航天器6维微振动力测试系统的设计与试验
为了测试不同状态下航天器各活动部件在低频及超低频区的6维微振动表现,设计了一种以压电传感器为核心的6维微振动力测试系统.通过标定及对软件的设计实现了传感器信号在空间上的实时采集、分析及处理等功能,并最终得到空间6维力.介绍了该测试系统的工作原理和动态标定方法,对该测试台进行了仿真及测试试验.结果表明,固有频率的仿真与试验结果前5阶的相对误差在5%以内,1阶频率大于400Hz;力及力矩分辨率分别可达到0.1N及0.01N·m（SNR大于10）;在频域上0-400Hz范围内,该测试系统各通道的相对误差在7%以内....
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| Published in | 江苏大学学报（自然科学版） Vol. 38; no. 1; pp. 56 - 61 |
|---|---|
| Main Author | |
| Format | Journal Article |
| Language | Chinese |
| Published |
中国科学院 长春光学精密机械与物理研究所,吉林 长春,130033
2017
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| Subjects | |
| Online Access | Get full text |
| ISSN | 1671-7775 |
| DOI | 10.3969/j.issn.1671-7775.2017.01.011 |
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| Abstract | 为了测试不同状态下航天器各活动部件在低频及超低频区的6维微振动表现,设计了一种以压电传感器为核心的6维微振动力测试系统.通过标定及对软件的设计实现了传感器信号在空间上的实时采集、分析及处理等功能,并最终得到空间6维力.介绍了该测试系统的工作原理和动态标定方法,对该测试台进行了仿真及测试试验.结果表明,固有频率的仿真与试验结果前5阶的相对误差在5%以内,1阶频率大于400Hz;力及力矩分辨率分别可达到0.1N及0.01N·m（SNR大于10）;在频域上0-400Hz范围内,该测试系统各通道的相对误差在7%以内. |
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| AbstractList | O329; 为了测试不同状态下航天器各活动部件在低频及超低频区的6维微振动表现，设计了一种以压电传感器为核心的6维微振动力测试系统．通过标定及对软件的设计实现了传感器信号在空间上的实时采集、分析及处理等功能，并最终得到空间6维力．介绍了该测试系统的工作原理和动态标定方法，对该测试台进行了仿真及测试试验．结果表明，固有频率的仿真与试验结果前5阶的相对误差在5％以内，1阶频率大于400 Hz；力及力矩分辨率分别可达到0．1 N及0．01 N·m（SNR大于10）；在频域上0～400 Hz范围内，该测试系统各通道的相对误差在7％以内． 为了测试不同状态下航天器各活动部件在低频及超低频区的6维微振动表现,设计了一种以压电传感器为核心的6维微振动力测试系统.通过标定及对软件的设计实现了传感器信号在空间上的实时采集、分析及处理等功能,并最终得到空间6维力.介绍了该测试系统的工作原理和动态标定方法,对该测试台进行了仿真及测试试验.结果表明,固有频率的仿真与试验结果前5阶的相对误差在5%以内,1阶频率大于400Hz;力及力矩分辨率分别可达到0.1N及0.01N·m（SNR大于10）;在频域上0-400Hz范围内,该测试系统各通道的相对误差在7%以内. |
| Abstract_FL | In order to test the spacecraft microvibration performance under different conditions at low and ultralow frequency,a six-dimension microvibration test system was designed with piezoelectric sensor as core.The software was designed to realize real-time acquisition analysis and sensor signals processing in space with calibration,and the six-dimension force was obtained at last.The working principle and the dynamic calibration method of test system were introduced,and the test system was also simulated and tested.The results show that the relative error of the first five natural frequencies is within 5%,and the first order is more than 400 Hz.The test resolution of force and torque can respectively reach 0.1 N and 0.01 N·m with SNR more than 1 0.The relative error of six components is within 7%in dynamic testing at the frequency range of 0 to 400 Hz. |
| Author | 夏明一 秦超 贺帅 |
| AuthorAffiliation | 中国科学院长春光学精密机械与物理研究所,吉林长春130033 |
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| Author_FL | HE Shuai QIN Chao XIA Mingyi |
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| Author_xml | – sequence: 1 fullname: 夏明一 秦超 贺帅 |
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| Keywords | 动态标定 空间微振动 有限元分析 space microvibration software design piezoelectric sensor 软件设计 dynamic calibration finite element analysis 压电传感器 |
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| Notes | XIA Mingyi, QIN Chao, HE Shuai（Changchun Institute of Optics , Fine Mechanics and Physics , Chinese Academy of Science , Changchun , Jilin 130033 , China） 32-1668/N In order to test the spacecraft microvibration performance under different conditions at low and ultralow frequency,a six-dimension microvibration test system was designed with piezoelectric sensor as core.The software was designed to realize real-time acquisition analysis and sensor signals processing in space with calibration,and the six-dimension force was obtained at last.The working principle and the dynamic calibration method of test system were introduced,and the test system was also simulated and tested.The results show that the relative error of the first five natural frequencies is within 5%,and the first order is more than 400 Hz.The test resolution of force and torque can respectively reach 0.1 N and 0.01 N·m with SNR more than 1 0.The relative error of six components is within 7%in dynamic testing at the frequency range of 0 to 400 Hz. s |
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| SubjectTerms | 动态标定 压电传感器 有限元分析 空间微振动 软件设计 |
| Title | 航天器6维微振动力测试系统的设计与试验 |
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