KEYWORDS: Satellites, Data analysis, Vibration, Design and modelling, Data storage, Data conversion, Data acquisition, Control software, Vibration control, Software development
In order to solve the problem of consuming a lot of time in data analysis, condition formulation and summary report compilation of satellite mechanics test, a set of software for data analysis of satellite mechanics test was developed. Firstly, the system framework is constructed from the process of satellite vibration test. Then, the functions of the software are divided by sorting out each link of the test data analysis. In addition, according to the flow of data in the test, design the engineering data structure. Finally, combined with the characteristics of data interaction and convenient use of the software, a general module of the software is constructed.
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 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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