Thermala??Structural Optimization of Integrated Cryogenic Propellant Tank Concepts for a Reusable Launch Vehicle

机译：可重复使用运载火箭的集成低温推进剂储罐概念的Thermala ??结构优化

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《AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics & Materials Conference;AIAA Non-Deterministic Approaches Forum;AIAA/ASME/AHS Adaptive Structures Conference;AIAA Gossamer Spacecraft Forum》|2004年|P.1-11|共11页
会议地点 Palm Springs, CA(US);Palm Springs, CA(US);Palm Springs, CA(US);Palm Springs, CA(US)
作者
T. Johnson; W. Waters; T. Singer; R. Haftka;
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NASA Langley Research Center Hampton VA;

University of Florida Gainesville FL;

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3. Using Fracture Mechanics Principles for Calculating the Pressurized Structure Lifetime by Example of the Propellant Tank for the Fourth Stage of Launch Vehicle VEGA [J] . A. S. Birukov, V. I. Kalinin, A. V. Grinevich, Solar system research . 2014,第7期

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4. Thermala??Structural Optimization of Integrated Cryogenic Propellant Tank Concepts for a Reusable Launch Vehicle [C] . American Institute of Aeronautics and Astronautics/American Society of Mechanical Engineers/American Society of Civil Engineers/American Helicopter Society/ASC Structures, Structural Dynamics Materials Conference . 2004

机译：Thermala ??用于可重复使用的发射车辆的综合低温推进剂罐概念的结构优化
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7. Thermal–Structural Optimization of Integrated Cryogenic Propellant Tank Concepts for a Reusable Launch Vehicle [O] . Theodore F. Johnson, W. Allen Waters, Thomas N. Singer, 2008

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8. Thermal-Structural Optimization of Integrated Cryogenic Propellant Tank Concepts for a Reusable Launch Vehicle [R] . Johnson, T. F. , Waters, W. A. , Singer, T. N. , 2004

机译：可重复使用运载火箭集成低温推进剂储罐概念的热结构优化

Thermala??Structural Optimization of Integrated Cryogenic Propellant Tank Concepts for a Reusable Launch Vehicle

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