Piasecki Aircraft Corporation

Luigi U Ricci Moretti

Frederick W Piasecki

Robert H Lewis

George Luis Firpi

Dinesh Barwey

Shane A Lewis

An electromechanical boost actuator for aircraft flight control is attached to a mechanical input by a mechanical linkage. The mechanical linkage is also attached to the output shaft of the electromechanical boost actuator. When a pilot or control system manually moves the mechanical input, a position sensor attached to the linkage activates electric motor(s), extending or retracting the output shaft in the direction commanded by the pilot or control system. The motion of the output shaft, acting through the linkage, moves the position sensor to a neutral position, stopping the electric motor(s) and the output shaft when the output shaft reaches the commanded position. Additional linear actuators may inject another control signal in conjunction with the mechanical input.

Apparatus, system and method for control of electromechanical boost actuators

A supplemental wing for a rotary wing aircraft rotates about a pitch axis between a forward flight position and a hover position. The supplemental wing generates lift and generates both positive and negative pitching moments that balance and that may passively rotate the supplemental wing to an equilibrium position. The supplemental wing may use power assist to overcome friction to move to the equilibrium position. The lift generated by the supplemental wing reduces at high forward speeds to preserve main rotor control authority. The supplemental wing rotates to avoid aft translation when in the hover position. The supplemental wing may be retrofitted to existing helicopters and flown using existing helicopter controls without pilot re-training.

Apparatus, system and method for a supplemental wing for a rotary wing aircraft

A removable battery to provide motive power for an aircraft includes a battery frame and removable, interchangeable battery modules. Each of the battery modules defines module common space through which liquid heat transfer fluid flows during charging of the battery when the battery is removed from the aircraft and through which air as a heat transfer fluid flows during discharge of the battery, as during flight. The module common space also defines a combustion conduit to convey heated air and products of combustion safely outside the battery in the event of a cell fire during flight. The removable battery frame is a structural component of the aircraft.

Apparatus, system and method for a removable aircraft battery

A compound aircraft includes a convertible thruster that pivots between an anti-torque position, a forward thrust position, and intermediate positions. A pilot has two inceptors to control thruster rotor pitch in the anti-torque and forward thrust positions. A mixer mechanically blends the signals from the two inceptors during transition between the anti-torque and forward thrust positions. A transfer rod coaxial with the pivot axis of the convertible thruster conveys convertible thruster pitch commands from the pilot to a pitch control actuator. The pitch control actuator may be located partially within the rotor of an electric motor that rotates the convertible thruster rotor. The electric motor and pitch control actuator are unitary. Both the electric motor and pitch control actuator pivot with the convertible thruster. The pitch actuator output shaft is coaxial to and disposed within a hollow electric motor output shaft.

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Swarthmore, PA, United States of America

Luigi U Ricci Moretti