Integrierte Leitwerkstruktur eines Hubschraubers

• Main Authors: TONER, THOMAS JOSEPH, MILFORD, CONNECTICUT 06460, US, OCCHIATO, JOHN JOSEPH, DERBY, CONNECTICUT 06418, US, WEINER, STEVEN DAVID, ORANGE, CONNECTICUT 06477, US
• Format: Patent
• Language: German
• Published: 09.11.1995
• Edition: 6
• Subjects: AEROPLANES; AIRCRAFT; AVIATION; COSMONAUTICS; HELICOPTERS; PERFORMING OPERATIONS; TRANSPORTING

The integrated empennage structure (20) includes a shroud (22) that houses the ducted fan antitorque device (18), a vertical stabilizer (28), and a horizontal stabilizer (30). The aerodynamic configurations and/or orientations and the spatial orientations of the shroud (22), vertical stabilizer (28), and the horizontal stabilizer (30) are interactively related and optimized to provide yaw stability and directional control and pitch stability and maneuverability required for helicopter flight operations. The shroud (22) is spatially orientated at a first predetermined cant angle ( theta 1) with respect to the vertical plane symmetry (ZS) of the helicopter fuselage (12) such that the ducted fan antitorque device (18) provides lateral antitorque thrust to counteract main rotor assembly (14) induced torque and a positive vertical force component to enhance the overall lift capability of the helicopter. The vertical stabilizer (28) is spatially orientated at a second predetermined cant angle ( theta 2) with respect to the vertical plane (ZS) and aerodynamically configured with a predetermined camber and/or aerodynamically orientated with a predetermined angle of incidence to provide an antitorque force during forward flight regimes that allows the ducted fan antitorque device (18) to be effectively off-loaded and a negative vertical force component that complements the negative vertical force provided by the horizontal stabilizer (30). The aerodynamic functioning of the vertical stabilizer (28) allows aerodynamic configuration and/or the aerodynamic orientation of the horizontal stabilizer (30) to be reduced and facilitates the attachment of the horizontal stabilizer (30) in substantially symmetrical relation to the vertical stabilizer (28). The horizontal stabilizer (30) is aerodynamically configured and orientated to optimize the dynamic pitch stability of the helicopter in the forward flight regimes.