Aircraft Thermal Management Using Loop Heat Pipes: Experimental Simulation of High Acceleration Environments Using the Centrifuge Table Test Bed 2006-01-3066
The objective of this paper is to describe the design of an experiment that will examine the effects of elevated acceleration environments on a high-temperature, titanium-water loop heat pipe for actuator cooling. An experimental test setup has been designed for mounting a loop heat pipe on an 8-ft-diameter centrifuge table, which is capable of radial accelerations of up to 12 g's. A high-temperature PAO loop will interface the condenser of the loop heat pipe to simulate the rejection of the transported heat to an elevated temperature. In addition to LHP experimentation, a mathematical model has been developed for aerodynamic heating of highspeed aircraft. A flat plate at zero-incidence, used to model an aircraft wing, was subjected to sub- and supersonic flow to examine whether heat will be rejected or absorbed. The results of this analysis will be used to determine the condenser conditions of the loop heat pipe during centrifuge testing.
Citation: Fleming, A., Leland, Q., Yerkes, K., Elston, L. et al., "Aircraft Thermal Management Using Loop Heat Pipes: Experimental Simulation of High Acceleration Environments Using the Centrifuge Table Test Bed," SAE Technical Paper 2006-01-3066, 2006, https://doi.org/10.4271/2006-01-3066. Download Citation
Andrew J. Fleming, Quinn H. Leland, Kirk L. Yerkes, Levi J. Elston, Scott K. Thomas
Air Force Research Laboratory, Wright-Patterson Air Force Base, Wright State University