Abstract
An improved method based on the Hybrid Finite Element-Statistical Energy Analysis (FE-SEA) method and quasi-steady state theory is proposed to predict the response of spacecraft structure during the process of pyrotechnics separation. Firstly, the amplitude–frequency value of shock load is obtained by using time-frequency conversion technology. Then, according to the frequency response characteristics of each part of the spacecraft structure, a more accurate hybrid FE-SEA model is established. The piecewise loading method is used to predict the response of the hybrid model. Finally, the time domain response results are reconstructed, and the shock response spectrum (SRS) is calculated. Based on the test system of simulating pyroshock, the shock experiment of spacecraft structure is conducted. The high frequency and high velocity character of pyroshock could be effectively simulated, and an accurate shock force function could be obtained through the experiment. This indicates that the numerical results are in line with the ones of the experiment. The SRS obtained from experiments and calculations have similar trends and amplitudes. This conclusion verifies the rationality and sufficient accuracy of the novel method in this paper. The novel method presented in this paper greatly improves the computational efficiency. At the same time, it provides theoretical guidance for shock response prediction of spacecraft structure by steady-state methods.
Highlights
The shock environment exists widely in aerospace engineering
A more accurate and applicable prediction method of the shock response based on the hybrid Finite Element-Statistical Energy Analysis (FE-SEA) method is presented in this paper
The shock response of the loading plate and the response plate of the spacecraft structure are obtained by the hybrid FE-SEA method
Summary
The shock environment exists widely in aerospace engineering. A high-frequency transient shock load will occur during the initiating process of a pyrotechnics device. The transient statistical energy analysis (TSEA), the finite element method, the local phase information reconstruction (LMPR), and the virtual mode synthesis (VMSS) were utilized to calculate the transient shock response of the structure. A compared shock experiment the typical spacecraft to the rationality and sufficient with theforfinite element method structure and other transient response prediction accuracy of the novel method is carried this paper. The research in thismethods, paper canthe better predict structures reasonably calculated, and the computational is greatly improved the shockare response of system level spacecraft structure andefficiency shorten the development cycle byofour method. The research in this paper can better predict the shock response of system the spacecraft It provides a basis for the application of the steady-state method to shock level spacecraft structure and shorten the development cycle of the spacecraft. A basis for the application of the steady-state method to shock problems
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