United Technologies Corporation

Other

Sikorsky Aircraft Corporation

Thomas J Toner

Peter C Ogle

Edward S Hibyan

Francis E Byrnes

Leonard J Doolin

George J Wehnert

Steven D Weiner

John J Occhiato

Randall J Martin

An emergency egress system (10) for facilitating emergency egress of passengers/crewmembers from an aircraft (4), which egress system (10) includes an egress panel (12), a panel frame (14) disposed about the egress panel (12) and a weather strip (16) defining back-to-back channels (18) for accepting the peripheral edges (12.sub.E, 14.sub.E) of the egress panel (12) and the panel frame (14). Furthermore, the emergency egress system (10) includes a plurality of retention devices (30) disposed about the periphery of the egress panel (12) for laterally retaining the egress panel (12) with respect to the panel frame (14) in a normal operating mode, a cam (80) operative to forcibly urge a portion of the weather strip (16) out of engagement with one of the peripheral edges (12.sub.E, 14.sub.E) and an actuation device (50) operative to sequentially disengage at least one of the retention devices (30) and actuate the cam (80) in an emergency operating mode. Following actuation, a passenger/crewmember may detach the egress panel (12) from the panel frame (14).

Emergency egress system for aircraft

A helicopter with a retractable rotor for transport wherein the rotor and its blades, the swashplate, the pitch change rods and support mast are lowered or raised in unison by the hydraulic flight control servos as commanded by the helicopter computerized flight control when being commanded by special rotor retraction/extension software.

Helicopter with retractable rotor for transport

An integrated empennage structure is provided for a helicopter embodying a ducted fan antitorque device. The integrated empennage structure includes a shroud that houses the ducted fan antitorque device, a vertical stabilizer, and a horizontal stabilizer. The aerodynamic configurations and/or orientations and the spatial orientations of the shroud, vertical stabilizer, and the horizontal stabilizer are interactively related and optimized to provide yaw stability and directional control and pitch stability and maneuverability required for helicopter flight operations. The shroud is spatially orientated at a first predetermined cant angle with respect to the vertical plane of symmetry of the helicopter fuselage such that the ducted fan antitorque device provides lateral antitorque thrust to counteract main rotor assembly induced torque and a positive vertical force component to enhance the overall lift capability of the helicopter. The vertical stabilizer is spatially orientated at a second predetermined cant angle with respect to the vertical plane and aerodynamically configured with a predetermined camber and/or aerodynamically orientated with a predetermined angle if incidence to provide an antitorque force during forward flight regimes that allows the ducted fan antitorque device to be effectively off-loaded and a negative vertical force component that complements the negative vertical force provided by the horizontal stabilizer. The aerodynamic functioning of the vertical stabilizer allows aerodynamic configuration and/or the aerodynamic orientation of the horizontal stabilizer to be reduced and facilitates the attachment of the horizontal stabilizer in substantially symmetrical relation to the vertical stabilizer. The horizontal stabilizer is aerodynamically configured and orientated to optimize the dynamic pitch stability of the helicopter in the forward flight regimes.

Integrated helicopter empennage structure

A helicopter rotor hub including a main retention plate that comprises triaxial braided tubular composite material having a fiber orientation that withstands forces both in the plane and normal to the plane of the retention plate. The retension plate comprises a plurality of fiber reinforced resin braided tubular rings that are spaced about in a plane normal to a central axis. The rings form a circumferential ring structure having arm means extending inwardly. A flattened braided tubular ring strap surrounds the circumferential ring structure. Fiber reinforced plates are disposed above and below the ring structure providing additional in-plane strength. The braided tubular rings and braided tubular ring strap comprises substantially circumferential fibers interwoven with angled fibers oriented at a predetermined angle to the circumferential fibers.

Composite helicopter rotor hub

A composite helicopter hub yoke is described. The yoke is made up of glass fibers unidirectionally oriented in the direction of principle stress, i.e. along the length of the yoke. The yoke also has clevis sections on either end and the clevis sections additionally contain multiaxially oriented multiple plies of unidirectionally oriented continuous graphite fibers interleaved with the unidirectionally oriented continuous glass fibers to produce crack resistance, damage tolerance, and integrity inspectability.

Fiber reinforced/epoxy matrix composite helicopter rotor yoke

A composite helicopter rotor hub is described having a composite retention plate, yokes and torque tubes. The retention plate is made up of graphite and glass fiber reinforced epoxy resin. The graphite fiber reinforcement is in-plane isotropically laid continuous graphite fibers and the glass fiber reinforcement comprises segments of fiberglass continuously and circumferentially wound around the areas of retention. The yoke is made up of glass fibers unidirectionally oriented in the direction of principle stress, i.e., along the length of the yoke. The yoke also has clevis sections on either end and the clevis sections additionally contain multiaxially oriented multiple plies of unidirectionally oriented continuous graphite fibers interleaved with the unidirectionally oriented continuous glass fibers. The torque tube contains upper and lower load bearing surfaces connected by two sidewall portions. Both the sidewall and load bearing portions contain filament wound glass fiber reinforced epoxy resin such fibers having a .+-.45.degree. orientation. The upper and lower load bearing portions additionally contain multiaxially oriented multiple plies of unidirectionally oriented continuous graphite fibers interleaved with the glass fibers. The particular materials selected combined in the unique manner described provide the individual components as well as the entire hub assembly with crack resistance, damage tolerance, light weight, strength and integrity inspectability.

A composite torque tube for a helicopter rotor hub is described. The torque tube contains upper and lower load bearing surfaces connected by two sidewall portions. Both the sidewall and load bearing portions contain filament wound glass fiber reinforced epoxy resin such fibers having a .+-.45.degree. orientation. The upper and lower load bearing portions additionally contain a plurality of multiaxially oriented plies of continuous unidirectionally oriented graphite fibers interleaved with the glass fibers so as to produce a torque tube with crack resistance, damage tolerance, light weight, strength and integrity inspectability.

Fiber reinforced/epoxy matrix composite helicopter rotor torque tube

An electrical circuit for monitoring the connection between a trailer and a trailer hitch. An electrical conductor is connected to the tongue of the trailer and the trailer hitch is grounded. A visual indicator is in series between the electrical conductor and a power source to provide an indication of trailer coupling as long as electrical continuity is maintained by the connection of the trailer to the hitch. An audible warning device and switch are in parallel with the visual indicator to provide a warning when electrical continuity is broken.

Growing community of inventors

Milford, CT, United States of America

Thomas J Toner