Thermal-structural analysis of large space structures - An assessment of recent advances

Thornton, Earl A.; Paul, Donald B.

doi:10.2514/3.25761

Cited by 50 publications

(29 citation statements)

References 13 publications

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“…The thermally-induced bending moment of the flexible structure by sunlight heating produces initial thermal deflection, accompanied by fluctuating moment due to periodic changes of sunlight incidence angle, causing oscillation. Therefore the spacecraft structure can be vibrated due to this periodic change of thermally-induced moment [1,2,3].…”

Section: Introductionmentioning

confidence: 99%

Study on Comparison of Atmospheric and Vacuum Environment of Thermally-Induced Vibration Using Vacuum Chamber

Kong¹,

Park²,

Lee³

2010

International Journal of Aeronautical and Space Sciences

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The present paper studies the thermally-induced vibration phenomenon of the flexible space boom structure. In order to simulate the thermally-induced vibration phenomenon of the flexible thin boom structure of the spacecraft with the attached tip mass in space, the thermally-induced vibration including thermal flutter is experimentally investigated at various thermal environments using a heating lamp in vacuum chamber. In this experimental study, fluctuating characteristics, natural frequency and thermal strains of the thermally-induced vibration are parametrically investigated at various thermal environment conditions. Finally the thermally-induced vibration of the flexible boom structure of the orbiting earth satellite in solar radiation environment from the earth eclipse region including umbra and penumbra is simulated using the power control of the heating lamp in the vacuum chamber.

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Section: Introductionmentioning

confidence: 99%

Study on Comparison of Atmospheric and Vacuum Environment of Thermally-Induced Vibration Using Vacuum Chamber

Kong¹,

Park²,

Lee³

2010

International Journal of Aeronautical and Space Sciences

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“…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]. The control of the thermoelastic distortion within small tolerances required careful consideration of the thermo-structural effect [5].…”

mentioning

confidence: 99%

“…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%

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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“…1) As spacecraft missions become more sophisticated, the requirements for dimensional stability naturally become more stringent.…”

Section: Introductionmentioning

confidence: 99%

Telescope Co-Alignment Design and Its Performance On-Orbit of Solar Observational Satellite ``Hinode''

Minesugi

Inoue

Tabata

et al. 2013

Trans. Japan Soc. Aero. S Sci.

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The three telescopes on Hinode, a highly sophisticated solar observational satellite, must be able to simultaneously observe the same point on the sun in order to ascertain data on the physical mechanisms for activity and heating in the solar atmosphere. To fulfill this mission requirement, the telescopes must remain co-aligned to within 2.0 arcsec under the temperature fluctuations the satellite experiences while orbiting the earth. Hinode consists of two modules and a connecting structure. Most of the structural elements are made of CFRP in order to suppress thermal deformations. In particular, the laminate configuration of the CFRP in the module holding the telescopes was carefully designed in terms of not only its stiffness and strength but also its coefficient of thermal expansion and thermal conductivity. A thermal deformation analysis was performed to estimate the co-alignment drift on-orbit and a thermal deformation test was conducted to verify the estimation. The results showed that the structural design would sufficiently suppress the drift on-orbit. Measurements on-orbit were conducted using the image of the sun, and the measured drift was in good agreement with the estimation.

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Thermal-structural analysis of large space structures - An assessment of recent advances

Cited by 50 publications

References 13 publications

Study on Comparison of Atmospheric and Vacuum Environment of Thermally-Induced Vibration Using Vacuum Chamber

Study on Comparison of Atmospheric and Vacuum Environment of Thermally-Induced Vibration Using Vacuum Chamber

Thermo-structural analysis of space structures using Fourier tube elements

Telescope Co-Alignment Design and Its Performance On-Orbit of Solar Observational Satellite ``Hinode''

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