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

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Kobayashi, Takashi Nomura, Takehide Kamifuji, Masaki Yao, Akira Ogushi, Tetsurou
Abstract	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.
Sponsorship	Design Engineering Division and Computers and Information in Engineering Division
Starting Page	181
Ending Page	189
Page Count	9
File Format	PDF
ISBN	0791836223
DOI	10.1115/DETC2002/DAC-34055
e-ISBN	0791836037
Volume Number	Volume 2: 28th Design Automation Conference
Conference Proceedings	ASME 2002 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference
Language	English
Publisher Date	2002-09-29
Publisher Place	Montreal, Quebec, Canada
Access Restriction	Subscribed
Content Type	Text
Resource Type	Article

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