Sikorsky Aircraft Corporation

United Technologies Corporation

Alan R Goodworth

Thomas Arthur Carstensen

Connie E Bird

William V Forster

Gary Hamilton

James A Anthony

Bruce Frederic Kay

A vertical take-off and landing (VTOL) aircraft includes an airframe having a transverse axis and a longitudinal axis that is substantially perpendicular relative to the transverse axis. A transmission and rotor support platform is arranged in the airframe. A transmission is supported by the transmission and rotor support platform. An energy attenuation system mechanically links the transmission and rotor support platform with the airframe. The energy attenuation system includes a first plurality of collapsible support members selectively facilitating rotation of the transmission and rotor support platform about the transverse axis and a second plurality of collapsible support members, the first and second pluralities of support members selectively facilitating translation of the transmission and rotor support platform along an axis that is substantially parallel to the rotor axis.

Crash energy attenuation system for a transmission support in a vertical lift aircraft

An armor panel includes a multiple of pins which penetrate a first skin, a high molecular weight polyethylene fiber composite material layer and a second skin which integrates ballistic protection into load bearing structure.

Non-ceramic structural panel with ballistic protection

A composite panel and method of manufacture includes a support structure and a tape skin wound about the support structure. A mandrel assembly with extractable longitudinal mandrels facilitates winding of the tape skin onto the support structure. The composite panel is suitable for use in an aircraft floor system.

Method of forming panels using an in-situ tape placement process and panels formed therefrom

The present invention broadly relates to a tail cone assembly for a helicopter. The tail cone assembly includes a monocoque shell formed from a composite material. The composite material preferably comprises a non-metallic matrix, such as an epoxy resin matrix, having fibers, such as graphite fibers, embedded therein. The fibers may be oriented along a single axis or along multiple axes. Other components of the tail cone assembly may also be formed from composite materials, which composite materials may be the same as or different from the composite material forming the shell.

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Oxford, CT, United States of America

Alan R Goodworth