Zhenxing Shen

Yanshan University

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Gengkai Hu

Mongolian University of Science and Technology

Huijian Li

King Fahd University of Petroleum and Minerals

Xiaoning Liu

BOE Technology Group (China)

Shengwang Hao

Yanshan University

Xiaofeng Xing

Yanshan University

Rujin Han

Technology and Engineering Center for Space Utilization

Cheng Liu

Georgia Institute of Technology

Boyu Li

Beijing University of Technology

Pei Li

Wenzhou University

Zihao Yuan

China University of Petroleum, Beijing

Cooperative Institutions

Chinese Academy of Sciences

Technology and Engineering Center for Space Utilization

University of Chinese Academy of Sciences

Beijing Institute of Technology

Yanshan University

Dalian University of Technology

Aerospace Technology Institute

Ministry of Industry and Information Technology

China University of Petroleum, Beijing

Seoul National University

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Thermal shock induced dynamics of a spacecraft with a flexible deploying boom

Acta Astronautica (2017)

Zhenxing Shen Huijian Li Xiaoning Liu Gengkai Hu

Multibody system

10.1016/j.actaastro.2017.10.004

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Citations (34)

THERMALLY INDUCED VIBRATIONS OF SOLAR PANEL AND THEIR COUPLING WITH SATELLITE

International Journal of Applied Mechanics (2013)

Zhenxing Shen Gengkai Hu

A coupled thermal-structural model of a laminated composite plate is proposed by using the absolute nodal coordinate formulation, the transverse shear and normal deformations through element thickness are included. The dynamic equations of structure are established by applying the d'Alembert's principle and then solved numerically to determine dynamic responses and transient heat conduction in the structure due to the nonlinear elastic force and thermal radiation. A cantilevered flexible solar panel subjected suddenly to a solar radiation is examined, it is found that by considering the coupling between the thermal and structural responses, thermal flutter of the composite panel can be well predicted. The coupled behavior of the composite solar panel with a satellite is also analyzed by idealizing it as a rigid-flexible multibody system in the low earth orbit, in which a natural coordinate formulation is established to analyze the attitude of the satellite rigid hub, the thermal snap phenomenon is also well predicted.

Flutter

10.1142/s1758825113500312

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Citations (35)

A new thin beam element with cross-section distortion of the absolute nodal coordinate formulation

Proceedings of the Institution of Mechanical Engineers Part C Journal of Mechanical Engineering Science (2021)

Zhenxing Shen Xiaofeng Xing Boyu Li

A novel modelling approach to beams with thin cross-sections is proposed in the absolute nodal coordinate formulation (ANCF), where the Lagrange interpolating and curve fitting techniques of numerical analysis are utilized for construction of the thin beam cross-section contour. Although the slope vector with respect to the coordinate line on cross-section contour is not considered in nodal coordinates, the cross-section distortion could be adequately captured through selecting an appropriate degree of polynomial. The main advantages of the present ANCF thin beam element are that the computational costs are more inexpensive than the ANCF shell element due to less generalized coordinates, there is very small amount of input data because slope vectors of the cross-section are eliminated, and the cross-sectional stress distribution may always be continuous on account of the fact that the cross-section is not discretized into a set of finite elements. Moreover, the formulations of elastic forces and Jacobian of thin laminated composite beam are also derived based on the continuum mechanics. Finally, several examples including both static and dynamic problems are performed to verify the new element and meanwhile demonstrate its general characteristics.

Distortion (music)

10.1177/09544062211020046

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Citations (4)

Thermally induced vibrations of flexible beams using Absolute Nodal Coordinate Formulation

Aerospace Science and Technology (2013)

Zhenxing Shen Qiang Tian Xiaoning Liu Gengkai Hu

10.1016/j.ast.2013.04.009

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Citations (112)

Thin-walled composite beam elements via the absolute nodal coordinate formulation

Multibody System Dynamics (2023)

Zhenxing Shen

Hermite interpolation

Image warping

Lagrange polynomial

Interpolation

10.1007/s11044-023-09956-y

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Citations (1)

Thermoelastic–Structural Analysis of Space Thin-Walled Beam Under Solar Flux

AIAA Journal (2019)

Zhenxing Shen Gengkai Hu

Solar Sail

10.2514/1.j057793

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Citations (14)

Cross-sectional zero-dimension temperature model for thin-walled circular tubes in space environment

Thin-Walled Structures (2024)

Zhe Ma Zhenxing Shen

Zero (linguistics)

10.1016/j.tws.2024.112591

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Citations (0)

Thermal-structural dynamic analysis of a satellite antenna with the cable-network and hoop-truss supports

Journal of Thermal Stresses (2019)

Zhenxing Shen Huijian Li Xiaoning Liu Gengkai Hu

Thermally induced structural disturbances of the flexible appendages on a satellite usually occur during eclipse transitions. As a large-scale space structure consists of rod members, cyclic thermal shock induced vibrations such as the divergent thermal flutter may be crucial for its functional serving. In this article, the motivation is to estimate the dynamical behaviors of the AstroMesh antenna under solar flux shock. For this purpose, we developed a numerical approach for the thermal-structural coupling analysis of tensegrity structures considering the pre-stressed state after the form-finding process. The Euler-Bernoulli beam theory, the pre-stressed bar model, and the Fourier thermal element are employed in conjunction with the special consideration on the effect of structural deformations on absorbing solar flux. It is found that, unlike the single boom structure, thermal deformations of the AstroMesh antenna are mainly caused by the temperature variation along rod axis-direction, rather than the temperature gradient on rod cross-section. Besides, the phenomenon of thermally induced vibrations can hardly happen in the AstroMesh antenna.

Thermal shock

Flutter

10.1080/01495739.2019.1649613

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Citations (27)

Viscoelastic analysis of bistable composite shells via absolute nodal coordinate formulation

Composite Structures (2020)

Zhenxing Shen Cheng Liu Huijian Li

Bistability

10.1016/j.compstruct.2020.112537

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Citations (23)