卫星结构基础加速度激励及界面力识别试验研究

针对某卫星结构模型，开展基于实测卫星结构加速度的卫星基础激励和星-箭连接界面动载荷反演试验研究。首先，根据卫星结构和试验条件，设计了用于测量星-箭界面传递载荷的工装；其次，基于卫星结构模态试验和有限元模型修正技术，获取了卫星结构的高保真有限元模型；进一步，开展基础激励下的卫星结构模型振动试验，利用动载荷识别技术获取振动台基础加速度激励并与振动台实测加速度激励对比；最后，将识别的基础加速度激励作用于修正后的卫星结构有限元模型，获取振动台与卫星结构间的界面传递载荷，并与力传感器测量载荷对比完成试验验证。研究表明动载荷识别方法可以为服役状态下的卫星振动载荷环境预测提供技术支持。

Experimental Study on Base Acceleration Excitation and Interface Load Identification on a Satellite Structure

Aiming at the satellite structural model, an experimental study on the inverse analysis of the satellite base excitation and the interface dynamic load between rocket and satellite from measured acceleration response of the satellite structure is conducted. Firstly, a tool for measuring the transfer load on the interface between rocket and satellite is designed according to the satellite structure and experimental condition. Secondly, a high fidelity finite element model of satellite structure is obtained based on the modal test of satellite structure and the finite element model updating technique. Thirdly, vibration test of the satellite structural model under base excitation is carried out, and the base acceleration excitation obtained by the dynamic load identification technique is compared with that measured on the shaking table. Finally, by applying the identified base acceleration excitation on the updated finite element model of satellite structure, the interface transfer load between the shaking table and the satellite structure can be obtained, and then the identified interface load is compared with the measured load from force transducers to accomplish the experimental verification. Research work proves that the dynamic load identification method can provide technical support for the prediction of vibrational environment of satellite during service condition.