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

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TLDR
In this paper, a coupled thermal-structural analysis for an attitude maneuvering spacecraft under solar radiation is conducted and the interaction between the thermally induced vibration and attitude maneuver is studied.
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This article is published in International Journal of Mechanical Sciences.The article was published on 2017-06-01. It has received 35 citations till now. The article focuses on the topics: Reaction wheel & Spacecraft.

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Citations
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Journal ArticleDOI

Rigid-flexible-thermal analysis of planar composite solar array with clearance joint considering torsional spring, latch mechanism and attitude controller

TL;DR: Results of six comparison models show that the coupling effect of thermal environment and overall motion brings dramatic and unmanageable shock to the system with clearance joint, that is no longer can be seen as a simple superposition of each single condition effect like theSystem with ideal joint.
Journal ArticleDOI

Dynamic characteristics of flexible spacecraft with double solar panels subjected to solar radiation

TL;DR: In this paper, the dynamic characteristics of a flexible spacecraft with double solar panels are studied comprehensively for attitude motion, structural deformation and thermal loading, and coupled thermal-structural analyses are carried out by interactively solving the system's dynamic equations and the heat conduction equations with a two-way coupled approach.
Journal ArticleDOI

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

TL;DR: In this article, the authors show that thermal 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, cycli...
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Thermal alternation induced vibration analysis of spacecraft with lateral solar arrays in orbit

TL;DR: In this article, a rigid-flexible-thermal coupling dynamic analysis for a spacecraft in orbit is studied, which consists of a central rigid platform and two groups of lateral solar arrays.
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Semi-active vibration control of two flexible plates using an innovative joint mechanism

TL;DR: The low frequency vibration of flexible appendages system can be attenuated robustly, which verifies the effectiveness of this semi-active technique of joint variable stiffness control, and the natural frequency of the system varies subsequently.
References
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Book

Cellular Solids: Structure and Properties

TL;DR: The linear elasticity of anisotropic cellular solids is studied in this article. But the authors focus on the design of sandwich panels with foam cores and do not consider the properties of the materials.
Journal ArticleDOI

Partitioned analysis of coupled mechanical systems

TL;DR: This is a tutorial article that reviews the use of partitioned analysis procedures for the analysis of coupled dynamical systems using the partitioned solution approach for multilevel decomposition aimed at massively parallel computation.
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Studies on Fluid-Thermal-Structural Coupling for Aerothermoelasticity in Hypersonic Flow

TL;DR: In this paper, the tradeoff between computational cost and accuracy is evaluated for aerothermoelastic analysis based on either quasi-static or time-averaged dynamic fluid-thermal-structural coupling, as well as computational fluid dynamics based reduced-order modeling of the aerodynamic heat flux.
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Thermally induced bending vibrations of a flexible rolled-up solar array

TL;DR: In this paper, an analytical approach for determining the thermal-structural response of a flexible rolled-up solar array due to a sudden increase in external heating is developed, and the analytical methods identify key parameters for understanding the static and dynamic response.
Journal ArticleDOI

Solar-array-induced disturbance of the Hubble Space Telescope pointing system

TL;DR: In this paper, the authors investigated the vibrational disturbances of the Hubble Space Telescope that were discovered soon after deployment in orbit, and found that the disturbances were particularly evident during orbital day-night crossings, and that the magnitude of the disturbances was considerably larger than the design jitter requirement.
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