Abstract: An elongate hollow structure with a plurality of reinforcements arranged in a pattern and acting as spacers between a pair of skins. The skins are of resin impregnated wound filaments with reinforcing strips of facing preimpregnated wound filaments that crisscross at the spacing reinforcements, abutting panels extend between adjacent reinforcing spacers to fill the space between the skins, and the structure is bonded with resin into a composite structure.

Abstract: A lightweight cargo container and fitting for the construction thereof are disclosed. The fitting has a simple cross-sectional shape so that it may be inexpensively manufactured of lightweight materials, yet it provides an easily assembled, secure connection between wall panels of a lightweight container.

Abstract: An elongate hollow structure with a plurality of reinforcements arranged in a pattern and acting as spacers between a pair of skins. The skins are of resin impregnated wound filaments with reinforcing strips of facing preimpregnated wound filaments that crisscross at the spacing reinforcements, abutting panels extend between adjacent reinforcing spacers to fill the space between the skins, and the structure is bonded with resin into a composite structure.

Abstract: A tandem wing aircraft is provided having two independent spaced apart fuselages and two wings of similar area, a lower forward wing and a higher aft wing. The lower forward wing is attached to the forward region of each of the spaced apart fuselages; the higher aft wing is aerodynamically spaced apart from and located above the aft region of the spaced apart fuselages. An aft strut member is disposed between the aft wing and each of the fuselages; each aft strut member has a length sufficient to cause the wing tips of the lower forward wing and the upper aft wing to be vertically spaced apart by a distance of at least 25% of the span of either of the wings.

Abstract: For increasing the cargo capacity of an airplane of given weight, the cargo space is formed by a plurality of parallel tubes having their lengths extending spanwise of the wing, so that such cargo-carrying space is generally coextensive with the lift-producing airfoil. Auxiliary lift-producing fans may also be spaced spanwise of the wing, and the ground effect of such fans may be augmented by skirts depending from the wing. Propulsion thrust engines are also spaced spanwise of the wing to distribute thrust loading. The airplane wing is tilted downwardly spanwise so that containerized or particulate solid cargo or liquid cargo can be supplied to the cargo tubes through the lower wing tip, and such cargo can be removed from the cargo tubes by gravity or assisted by air under pressure to fluidize or expel the cargo. The wing may carry a plurality of spaced parallel fuselages.

Abstract: An apparatus is provided for rapid loading and unloading of large volumes of liquid to and from a cargo transport, herein a landed aircraft transport. At a ground station, liquid is loaded from, or unloaded to, a reservoir equipped with a positionable, extendible hollow tubular boom having a cross-sectional flow area exceeding thirty square feet. At the extendible end of the boom, a valve closure is provided, movable by a power-driven ball-screw actuator between a retracted position closing the open end of the boom and an extended, open position spaced forwardly of the boom end. A cooperating valve assembly and receptacle for receiving the positionable boom end are mounted on the aircraft in a wing section, accessible by a fold-away hinged wingtip.

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 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 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 radical and torsional loads. Also the aft suspension provides for unrestrained axial and radial contraction and expansion of the outer shell of the tank.

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.