Launch Solid Stress Analyses of Ultra-Light Heat Rejection Radiator Module and Panel for Lunar Fission Surface Power

Timothy M. Schriener & Mohamed S. El-Genk

jbis-078-03-0092

DOI https://doi.org/10.59332/jbis-078-03-0092

This work presents the results of performed finite element solid stress analyses of a single lightweight radiator module and a radiator panel during launch. The analyses investigate the effect of 5-100 Hz vibration acceleration loads of the Falcon Heavy and Delta IV Heavy launch vehicles. The radiator module comprises of a Cs-Ti heat pipe with HOPG/Ti heat spreading fins mounted into a titanium frame and the panel comprises of ten modules hydraulically coupled in parallel. The radiator panel has an areal density of 2.98 kg/m2 and rejects >56 kWth into space at a surface average temperature of 600 K. The highest induced Von Mises stresses for the radiator module during launch of 11.9 -12.9 MPa are only 1.2%-1.5% of the yield strength of the Ti alloy walls and the highest induced tensile stresses are <6% of the bending failure of HOPG. The highest induced Von Mises stresses in the radiator panel during launch on the Falcon Heavy in the Ti alloy walls of 22.5-97.6 MPa are <10% of the titanium alloys yield strength of 898 MPa. These results confirm that the designed lightweight Cs-Ti heat pipe radiator panel would survive vibration acceleration loads during launch..

Keywords: Heat Pipes, Fission Surface Power, Radiators, Finite Element Analysis, Launch Stresses