Abstract: An airframe includes an energy absorbing structure with a frame, a beam mounted to the frame at a rotational joint and a collapsible member. In response to reaching a predetermined threshold load value during a high sink rate impact event, the collapsible member will collapse under an aft section of the upper deck. The rotational joint operates as a virtual hinge such that a forward section of the upper deck deforms in a predictable manner. As the upper deck supports the high mass systems, the high mass components are less likely to separate from their mounting and penetrate into the crew compartment and the main rotor system will tilt aft away from the crew compartment to minimize the likelihood that the rotor blades may penetrate the crew compartment.

Abstract: In accordance with the present invention, a tail rotor pylon for use on a rotorcraft, such as a helicopter, is provided. The tail rotor pylon has a plurality of elements formed from a carbon/epoxy composite material. These elements include side skin panels, ribs, and spars.

Abstract: The present invention relates to a graphical display for cueing helicopter main rotor aerodynamic braking. The graphical display comprises first indicia representing wind direction, second indicia representing main rotor roll control, third indicia representing main rotor pitch control, and fourth indicia representing a margin from main rotor flapping limit. The display cues a pilot with the proper direction in which to orient a rotor disk without exceeding main rotor flapping structural limitations.

Abstract: A composite component includes splinter arrestors laminated transverse to the fiber orientation of an outermost composite material layer. The splinter arrestors are located upon the outermost composite material layers at a predetermined distance from each other to constrain a splinter of fibers from the outermost composite material layers to an acceptable length.