Abstract: An internal combustion engine of the present invention features separate compression and expansion cycles. The engine includes a separate compressor device which pressurizes air by a ratio greater than 15 to 1, at least one two stroke combustion cylinder and a compressed air conduit for transferring compressed air from the compressor to the at least one combustion cylinder. An air injection valve injects the compressed air into the combustion cylinder during the second half portion of the return stroke of the combustion cylinder. The compressed air is mixed with fuel and combusted for expansion during a power stroke. In this engine compression occurs only to a minor degree in the combustion cylinder. Accordingly, the compression ratio of the present engine may be significantly higher or lower than the volumetric expansion ratio of the combustion cylinder thus resulting in corresponding increases in either power density or thermodynamic efficiency respectively.

Abstract: A wheel (10) with a rim (12) and at least one spoke (14) includes a rim (12) wherein the depth of the rim (12) varies circumferentially around the rim (12). At least one spoke (14) with a first end (16) connected to the rim (12) and a second end (18) connected to a wheel hub (20) is provided wherein the cross-section of the spoke (14) varies from the first end (16) to the second end (18). The rim (12) depth varies circumferentially so that the depth is greater between the spokes (14) and less at the spokes (14). Further, the spoke (14) cross-section is symmetrical at the second end (18) connected to the wheel hub (20) and asymmetrical at the first end (16).

Abstract: An aerial refueling system includes a pod assembly which is removably mounted for translation on an elongated pylon secured to the underside of an aircraft fuselage, whereby the pod assembly is moved relatively forward on the fuselage for stowage and relatively aftward on the fuselage for refueling operations. The pod assembly includes a pivotable, telescoping boom having control surfaces by which to aerodynamically position the boom's free end relative to the pod assembly. A coupling preferably establishes fluid communication between the boom and a fuel tank within the aircraft fuselage only when the pod assembly assumes the relatively-aftward refueling position on the pylon. A ram-air turbine on the forward end of the pod assembly provides all necessary power for the pod assembly, with wireless remote operation of all pod assembly functions preferably used to minimize the extent of alterations when installing the aerial refueling system on the aircraft.

Abstract: A cascade assembly (14) for use in a thrust reversing mechanism (16) of a jet engine (18) includes at least one group of substantially identically-shaped cascade elements (28) each in the shape of a predefined polygon. The cascade elements (28) are positioned in an array, wherein each cascade element (28) in the group may be interchanged in a location in the array with any other cascade element (28) in the group. In a first preferred embodiment, the predefined polygon is a regular polygon and each cascade element (28) is rotatable in its array position about an axis generally normal to the cascade element (28). The array substantially approximates sections of two intersecting spheres, wherein a central axis of the array is generally coincident with the longitudinal axis of the jet engine (18).

Abstract: A novel method and apparatus are provided for consolidating and perforating multilayer laminates by a combination of vibratory motion and impacting pressure applied by a special compacting tool preparatory to final cure.