Thermal-structural analysis for an attitude maneuvering flexible spacecraft under solar radiation

Liu, Lun; Cao, Dengqing; Huang, Hua; Shao, Chonghui; Xu, Yuqian

doi:10.1016/j.ijmecsci.2017.03.028

Cited by 43 publications

(14 citation statements)

References 22 publications

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“…The performance requirements of a spacecraft's mission could be assessed at the earliest stages of design through the development of mathematical models and deployment of computational tools. Recent advances in computer hardware and software have enabled to reduce the computational burden associated with the numerical integration of the high-fidelity equations governing the heat transfer of the aforementioned systems [2,9,26]. Software tools can be deployed to assist the design process and provide guidelines to enable enhanced operability of spacecraft.…”

Section: Heat Transfer Modeling Of a Rotating Spacecraft Under Solar mentioning

confidence: 99%

“…In general, it is considered that the satellite has a pitch angle rotation maneuver due to the severe solar radiation during daytime transition. Modeling of the thermal behavior is then associated with heat radiation effects and thermally-induced vibration may exist at the high temperature gradients [25,26]. Therefore, a coupled-thermal structural analysis for an altitude maneuvering under solar thermal loading and maneuvering dynamics is very important in the analysis.…”

Section: Introductionmentioning

confidence: 99%

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Modeling and Thermal Analysis of a Moving Spacecraft Subject to Solar Radiation Effect

et al. 2019

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The impact of solar radiation on spacecraft can increase the cooling load, degrade the material properties of the structure and possibly lead to catastrophic failure of their missions. In this paper, we develop a computational model to investigate the effect of the exposure to solar radiation on the thermal distribution of a spacecraft with a cylindrical shape which is traveling in low earth orbit environment. This is obtained by the energy conservation between the heat conduction among the spacecraft, the heating from the solar radiation, and the radiative heat dissipation into the surroundings while accounting for the dynamics of the space vehicle (rotational motion). The model is solved numerically using the meshless collocation point method to evaluate the temperature variations under different operating conditions. The meshless method is based on approximating the unknown field function and their space derivatives, by using a set of nodes, sprinkled over the spatial domain of the spacecraft wall and functions with compact support. Meshless schemes bypass the use of conventional mesh configurations and require only clouds of points, without any prior knowledge on their connectivity. This would relieve the computational burden associated with mesh generation. The simulation results are found in good agreement with those reported in previously-published research works. The numerical results show that spinning the spacecraft at appropriate rates ensures low and uniform temperature distribution on the spacecraft, treated as thick-walled object of different geometries. Therefore, this would extend its lifetime and protect all on-board electronic equipment needed to accomplish its mission.

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Section: Heat Transfer Modeling Of a Rotating Spacecraft Under Solar mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Modeling and Thermal Analysis of a Moving Spacecraft Subject to Solar Radiation Effect

et al. 2019

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“…[1][2][3][4][5] In addition to mechanical properties, the cellular solids with unified microstructure have functional properties (such as thermal insulation, sound absorption, and invisibility) and have been extensively explored by numerous scholars. [6][7][8][9] Extension for the applications of intelligent materials, bio-mimetic materials, and composites and advances in industrial technologies (such as freeze-cast, additive manufacturing, and nanotechnology) have recently made the trend that combining emerging materials with porous structures to develop functional metamaterials with certain mechanical properties. 10,11 Lurie et al 12,13 performed theoretical analysis and numerical simulation in order to optimize the microstructure variables of the corrugated-core sandwich panels; thermal barrier skins with best combinations of the thermal and mechanical performances under extreme temperature conditions were designed.…”

Section: Introductionmentioning

confidence: 99%

Assessment on speed and amplitude of elastic wave propagation in square-packed circular honeycombs

Zhang

Liu

2020

The Journal of Strain Analysis for Engineering Design

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In contrast to the dynamic response characteristics, few propagation characteristics of elastic waves have been described on cellular materials, to date. In view of the development trend of emerging metamaterials on multi-functional, detailed characterization of elastic wave in honeycombs becomes an important task in order to assess their performances. This study investigates the propagation characteristics of elastic wave in square-packed circular honeycombs through combining theoretical analysis and numerical simulation. We also establish a one-dimensional circular chain model to discuss the influence mechanism of impact velocities, material parameters, and structural parameters on the elastic wave propagation characteristics in square-packed circular honeycombs. The influence relations are quantified and a semi-empirical theoretical expression for assessing characterization is presented, which extends theory of elastic wave propagation speed from solid materials to square-packed circular honeycombs. The assessment equation fully describes the elastic wave propagation speed and stress amplitude variation with location during propagation in square-packed circular honeycombs, and the results are consistent with the experimental data from the literature. The findings herein are aimed at providing an assessment equation with simple form for engineering applications easily and providing theoretical basis for elastic wave control and multi-functional combination design of metamaterials.

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“…T HE uncoupled and coupled thermal-structural analysis models have been employed extensively to study thermally induced vibrations of spacecraft appendages [1][2][3][4][5]. The uncoupled model assumes that the absorbed solar flux for the structure surface is not affected by thermally induced motions (i.e., neglecting the coupling effect between structural deformations and incident heating); however, the coupled model includes the effect [1].…”

Section: Introductionmentioning

confidence: 99%

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

Shen

2019

AIAA Journal

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Thermal-structural analysis for an attitude maneuvering flexible spacecraft under solar radiation

Cited by 43 publications

References 22 publications

Modeling and Thermal Analysis of a Moving Spacecraft Subject to Solar Radiation Effect

Modeling and Thermal Analysis of a Moving Spacecraft Subject to Solar Radiation Effect

Assessment on speed and amplitude of elastic wave propagation in square-packed circular honeycombs

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

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