力测试架实物
Fig.10 Integrated thrust test stand

图11 推力测试平台<br/>Fig.11 Thrust test platform

图11 推力测试平台
Fig.11 Thrust test platform

图12 推力标定结果<br/>Fig.12 Thrust calibration result

图12 推力标定结果
Fig.12 Thrust calibration result

表2 静态性能测试结果<br/>Tab.2 Static performance test results

表2 静态性能测试结果
Tab.2 Static performance test results

表3 现有测量方式对比<br/>Tab.3 Comparison of existing measurement methods

表3 现有测量方式对比
Tab.3 Comparison of existing measurement methods

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备注

引言

1 一体化推力测试架结构设计

2 敏感单元制备

3 测试与分析

4 结语

期刊信息