| 摘要 |
A liquid fuel tank for an airplane of the type which constitutes a structural part of the airplane wing, the outer surface of which defines the aerodynamic outer surface of at least a portion of the wing, includes walls having a bonded multilayer sandwich structure having sufficient rigidity and strength while being devoid of internal and external reinforcing structure. The sandwich structure includes an inner liquid-tight tank formed of thin sheet material, an intermediate core layer formed of a cellular material or the like bonded to the outer surface of the tank, and an outer shell layer formed of sheet material bonded to the outer surface of the intermediate layer. The outer surface of the outer layer constitutes the aerodynamic outer surface of at least a portion of the airplane wing. The liquid tank is manufactured by enclosing an inner liquid-tight tank in an intermediate core layer of cellular material or the like, enclosing the intermediate core layer in an outer shell layer formed of sheet material and bonding the intermediate core layer to the inner tank and the outer shell layer to the intermediate core layer in a die cavity of a die tool which defines an inner surface which corresponds in shape to the outer surface of the liquid tank and the aerodynamic outer surface of at least a portion of the airplane wing. In this manner, the outer surface of the outer shell layer will correspond in shape to the aerodynamic outer surface of the airplane wing. |
