摘要
为准确测量某卫星平台真实飞行过程发射主动段结构动力学响应及入轨阶段星板结构微振动特性,设计了一种新型MEMS振动测量系统,综合实现对卫星主动段及在轨阶段振动特性测量。针对卫星发射主动段振动冲击大、频谱范围宽且入轨段振动信号振幅和频率较低的特点,测量系统采用了大量程宽带压电式加速度计,以及国产MEMS加速度计和陀螺仪集成设计方案。卫星主动段各关键时段及在轨段各测量工况下的时域和频域冲击振动分析结果表明:测量系统压电加速度计、MEMS加速度计和MEMS陀螺仪均工作正常,测试数据完整有效,测量精度满足卫星结构动力学分析要求,输出结果符合指标要求,已具备产品化条件,具有广阔的应用前景。
In order to measure the structural dynamic responses in the powered-flight phase and the micro vibration characteristics of the spacecraft structural slab in the orbital injection phase with high precision,a novel MEMS vibration response testing system is designed.In view of the strong vibration shock and the wide spectrum of the vibration signal in the powered-flight phase,as well as the small amplitudes and low-frequency of the vibration signal in the orbital injection phase,an integrated design composed of a high-capacity piezoelectric accelerometer,a domestic MEMS accelerometer and a MEMS gyroscope is implemented,which can synthetically measure the structural dynamic responses and the micro vibration characteristics.The vibration response analyses both in the time domain and the frequency domain for the spacecraft motion,show that the system work normally with complete and effective measurement data of adequate accuracy,satisfactory for the related requirements.Besides,the system is already technically-mature to become a product for further applications.
作者
庄海孝
张晓鹏
曹燕
何宗波
左苗
ZHUANG Haixiao;ZHANG Xiaopeng;CAO Yan;HE Zongbo;ZUO Miao(Beijing Institute of Spacecraft System Engineering;Beijing Institute of Spacecraft Environment Engineering;Beijing Spacecrafts:Beijing 100094,China)
出处
《航天器环境工程》
2019年第1期76-82,共7页
Spacecraft Environment Engineering
基金
国家国防科工局民用航天预研基金项目(编号:D040202)
关键词
航天器
主动段
入轨段
振动特性
测量系统
spacecraft
powered-flight phase
orbit injection phase
vibration response
measurement system
