Solar Orbiter—Heat shield and system technology

Poncy, J.; Jubineau, F.; D'Angelo, F.; Perotto, Valter; Juillet, J. J.

doi:10.1016/j.actaastro.2009.03.031

Cited by 6 publications

(4 citation statements)

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“…The developed model, given by Equations (8)- (10), is obtained by energy conservation between the heat conduction among the space vehicle, the heating from the solar radiation, the radiative heat dissipation into the surroundings while accounting for the dynamics of the space vehicle (rotational motion). This model is solved numerically using the meshless collocation point method (MCP) to evaluate the temperature distribution under different operating conditions.…”

Section: Resultsmentioning

confidence: 99%

“…The diffusion-convection problem simulating the temperature variations of the space vehicle is described by Equations (1)- (10). To implement the meshless point collocation method, it is necessary to represent the spatial domain with a set of nodes, distributed over the interior domain and on the boundary.…”

Section: Explicit Solvermentioning

confidence: 99%

“…The space environment during the spacecraft travelling time and mission continues to be a major cause of anomalies in many space missions. The most common factors of such anomalies are surface charging and discharging, solar radiation heating loads, and the existence of orbital debris in space as indicated by several published studies [1][2][3][4][5][6][7][8][9][10][11][12]. In addition, the solar load, shielding material, onboard equipment location, thermal control and air conditioning systems must be considered during the design stage of spacecraft/satellites [13][14][15][16][17][18][19].…”

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: Resultsmentioning

confidence: 99%

Section: Explicit Solvermentioning

confidence: 99%

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 space environment continues to be a major cause of anomalies in many space missions. The most common causes of such anomalies are surface charging and discharging and solar radiation heating as indicated by some previous investigators [1–8]. The solar heating must be considered during the design stage of spacecraft's shielding, air conditioning system, electronics' location, measuring systems, and material selected for use on spacecraft [9–15].…”

Section: Introductionmentioning

confidence: 99%

Computational modeling and analysis of thermal characteristics of a rotating spacecraft subjected to solar radiation

Gadalla

Wahba

2011

Heat Trans. Asian Res.

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This paper presents a computational modeling for the temperature distribution of a rotating thick-walled cylindrical spacecraft subjected to solar radiation. The inner surface of the spacecraft is thermally insulated while the outer surface is subjected to concurrent events of solar incidence and radiative heat dissipation to space. The governing equation for the normalized temperature is discretized using a finite difference scheme and Successive Line Over-Relaxation (SLOR) is used to solve the resulting system of algebraic equations. Numerical simulations of temperature distribution on the spacecraft for different spinning speeds, angular positions, and different radii are discussed and evaluated for both linearized and nonlinear boundary conditions. Comparative analysis between the computational modeling and the exact analytical solution for the linearized boundary condition is presented. The results indicate that the outer surface temperature distribution of the spacecraft is nearly independent of the angular position; at sub-cylindrical surface, this independence is achieved at low angular velocity. Moreover, numerical simulations show that the use of the linearized boundary condition at the outer surface presents a good approximation for the case of high-speed spinning spacecrafts, while it results in significant errors in the temperature field in the case of stationary and low-speed spinning spacecrafts.

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