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

A technology for solar cell arrays and load conditions, applied in electrical digital data processing, special data processing applications, instruments, etc., can solve problems such as failure of locking motors

CN109522622AActive Publication Date: 2019-03-26CHINA ACAD OF LAUNCH VEHICLE TECH
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Publication Date
2019-03-26

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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.
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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...

Examples

Embodiment Construction

[0076] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0077] like figure 1 Shown is the flow chart of the method for determining the on-orbit load condition of a multi-degree-of-freedom solar cell array in the present invention. It can be seen from the figure that the method for determining the on-orbit load condition of a multi-degree-of-freedom solar cell array includes the following steps:

[0078] Step (1), based on solar cell array structure, mechanism scheme, quality characteristics, adopt finite element software to establish the finite element model of solar cell array; Adopt MSC.Nastran software to establish the finite element of solar cell array in an optional embodiment of the present invention Model, the established finite element model includes the solar cell array sail model simulated by shell elements and the solar cell array structure simulated by beam elements, and also includes the...