Abstract: According to one implementation of the present disclosure, a stabilizer of an aircraft includes an energy attenuating portion. The energy attenuating portion includes first and second edge sections separated by an adaptable section. The adaptable section may be rigid in a first range of directions and compressible in a second range of directions.

Abstract: According to one implementation of the present disclosure, a stabilizer of an aircraft includes an energy attenuating portion. The energy attenuating portion includes first and second edge sections separated by an adaptable section. The adaptable section may be rigid in a first range of directions and compressible in a second range of directions.

Abstract: According to one implementation of the present disclosure, a stabilizer of an aircraft includes an energy absorbing assembly. The energy absorbing assembly includes first and second portions and a retractable section. The retractable section may be at least partially affixed to the first portion and is configured to enable displacement of the second portion of the stabilizer with respect to the first portion.

Abstract: According to one implementation of the present disclosure, a stabilizer of an aircraft includes an energy attenuating portion. The energy attenuating portion includes first and second edge sections separated by an adaptable section. The adaptable section may be rigid in a first range of directions and compressible in a second range of directions.

Abstract: The present invention includes a system and method for slowing the rotation of a rotor using, for example, rotor brake system for a rotorcraft comprising: one or more generators connected to a main rotor gearbox; an electric distributed anti-torque system mounted on a tail boom of the rotorcraft comprising two or more electric motors connected to the one or more generators, wherein the two or more electric motors are connected to one or more blades; and wherein a rotation of the rotor is slowed by placing a drive load on the main rotor gearbox with the one or more generators to bleed the mechanical power from rotor into electrical power via the two or more electric motors, wherein the electric distributed anti-torque system generates thrust in opposing directions.

Abstract: A variable-speed gearbox for a tiltrotor with fixed engine and rotating proprotor includes an input shaft coupled to the respective fixed engine, an output shaft coupled to the respective proprotor; a high-speed clutch integrated into a high-speed gear train, the high-speed gear train having an input coupled to the input shaft and an output coupled to the output shaft; and a low-speed clutch integrated into a low-speed gear train, the low-speed gear train having an input coupled to the input shaft and an output coupled to the output shaft. The high-speed clutch and the low-speed clutch can be freewheeling clutches capable of disconnecting the output and the input of the respective gear train of the high and low-speed gear trains in an overrunning condition when the output rotates faster than the input of the respective gear train. The low-speed clutch can be permanently engaged. In accordance to some embodiments the variable-speed gearboxes may include an accessory drive.

Abstract: According to one implementation of the present disclosure, a stabilizer of an aircraft includes an energy attenuating portion. The energy attenuating portion includes first and second edge sections separated by an adaptable section. The adaptable section may be rigid in a first range of directions and compressible in a second range of directions.

Abstract: According to one implementation of the present disclosure, a stabilizer of an aircraft includes an energy absorbing assembly. The energy absorbing assembly includes first and second portions and a retractable section. The retractable section may be at least partially affixed to the first portion and is configured to enable displacement of the second portion of the stabilizer with respect to the first portion.

Abstract: A variable-speed gearbox for a tiltrotor with fixed engine and rotating proprotor includes an input shaft coupled to the respective fixed engine, an output shaft coupled to the respective proprotor; a high-speed clutch integrated into a high-speed gear train, the high-speed gear train having an input coupled to the input shaft and an output coupled to the output shaft; and a low-speed clutch integrated into a low-speed gear train, the low-speed gear train having an input coupled to the input shaft and an output coupled to the output shaft. The high-speed clutch and the low-speed clutch can be freewheeling clutches capable of disconnecting the output and the input of the respective gear train of the high and low-speed gear trains in an overrunning condition when the output rotates faster than the input of the respective gear train. The low-speed clutch can be permanently engaged. In accordance to some embodiments the variable-speed gearboxes may include an accessory drive.

Abstract: The present invention includes a system and method for slowing the rotation of a rotor using, for example, rotor brake system for a rotorcraft comprising: one or more generators connected to a main rotor gearbox; an electric distributed anti-torque system mounted on a tail boom of the rotorcraft comprising two or more electric motors connected to the one or more generators, wherein the two or more electric motors are connected to one or more blades; and wherein a rotation of the rotor is slowed by placing a drive load on the main rotor gearbox with the one or more generators to bleed the mechanical power from rotor into electrical power via the two or more electric motors, wherein the electric distributed anti-torque system generates thrust in opposing directions.

Abstract: An electrical generator assembly including a central rotatable shaft (12) having a winding assembly (26) mounted thereto for rotation therewith, a rotatable permanent magnet assembly (28) surrounding the winding assembly (26) adjacent thereto and in use cooperating therewith to induce a current in the winding assembly (26), and a drive system (38, 138, 238, 338, 438) drivingly interconnecting the central shaft (12) and the permanent magnet assembly (28), the drive system (38, 138, 238, 338, 438) defining a relative rotational speed between the permanent magnet assembly (28) and the winding assembly (26) which is greater than an absolute rotational speed of the winding assembly (26). A method of powering an electrical system (22) on a rotating rotor blade (18) supported by a rotating mast (12) is also discussed.

Abstract: An electrical generator assembly including a central rotatable shaft (12) having a winding assembly (26) mounted thereto for rotation therewith, a rotatable permanent magnet assembly (28) surrounding the winding assembly (26) adjacent thereto and in use cooperating therewith to induce a current in the winding assembly (26), and a drive system (38, 138, 238, 338, 438) drivingly interconnecting the central shaft (12) and the permanent magnet assembly (28), the drive system (38, 138, 238, 338, 438) defining a relative rotational speed between the permanent magnet assembly (28) and the winding assembly (26) which is greater than an absolute rotational speed of the winding assembly (26). A method of powering an electrical system (22) on a rotating rotor blade (18) supported by a rotating mast (12) is also discussed.