Thermal analysis of a reflective baffle designed for space applications

Beck, T.; Lüthi, Benjamin; Messina, Gabriele; Piazza, Daniele; Seiferlin, K.; Thomas, N.

doi:10.1016/j.actaastro.2011.03.014

Cited by 16 publications

(4 citation statements)

References 8 publications

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“…The solar flux received by a surface is given by q s = Sα eff cos θ (1) where θ is the angle between the solar vector and the normal of the surface, and α eff is the effective solar absorptivity of the anodic surface of solar array. For solar array, the angle θ equals to 0.…”

Section: External Heat Fluxmentioning

confidence: 99%

“…Much research on the thermal analysis and thermal-structure response of solar array and other appendages has been carried out [1,3,4,[7][8][9][10][11]14,15,[17][18][19][20]. Foster and Tinker [4] compared the flight data and computer simulation results of the solar array for Hubble Space Telescope, and pointed out that the source of the disturbances was the thermally driven deformation of the solar arrays in conjunction with frictional effects in the array mechanisms.…”

Section: Introductionmentioning

confidence: 98%

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Thermal analysis of composite solar array subjected to space heat flux

Yan

Cai

2013

Aerospace Science and Technology

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Section: External Heat Fluxmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 98%

Thermal analysis of composite solar array subjected to space heat flux

Yan

Cai

2013

Aerospace Science and Technology

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“…Difficulties were encountered when attempting to use standard thermal modelling software to determine temperatures because the shapes of the surfaces could not be defined accurately enough within the software environment. Detailed analyses were necessary to model the baffles and to correlate the test results [9,10].…”

Section: Baffling and Thermal Controlmentioning

confidence: 99%

The BepiColombo Laser Altimeter (BELA): a post-launch summary

2019

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We provide a brief description of the BepiColombo Laser Altimeter (BELA) experiment for the joint ESA-JAXA mission to Mercury, BepiColombo. The text describes the main elements of the instrument and discusses several of the problems encountered during the instrument development. The actions taken to mitigate the issues are also described and the resulting performance of the instrument as determined by combining ground test data with models of Mercury and the spacecraft orbit is presented. The instrument has met the requirements set in 2005 and should provide a solid data set for the global study of the topography and internal structure of Mercury

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“…Kim and Han (2010) studied the thermal analysis of a fixed type solar array in a low-earth orbit satellite through both an analytical method with a simplified thermal model and a numerical method with a detailed thermal model. Beck et al (2011) presented the implementation and results from thermal mathematical modeling of a Stavroudis-type reflective baffle for space applications. Zhang et al (2014) developed a coupled thermal structural analytical model and its approximate solution.…”

Section: Introductionmentioning

confidence: 99%

Thermoelastic vibration and maneuver control of smart satellites

Fazelzadeh

Azadi

2017

AEAT

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Purpose The purpose of this paper is to analyze and control the thermally induced vibration of orbiting smart satellite panels, which have been modeled as functionally graded material (FGM) beams. Design/methodology/approach It is assumed that the satellite moves in a circular orbit and has pitch angle rotation maneuver. Rapid temperature changes at day–night transitions in orbit generate time dependent bending moments that induce vibrations in the appendages. So, the heat radiation effects on the appendages should be considered. The thermally induced vibrations of the appendages and the nonlinear heat transfer equation are coupled and should be solved simultaneously. So, the governing equations of the motion are nonlinear and very complicated ones. A robust passivity-based controller is proposed to control the satellite maneuver and appendages vibrations, using piezoelectric sensors/actuators. Findings After the simulation, the effects of the heat radiation, piezoelectric actuators and piezoelectric locations on the response of the system are studied. The results of dynamic response and thermal analysis show that the radiation thermal effects are coupled with structure dynamic. These effects induce the vibration. Also, the effectiveness and the capability of the controller are analyzed. The results of the simulation show that the robust passivity-based control can ensure that the satellite rotates in the desired trajectory and vibrations of the appendages are damped. It demonstrates that the proposed control scheme is feasible and effective. Originality/value The paper is the basis of deriving the governing equations, thermal analysis and a robust control system design of a smart satellite with FGM panels.

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Thermal analysis of a reflective baffle designed for space applications

Cited by 16 publications

References 8 publications

Thermal analysis of composite solar array subjected to space heat flux

Thermal analysis of composite solar array subjected to space heat flux

The BepiColombo Laser Altimeter (BELA): a post-launch summary

Thermoelastic vibration and maneuver control of smart satellites

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