Thermally induced bending vibrations of a flexible rolled-up solar array

Thornton, Earl A.; Kim, Yool A.

doi:10.2514/3.25550

Cited by 139 publications

(101 citation statements)

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“…The control of the thermoelastic distortion within small tolerances required careful consideration of the thermo-structural effect [5]. To achieve low weight and high stiffness, thin walled circular tubes are often employed as the main components for large space structures, such as main booms for solar array [1,3,4] and space antenna [6]. An accurate analysis of these structures requires a careful consideration of the thermo-structural responses of thin-walled tubes.…”

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confidence: 99%

“…2 Theory and formulation of Fourier-finite elements for thermal analysis Following the previous analysis [1] that studied the temperature field across the tube cross-section, a Fourier-finite element is presented here for a circular tube consisting of a thin wall. Each node of the element possesses three degrees of freedom: the average temperature and the amplitudes of the cos-and sineshaped perturbation temperatures.…”

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confidence: 99%

“…Several simplified methods have been proposed to analyze the thermally induced deformations, including the analytical method, 2D FEM and conventional beam element analysis. In the analytical method [1][2][3], or 2D FE analysis [7], the temperature gradient in the cross section of the tube was the main factor causing thermal deformation, so that the temperature difference along the tube axis was neglected. In the conventional beam element analysis [3,8], an average temperature was assumed across the cross section without considering temperature gradient.…”

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confidence: 99%

“…In the conventional beam element analysis [3,8], an average temperature was assumed across the cross section without considering temperature gradient. The thermal gradient should be taken into account because it is the main cause of bending of the tube [1].…”

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confidence: 99%

“…The structural response may cause the spacecraft not to function properly. A typical example is the failure of Hubble Space Telescope (HST) because of the thermally induced vibration and buckling of the solar array [1][2][3]. Another example is the thermoelastic distortion of the parabolic antenna, which is the main component of Microwave Radiometer Spacecraft (MRS) and Synthetic Aperture Radar (SAR) [4].…”

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Thermo-structural analysis of space structures using Fourier tube elements

2005

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Space structures consisting of thin walled beams are subjected to incident solar heat flux and emit thermal energy by radiation. An improved thermostructural analysis has been developed taking into account the nonlinear and time-dependent heat conduction and structural response in a circular tube space structure. The tube is modeled using the finite element method in the longitudinal direction, and the temperature gradient in the circumferential direction is predicted based on the Fourier series. The thermal and deflection analyses of a thin-walled tube beam suggests that the Fourier elemental model developed in this study can simulate accurately the thermo-structural behavior of tube structure, which agrees well with the predictions based on a conventional FE analysis and an analytical solution. The thermo-structural analysis of a more complex space parabolic antenna indicates that the Fourier elemental analysis can predict the change in focal length due to solar heat flux more accurately than the conventional FE analysis because of the consideration of the temperature difference in the cross-section of the beam in the Fourier elemental analysis.

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Thermo-structural analysis of space structures using Fourier tube elements

2005

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Spacecraft Structures: Development

Marulo

2012

Wiley Encyclopedia of Composites

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Current spacecraft designs include materials and structural systems engineered to satisfy a variety of requirements, including structural integrity, damage tolerance, radiation protection, debris/micrometeoroid shielding, and thermal insulation. To comply with these different design requirements, composite materials are tailored and designed for specific application and constraint. A survey of the present status of composite materials technology is made with emphasis on materials and applications useful in spacecraft structures. Information is obtained from the open literature, by attendance at meetings and symposia, and from the World Wide Web. Brief discussions of the theory of composite strengthening and reinforcement mechanics are included. Advantages, disadvantages, problem areas, and actual and potential applications are described. The status of testing, processing, forming, fabrication, and joining are noted, and the opportunities offered by employing composite materials for spacecraft applications are described. The advantages as well as the drawbacks behind the use of composites are also listed with specific reference to the space environment. The most critical aspects, which involve the design and the development of a spacecraft are presented with reference to composite materials specifications and guidelines for selection. Next, the characteristics of fiber‐reinforced composite materials are listed. It is shown that composites possess significant advantages over presently used spacecraft structural materials; these include superior strength‐to‐weight and stiffness‐to‐weight ratios, more design freedom and flexibility, improved resistance to crack propagation, and greater potential for improvement of properties. Major problems include lack of uniform test methods, difficulty of joining, high cost, difficulty of fabrication and processing, and lack of information on reliability and reproducibility, particularly for the more advanced composites.

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Thermal flutter analysis of large‐scale space structures based on finite element method

Xiang

Chen

et al. 2006

Numerical Meth Engineering

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SUMMARYDuring the orbital day-night crossing period, the suddenly applied thermal loading is apt to introducing vibration on flexible appendages of large-scale space structures. This kind of thermally-induced vibration is a typical failure of modern spacecrafts. However, owing to the complexity of this problem, many earlier researches study only the vibration of simplified beam models, which can hardly describe the performance of practical structures. This paper aims at using the finite element method to analyse the non-linear vibration of practical thin-walled large-scale space structures subjected to suddenly applied thermal loading. In this study, the coupling effect between structural deformations and the incident normal solar heat flux is considered; the necessary condition of thermally-induced vibration is verified; and the criterion of thermal flutter is established.

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Thermally induced bending vibrations of a flexible rolled-up solar array

Cited by 139 publications

References 2 publications

Thermo-structural analysis of space structures using Fourier tube elements

Thermo-structural analysis of space structures using Fourier tube elements

Spacecraft Structures: Development

Thermal flutter analysis of large‐scale space structures based on finite element method

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