Method and a system for determining the on-orbit load condition of a solar cell array with multiple degrees of freedom

Abstract

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, and the consistency of joint torque is obtained by comparing the two methods. If the calculation is correct, the maximum absolute value of joint torque can be obtained, and the load condition of solar array can be obtained, so as to ensure the reliability of the on-orbit mission of the vehicle.

Description

technical field [0001] The present invention relates to a method and system for determining the on-orbit load condition of a multi-degree-of-freedom solar cell array, in particular to a method and system for determining the on-orbit load condition of a multi-degree-of-freedom solar cell array considering elastic vibrations, belonging to aerospace vehicle structures The field of load and mechanical environment. Background technique [0002] Solar cell arrays rely on large-area and light-weight wings to reflect sunlight to obtain energy, which is an important guarantee for long-term on-orbit operation and mission execution of aircraft. Therefore, large-flexible solar cell array aircraft has become a research hotspot in the aerospace field in recent years. . The solar cell array has the structural characteristics of large area, low stiffness, and small damping, which lead to complex dynamic characteristics. Once the low-order modes are excited by external disturbance torque, i...

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Problems solved by technology

[0004] The purpose of the present invention is to overcome the above-mentioned deficiencies in the prior art, and provide a method and system for determining the on-orbit load condition of a multi-degree-of-freedom solar cell array, aiming at the elasticity caused by the multi-degree-of-freedom solar cell array under the interference force of the aircraft attitude control engine Vibration, which may lead to the failure of the locking motor, sort out the working mode of the aircraft in orbit, and based on the dynamics model, carry out the dynamics simulation to obtain the attitude motion information and generalized coordinates of the solar wing aircraft, and conduct the analysis and research of the rigid body and elastic load of the solar array joints, Guide solar cell array structure and mechanism design

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