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ISSN Online: 2688-7231

ISBN Online: 978-1-56700-524-0

Proceedings of the 26thNational and 4th International ISHMT-ASTFE Heat and Mass Transfer Conference December 17-20, 2021, IIT Madras, Chennai-600036, Tamil Nadu, India
December, 17-20, 2021, IIT Madras, Chennai, India

Thermo-structural Design of an AA2014 mounting between a Structure and Liquid Oxygen Propellant Tank of a Launch Vehicle

Get access (open in a dialog) DOI: 10.1615/IHMTC-2021.2100
pages 1391-1396


Launch vehicle structures are designed to take the inertial, aerodynamic and thermal loads experienced during flight. In rocket stages where liquid oxygen (LOX) is the oxidizer, design of the interface between the LOX tank and the adjoining structures is a challenge. Generally, such interfaces are configured with spherical joints made of titanium alloys but, those joints are difficult to fabricate, heavy and expensive.
A cost-effective simple joint between Aluminum alloy (AA 2014) mounting and tank, which can withstand thermal and structural loads is addressed in this study. Thermal contact resistance across the joint and restricted contact area helps to limit the heat in-leak to the propellant tank. The mounting brackets assembled with pre-defined inclination at ambient temperature straightens during LOX tank contraction, ensuring proper load transfer. An added advantage of the design is that no additional isolator needs to be provided at the interface. Enhancement of thermal isolation using interstitial on the mating interfaces and thermal behavior of the joint is also studied. The temperature distribution across the mounting is obtained from the thermal analysis and subsequently the structural verification is carried out with the joint loads. The configuration is iterated to an optimum one based on thermal and strength considerations.