Research on the method of formulating test conditions for triaxial vibration of satellite structures

Abstract Satellite vibration testing plays a critical role in ensuring their structural integrity and reliable performance in the demanding space environment. However, current single-axis separate loading methods fail to accurately replicate the real-world multi-axis vibration conditions, leading to unrealistic approximations and compromising the testing process. To simulate the real satellite vibration environment and shorten the development cycle, this paper proposes an equivalent formulation method for satellite triaxial vibration test conditions. Finite element analysis technology is employed to conduct uniaxial simulation analysis. Based on the results of these simulations and the principle of maximum response envelope, the problem is transformed into a mathematical optimization problem. Global optimization algorithms are introduced to build the optimization process and realize the rational formulation of triaxial test conditions. The proposed methodology is given in detail, and an engineering example is provided to demonstrate its application. Furthermore, the results are discussed, substantiating the validity and reasonability of the developed methodology.