Takehide Nomura

Thermal Robustness and Mass Optimization of Heat Pipe Shape for Spacecraft Panel Using a Combination of Response Surface Methodology and Monte Carlo Simulation

A commercial spacecraft should survive on orbit for more than 10 years under the severe circumstances without any maintenance. To realize this subject, not only performance but also other design factors such as reliability, mass, robustness, cost, etc. should be taken into consideration. From point of the thermal design, it is very important to obtain the robust thermal control subsystem with matrix heat pipe layout while minimizing the mass (weight). A new thermal optimization method without compromising the thermal robustness and the mass of thermal subsystem is highly anticipated. This paper proposes a robust thermal design approach for optimizing the heat pipe shape to minimize the mass of the spacecraft panel. We apply a combination of Design of Experiments (DOE), Response Surface Methodology (RSM) and Monte Carlo Simulation to determine the robust design parameters that minimize the mass of the heat pipe structure. Dimensions of the heat pipe design parameters were determined with rationally in a short time and practical robust optimization method was established.Copyright

Characteristics of Reservoir Embedded Loop Heat Pipe in Deployable Radiator on ETS-VIII at Beginning of the Experiment under Orbital Environment

A deployable radiator (DPR) on the Engineering Test Satellite-VIII (ETS-VIII) was launched to a geo stationary orbit using H-IIA rocket on 18 Dec. 2006, carrying a deployable radiator (DPR). Deployable radiators are anticipated for extension of the radiator area on satellites to mitigate increased heat generation. The DPR is an experimental apparatus on the ETSVIII; it has a reservoir-embedded loop heat pipe (RELHP) for heat transfer from the experimental heat load to the DPR radiator. The RELHP reservoir is embedded in the evaporator for reliable function of the Loop Heat Pipe (LHP). This paper describes the DPR and the RELHP characteristics on the ETS-VIII from its launch operation to the beginning of the test under an orbital environment.

Characteristics Variation of Reservoir Embedded Loop Heat Pipe under the Orbital Environment in Three Years

A deployable radiator (DPR) on the Engineering Test Satellite-VIII (ETS-VIII) was launched to a geo stationary orbit by the H-IIA rocket on 18 Dec. 2006. The DPR, an experimental apparatus on ETS- VIII; it has a Reservoir-Embedded Loop Heat Pipe (RELHP) for heat transfer from the experimental heat load to the DPR radiator. The RELHP reservoir is embedded in the evaporator for reliable function of the Loop Heat Pipe (LHP). This paper describes the characteristics of the DPR and the RELHP under an orbital environment over three years.