A sun-tracking solar array is an effective solution to the increasing energy demand of spacecrafts. However, the driving torque fluctuation of the solar array driving assembly (SADA) and its oscillatory motion lead to the micro-vibration problem of the spacecraft. In this article, a disturbance torque model of the sun-tracking solar array, which takes its friction and flexibility into consideration, is established. Furthermore, a test platform was built to measure the disturbance force/torque, and a solar array simulator (SAS) was designed to replace the solar array in the ground experiments. Finally, the disturbance torque of the SADA-driven SAS is simulated, and the model is validated by comparing the simulation results with the experimental results. These results show that the frequency error of the model is less than 0.648%, and the amplitude error of the corresponding frequency is less than 22.33%, which indicates that the proposed model can effectively predict the disturbance torque generated by the sun-tracking solar array in orbit. The research provides theoretical guidance for the system optimization design and micro-vibration suppression of spacecrafts.

Body-mounted solar panels are extensively utilized in satellite construction due to their simple structure and robust vibration resistance. The quantity and arrangement of support points on the body-mounted solar panel significantly affect its natural frequency. Thus, the design of these support points is a crucial aspect of the design process for body-mounted solar panels. This study presents a method for determining the support points of body-mounted solar panels, enabling rapid and precise identification of the quantity and positioning of these points based on the stated natural frequency in the design. First, a new algorithm is proposed, based on the finite element method, to optimize the positioning of support points on the body-mounted solar panel without the need for remeshing. Utilizing this algorithm, the distinct impacts of support point positioning and stiffness on the natural frequency of the solar panel are investigated, and the practical principles are proposed for quickly and accurately identifying the optimal locations of support points to maximize the natural frequency of the solar panel, given a predetermined number of support points. Subsequently, based on Courant–Fischer’s theorem, a method to ascertain the least quantity of support points through two modal analyses is presented. By integrating the aforementioned principles and method, a two-step procedure for identifying the quantity and positioning of support points is developed. Ultimately, the proposed two-step procedure is implemented in the design of the solar panel of the Jilin-1XXX satellite. The modal test reveals that the natural frequency of the solar panel surpasses the design index criteria, hence validating the efficacy and feasibility of the optimal design technique for the support points of the body-mounted solar panel presented in this study.

The ground modal test is an important approach to the natural frequency of solar arrays to support the attitude control of spacecraft. However, for the batch production of small satellites, the accuracy and efficiency of traditional ground modal testing methods are limited. This shortcoming restricts the development of satellite constellations. Based on the encapsulation method widely used in the computer field, this paper proposed a natural frequency identification method of deployable solar arrays with multiple plates. This method is of high accuracy and efficiency that meets the demand of attitude control and makes sense to accelerate the batch production of small satellites. First, a suspended modal test system with gravity compensation function is designed. Second, the mathematical model of the test system is established. Abstracting parts of the parameters of the test object into an encapsulated entity, the mathematical model is simplified by equivalent variables. Thus, the direct mapping relationship between the ground test result and the true natural frequency is proposed. Finally, to verify the identification accuracy, finite element analysis (FEA) and the ground modal test of a two‐folder solar array simulant are carried out. The results show that the relative error of the first‐order natural frequency after correction and the theoretical value is less than 3%. Meanwhile, the identification accuracy of the ground modal test is improved by more than 50%. This method improves the availability of ground test results and reduces the calculation amount, so that it is convenient for engineering applications.