Abstract: Embodiments of rotary-wing aircraft include a fuselage, and a main rotor assembly mounted for rotation on the fuselage. The rotary-wing aircraft also have an anti-torque device. The anti-torque device has a body that is contiguous with the fuselage, and a rotor mounted within a duct defined by the body.

Abstract: Processes for manufacturing hollow structures such as spars for helicopter rotor blades, fixed wings for aircraft, and other aerostructures can include the provision of a path for gases to exit the material from which the spar is formed as the material is heated and cured, to help eliminate voids within the material caused by the presence of such gases.

Abstract: Processes for manufacturing hollow structures such as spars for helicopter rotor blades, fixed wings for aircraft, and other aerostructures can include the provision of a path for gases to exit the material from which the spar is formed as the material is heated and cured, to help eliminate voids within the material caused by the presence of such gases.

Abstract: A preferred embodiment of a rotor head for a rotary-wing aircraft having a plurality of rotor blades and a drive shaft includes a gimbal mechanically coupled to the drive shaft so that the gimbal rotates with the drive shaft, and a hub pivotally coupled to the gimbal for receiving the rotor blades. The rotor head also includes an actuator mechanically coupled to the hub for causing the hub to pivot about the gimbal.

Abstract: A preferred embodiment of a rotary-wing aircraft includes a fuselage, a tail boom fixedly coupled the fuselage, a pylon fixedly coupled to the tail boom, and a main rotor assembly rotatably coupled to the fuselage and comprising a hub and a plurality of rotor blades pivotally coupled to the hub. The preferred embodiment also includes a cyclic control adapted to vary an orientation of the rotor blades in relation to the hub on a cyclical basis, and a horizontal stabilizer mounted on one of the pylon and the tail boom. At least a portion of the horizontal stabilizer is movable in relation to the one of the pylon and the tail boom and a position of the at least a portion of the horizontal stabilizer is controllable independent of the cyclic control.

Abstract: A preferred embodiment of a rotary-wing aircraft comprises a main rotor, a tail boom extending through an area of downwash from the main rotor, and a linear nozzle fixedly coupled to the tail boom and having an opening extending along the tail boom for discharging a sheet of fluid in a direction substantially tangential to an outer surface of the tail boom. A preferred embodiment also comprises a yaw-control device movably coupled to the tail boom and having an opening formed therein for discharging fluid in a direction away from the yaw-control device and into the area of downwash from the main rotor.

Abstract: A preferred embodiment of a rotary-wing aircraft comprises a fuselage, a tail boom fixedly coupled the fuselage, a pylon fixedly coupled to the tail boom, and a main rotor assembly rotatably coupled to the fuselage and comprising a hub and a plurality of rotor blades pivotally coupled to the hub. The preferred embodiment also comprises a cyclic control adapted to vary an orientation of the rotor blades in relation to the hub on a cyclical basis, and a horizontal stabilizer mounted on one of the pylon and the tail boom. At least a portion of the horizontal stabilizer is movable in relation to the one of the pylon and the tail boom and a position of the at least a portion of the horizontal stabilizer is controllable independent of the cyclic control.

Abstract: A rotary-wing aircraft comprises a main rotor, a tail boom extending through an area of downwash from the main rotor, and first and second linear nozzles fixedly coupled to the tail boom. The first nozzle is adapted to discharge a sheet of fluid in a direction substantially tangential to an outer surface of the tail boom to divert the rotor downwash and thereby produce a force that counteracts the biasing torque of the main rotor. The rotary-wing aircraft further comprises a yaw-control member movably coupled to the tail boom. The second nozzle is adapted to discharge a sheet of fluid in a direction substantially tangential to an outer surface of the yaw-control member to further divert the rotor downwash and thereby increase the force that counters the main-rotor torque.

Abstract: A method is disclosed for airborne gravity and magnetic field surveying, in which the airborne vehicle is stabilized with respect to speed, direction of heading, and center of gravity, and in which the gravity meter is of adequate sensitivity and provides signals that are recorded at a high sample rate on a magnetic tape, with magnetic data collected and preserved which can be used alone or as a reference for checking the accuracy of the gravity data, and with the aircraft's position computed using a satellite positioning system, or a multi-range navigation system that is geodetically located.

Abstract: Method and apparatus are disclosed for airborne gravity surveying in which the airborne vehicle is stabilized with respect to speed, direction of heading and altitude, and in which the gravity meter has adequate sensitivity and signals that are recorded at a high sample rate on a magnetic tape, in which the aircraft position is computed using a multi-range navigation system that is located geodetically.