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A Study of Heat Transfer and Vibration in Solar Array

Author: JiangZhuoLiang
Tutor: ZhaoHua
School: Southwest Jiaotong University
Course: Engineering Mechanics
Keywords: Solar panels Temperature field Heat distortion Dynamic response Collision
CLC: V414.1
Type: Master's thesis
Year: 2010
Downloads: 152
Quote: 0
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Abstract


Spacecraft solar arrays cycle heating radiation in outer space by the sun and other stars, the reliability of thermal deformation under high and low temperature and thermal vibration of the the windsurfing structure of security has an important impact. The drift space junk may collide with solar panels, the the windsurfing structure dynamics is also designed to be considered important indicators. Thornton theory as the theoretical basis of the thermal analysis using Marc finite element software, the first of the main beam of the Hubble Space Telescope solar panels heat up in the sun light in the Earth's shadow into outer space radiation the thermal cooling the temperature field simulation obtain the temperature field of the main beam, main beam of thermal deformation and thermal stress simulation, calculation results with existing theoretical solutions, numerical solutions are in good agreement. Marc software implementation of the main beam in the elastic modulus and density with temperature under the variation of modal analysis to study the dynamic response of the Main Cantilever end point loads. Finally, the simulation the whole cycle changes in temperature field of solar panels, the dynamic response varies with temperature, focusing on the dynamic response of the solar panels in space junk collision. Through the study, we get the following results: (1) during the heating process, the solar panels the main beam of the temperature field in the sunshine for about 15 minutes to stabilize, the highest steady-state temperature of 158.4 ° C, the lowest temperature of 116.6 ° C. The average temperature is about 130 ℃. The cooling process, the solar panels the main beam in about 150 seconds or so-sectional temperature difference is less than 0.1 ℃, the temperature of the main beam section probably in about 1000 seconds and the outside ambient temperature tends to be the same. (2) when the solar panels main beam by the sun light, the cross-sectional temperature distribution is a sinusoidal distribution within 15 minutes of the start, in the sunshine, the overall temperature rise and after 15 minutes the main beam absorption and heat radiated outward equal, the entire reach steady-state temperature field of the main beam. (3) when the main beam density and elastic modulus amount with increasing temperature and reduced, the main beam of each order inherent frequency corresponding reduced; density and elastic modulus amount not over temperature changes, temperature change of the main beam inherent frequency of the have little effect. (4) the overall simulation of the solar panels the overall inherent frequency of the solar panels is very low, for a typical flexible structure. A temperature cycle under the conditions of the dynamic response is actually caused by the temperature difference of the main beam section due to thermal deformation, the dynamic response of the speed, the acceleration is very small. (5) This paper simulation of the solar panels as a whole in outer space at some point encounter the pulse load, for example, when the space junk collision of windsurfing dynamic response, displacement, velocity and acceleration versus time variation given the the windsurfing main beam maximum stress area of ??stress variation over time, windsurfing significant torsional deformation.

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CLC: > Aviation, aerospace > Aerospace ( Astronauts ) > Basic theory and experiments > Spacecraft structural mechanics > Structural Analysis and Calculation
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