Cryogenic tank and aircraft structural interface

Details Cryogenic tank and aircraft structural interface Cryogenic tank and aircraft structural interface

1974-05-13

1976-04-20

Blix, Trygve M.

Aeronautics and astronautics

Aircraft structure

Load accommodation

114 74A, 220 9LG, 244135R, B64D 900, B64D 3706

Patent

active

039513629

ABSTRACT:
A cryogenic fuel tank of a cylindrical design having toroidal surface ends, is suspended in aircraft structure through a central front mount member; and the rear of the tank is supported by rod elements which extend: from a mounting ring about the tank, to mount points rearwardly within the interior of the fuselage. The central front mount member has a baffles attached thereto, so as to prevent undue sloshing of the liquid within the tank. The front end of the tank suspension absorbs radial and axial loads, but no bending moments; and the aft linkage suspension arrangement takes primarily radial and torsional loads. Also the aft suspension provides for unrestrained axial and radial contraction and expansion of the outer shell of the tank.

REFERENCES:
patent: 2379126 (1945-06-01), Welden
patent: 2504422 (1950-04-01), Johnson et al.
patent: 3078004 (1963-02-01), Randolph
patent: 3107498 (1963-10-01), Messer
patent: 3110318 (1963-11-01), Eulitz
patent: 3157147 (1964-11-01), Ludwig
patent: 3321159 (1967-05-01), Jackson
patent: 3502239 (1970-03-01), Worboys et al.
patent: 3659817 (1972-05-01), Hendal et al.

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