In order to improve the fatigue evaluation system of the satellite in the transportation environment, a fatigue analysis method of satellite transportation environment based on the digital twin was explored in this paper. At first, the basic theories and method of fatigue analysis are introduced in detail. The fatigue damages of the satellite in the transportation environment are evaluated by using the random vibration and sinusoidal vibration stress fatigue analysis separately. And then, digital twin fatigue models based on the acceleration response of random vibration and sinusoidal vibration are established. Finally, fatigue models are utilized to analyze the fatigue damage to the satellite in the transportation environment and are compared with the stress fatigue models before. The results show that all the fatigue damage keeps in accordance with each other verifying the accuracy of the fatigue model based on the digital twin presented in this paper.
In order to further improve the measurement precision of the star sensor and solve the problem on displacement field construction for on-orbit star sensor mounting bracket. In this paper, star sensor mounting bracket is simplified, and the theoretical formula on the displacement field of the star sensor mounting bracket is constructed based on beam bending theory, curvature recursive method and the least square method. Secondly, fiber Bragg grating sensors are embedded in the key nodes of the star sensor mounting bracket, and the strain of the star sensor mounting bracket is measured by the static test. Then, the displacement field of the star sensor mounting bracket is constructed based on the strain test data, and combined with the theoretical formula for the displacement field. Finally, comparing the measured data of displacement mete with the constructed displacement field values and static simulation results, the feasibility and accuracy of the method on constructing the displacement field of star sensor mounting bracket by using embedded fiber Bragg grating for strain monitoring is further verified.
In order to formulate accurate and reasonable random vibration test conditions for optical cameras and solve the problem of conservative design of test conditions caused by inaccurate simulation calculation, this paper proposes a general method for the design of random vibration specification for small satellites’ optical cameras. First, we derive the dynamic response formula, which lays a foundation for the small satellite dynamic simulation calculation. Then, the response of the optical camera mounting surface, which is obtained by the dynamic calculation of the small satellite finite element model, and the random vibration test conditions of the camera process is enveloped to obtain the preliminary random vibration test condition of the new research optical camera. Subsequently, we combine the random vibration test data of the optical remote sensing satellite, which has been used in orbit, and revise the preliminary random vibration test conditions of the new research camera in terms of response magnitude and frequency. Finally, we verify the rationality of this method through random vibration test of a small satellite. This scheme is conducive to the establishment of more reasonable and feasible random vibration test conditions for small satellites’ optical cameras, which is beneficial to the development and production of optical cameras.
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