研究目的
Exploring the role of the screw axial load on the temperature experienced by the mounting set of a Cube Corner Retroreflector (CCR) in a spherical satellite, designed to achieve 1-mm accuracy in satellite laser ranging.
研究成果
The simulations showed the thermal feasibility of the satellite, with CCRs presenting mean thermal gradients around 2.5 K and Kel-F rings not overcoming their limit temperature. The work serves as a basis for the development of a new satellite, but further tests are needed to validate the thermo-optical model.
研究不足
The interface conductance has been computed analytically, but an experimental value is needed to update the model. The real interface resistances have to be computed experimentally for a more critical study.
1：Experimental Design and Method Selection:
The study uses thermal analysis and simulation to explore the thermal behavior of CCRs in a spherical satellite. Two models are created in Thermal Desktop?: a simplified satellite model and a detailed cavity model.
2：Sample Selection and Data Sources:
The study focuses on a spherical satellite with CCRs, inspired by LAGEOS and LARES satellites.
3：List of Experimental Equipment and Materials:
The satellite is modeled with a nickel alloy sphere and Kel-F mounting rings.
4：Experimental Procedures and Operational Workflow:
Simulations are performed for different on-orbit scenarios, focusing on the influence of the screw axial load.
5：Data Analysis Methods:
The thermal gradients inside CCRs and the temperature of mounting rings are analyzed to assess the satellite's thermal behavior.
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