Abstract: A solar array structure for use with satellites requiring large areas of solar arrays. Each array is a single continuous structure having continuous longitudinal members which in a stowed condition enable the panel to be wrapped around the satellite within its launch vehicle. In a deployed configuration, the longitudinal members are reconfigured to provide substantially increased stiffness in the direction of winding.

Abstract: The invention is a counterbalanced bifurcated cowling assembly for a pylon-mounted engine and nacelle therefor, the pylon 16 extending, generally, horizontally from the fuselage 15 of the aircraft 10. The assembly comprises a first cowling section 18 pivotally attached to the pylon 16 which is rotatable from a closed position partially extending about the upper side of the engine 12 to an open position above the engine. A second cowling section 19 is pivotally attached to the pylon 16 and rotatable from a closed position about the underside of the engine 12 to an open position extending downward from the engine. A hydraulic cylinder 40 having an output drive shaft 42 is at least partially mounted within the pylon 16. A pair of first link 44A, 44B are pivotally attached by their first ends 45A, 45B to the end 46 of the output drive shaft 42 and pivotally attached by their second ends 60A, 60B to the first cowling section 18.