method and a system for determining the on-orbit load condition of a solar cell array with multiple degrees of freedom
The invention relates to a method and a system for determining the on-orbit load condition of a solar cell array with multiple degrees of freedom. Firstly, a finite element model of the solar cell array is established by using a finite element software. The mass matrices of all finite element nodes...
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| creator | CAO XIAORUI MAN YIMING HUANG XIYUAN ZHANG CHUNYANG YANG YONG ZHOU ZHENGYANG ZHANG HUASHAN CHEN HONGBO LI XIAOYAN XIE JING WANG GUOQING SUN GUANG ZHU YONGGUI ZHANG JIAXIONG |
| description | The invention relates to a method and a system for determining the on-orbit load condition of a solar cell array with multiple degrees of freedom. Firstly, a finite element model of the solar cell array is established by using a finite element software. The mass matrices of all finite element nodes in the rotating part of the solar array and the coordinate matrices in the local coordinate system of the rotating point are obtained from the finite element model. The finite element software is used to analyze the dynamic characteristics of the finite element model, and the modal frequencies and modal shapes of the model are extracted. According to the on-orbit dynamic model of the spacecraft with flexible solar array, the dynamic simulation is carried out according to the on-orbit mission conditions of the spacecraft, and the modal coordinates, acceleration, angular acceleration and angular velocity of the spacecraft are obtained. Elasticity method and Hooke method are used to calculate joint torque respectively |
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Firstly, a finite element model of the solar cell array is established by using a finite element software. The mass matrices of all finite element nodes in the rotating part of the solar array and the coordinate matrices in the local coordinate system of the rotating point are obtained from the finite element model. The finite element software is used to analyze the dynamic characteristics of the finite element model, and the modal frequencies and modal shapes of the model are extracted. According to the on-orbit dynamic model of the spacecraft with flexible solar array, the dynamic simulation is carried out according to the on-orbit mission conditions of the spacecraft, and the modal coordinates, acceleration, angular acceleration and angular velocity of the spacecraft are obtained. 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Firstly, a finite element model of the solar cell array is established by using a finite element software. The mass matrices of all finite element nodes in the rotating part of the solar array and the coordinate matrices in the local coordinate system of the rotating point are obtained from the finite element model. The finite element software is used to analyze the dynamic characteristics of the finite element model, and the modal frequencies and modal shapes of the model are extracted. According to the on-orbit dynamic model of the spacecraft with flexible solar array, the dynamic simulation is carried out according to the on-orbit mission conditions of the spacecraft, and the modal coordinates, acceleration, angular acceleration and angular velocity of the spacecraft are obtained. 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Firstly, a finite element model of the solar cell array is established by using a finite element software. The mass matrices of all finite element nodes in the rotating part of the solar array and the coordinate matrices in the local coordinate system of the rotating point are obtained from the finite element model. The finite element software is used to analyze the dynamic characteristics of the finite element model, and the modal frequencies and modal shapes of the model are extracted. According to the on-orbit dynamic model of the spacecraft with flexible solar array, the dynamic simulation is carried out according to the on-orbit mission conditions of the spacecraft, and the modal coordinates, acceleration, angular acceleration and angular velocity of the spacecraft are obtained. Elasticity method and Hooke method are used to calculate joint torque respectively</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | CALCULATING COMPUTING COUNTING ELECTRIC DIGITAL DATA PROCESSING PHYSICS |
| title | method and a system for determining the on-orbit load condition of a solar cell array with multiple degrees of freedom |
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