Abstract: A clutch that has a synchronizer for matching a rotational velocity of a drive input with a rotational velocity of a driven output prior to engagement of a locking mechanism.

Abstract: A seal system for coaxially aligned shafts includes an input shaft and an output shaft coaxially aligned with the input shaft. The seal system includes a seal adapter support housing coupled to the output shaft and a seal positioned between an end of the input shaft and an end of the seal adapter support housing. The input shaft is configured to rotate at a speed that is different than a speed of the output shaft.

Abstract: A rotorcraft includes a plurality of fan assemblies. Each fan assembly of the plurality of fan assemblies includes a drivetrain having a gearbox with an input shaft and a mast coaxially aligned with the input shaft, and a plurality of electric motors coupled to the input shaft. Each electric motor of the plurality of electric motors is coupled to the input shaft via a sprag clutch.

Abstract: A planetary gear system includes a planetary gear carrier having three or more posts extending from the planetary gear carrier, each post having a hardened exterior surface, and a planet pinion gear in contact with the hardened exterior surface of each post.

Abstract: A gearbox system for a rotorcraft includes a gearbox housing, an oil pump receiving bore formed into the gearbox housing and having formed therein a first opening having a first diameter and a second opening, and an oil pump positioned within the oil pump receiving bore. The second opening is bounded by a lip that extends radially into the second opening, the second opening having a second diameter that is smaller than the first diameter.

Abstract: A clutch that has a synchronizer for matching a rotational velocity of a drive input with a rotational velocity of a driven output prior to engagement of a locking mechanism.

Abstract: A rotor assembly configured to increase the stiffness of a rotor mast. The rotor assembly includes the rotor mast, a rotor hub, a mast nut, a mast bearing, and a cuff disposed between the mast nut and the mast bearing. The cuff is captured and compressed between the mast nut and the inner race of the mast bearing along an uninterrupted load path that extends between the mast nut and the mast bearing.

Abstract: A propulsion assembly for a rotorcraft includes a mast including a distal ridge and a proximal ridge forming a retaining pocket therebetween, a raceway receivable by the retaining pocket to form a press fit between the mast and the raceway and a mast bearing assembly including a plurality of bearings facing the mast to engage the raceway. The distal and proximal ridges are operable to reduce axial motion of the raceway along the mast, thereby securing the raceway in the retaining pocket.

Abstract: A mast lockout system for a tiltrotor aircraft having a proprotor assembly. The system includes a mast coupled to and rotatable with the proprotor assembly. A proprotor gearbox having a proprotor gearbox housing is operable to transmit torque and rotation energy to the mast. A lock assembly has first and second lock members. The first lock member is coupled to and rotatable with the mast. The second lock member is coupled to the proprotor gearbox housing. The lock assembly has a first position in which the first and second lock members are disengaged, thereby allowing rotation of the proprotor assembly. The lock assembly has a second position in which the first and second lock members are engaged, thereby preventing rotation of the proprotor assembly. The lock assembly is actuatable between the first and second positions.

Abstract: A mast lockout system for a tiltrotor aircraft having a proprotor assembly. The system includes a mast coupled to and rotatable with the proprotor assembly. A proprotor gearbox having a proprotor gearbox housing is configured to transmit torque and rotation energy to the mast. A lock assembly has first and second lock members. The first lock member is coupled to the mast between first and second mast bearings and configured to rotate with the mast. The second lock member is coupled to the proprotor gearbox housing. The lock assembly has a first position in which the first and second lock members are disengaged, thereby allowing rotation of the mast. The lock assembly has a second position in which the first and second lock members are engaged, thereby preventing rotation of the mast. The lock assembly is actuatable between the first and second positions.

Abstract: A swashplate assembly includes: a mounting sleeve configured for coupling to and around an upper portion of a gearbox, wherein the mounting sleeve extends downwards from the upper portion of the gearbox; a tilt sleeve coupled to the mounting sleeve, wherein the tilt sleeve has a curved exterior surface; a non-rotating swashplate ring positioned around the tilt sleeve, wherein the non-rotating swashplate ring has a first set of pitch control connectors and an anti-rotation connector; a rotating swashplate ring rotatable about the non-rotating swashplate ring, wherein the rotating swashplate ring has a second set of pitch control connectors and a drive link connector; and a first bearing system mounted between the non-rotating swashplate ring and the rotating swashplate ring.

Abstract: A power system for an aircraft includes a plurality of power consumers each operable to consume power in a range from zero to maximum power demand and collectively capable of consuming a combined maximum power demand, a power source operable to output power to the power consumers and a power allocation system operable to allocate power from the power source to the power consumers based on an operational parameter of the aircraft. The power allocated by the power allocation system is less than the combined maximum power demand of the power consumers, thereby allowing the power source to have a maximum power output less than the combined maximum power demand of the power consumers.

Abstract: A propulsion assembly for a rotorcraft includes a mast including a distal ridge and a proximal ridge forming a retaining pocket therebetween, a raceway receivable by the retaining pocket to form a press fit between the mast and the raceway and a mast bearing assembly including a plurality of bearings facing the mast to engage the raceway. The distal and proximal ridges are operable to reduce axial motion of the raceway along the mast, thereby securing the raceway in the retaining pocket.

Abstract: A planetary gear system includes a planetary gear carrier having three or more posts extending from the planetary gear carrier, each post having a hardened exterior surface, and a planet pinion gear in contact with the hardened exterior surface of each post.

Abstract: A ring gear includes a ring having one or more sets of inwardly facing teeth, a circumferential flange extending outward from the ring, and the flange is mounted between a first housing and a second housing. In addition, the flange protrudes into an ambient air outside the first housing and second housing.

Abstract: A mast lockout system for a tiltrotor aircraft having a proprotor assembly. The system includes a mast coupled to and rotatable with the proprotor assembly. A proprotor gearbox having a proprotor gearbox housing is configured to transmit torque and rotation energy to the mast. A lock assembly has first and second lock members. The first lock member is coupled to the mast between first and second mast bearings and configured to rotate with the mast. The second lock member is coupled to the proprotor gearbox housing. The lock assembly has a first position in which the first and second lock members are disengaged, thereby allowing rotation of the mast. The lock assembly has a second position in which the first and second lock members are engaged, thereby preventing rotation of the mast. The lock assembly is actuatable between the first and second positions.

Abstract: A mast lockout system for a tiltrotor aircraft having a proprotor assembly. The system includes a mast coupled to and rotatable with the proprotor assembly. A proprotor gearbox having a proprotor gearbox housing is operable to transmit torque and rotation energy to the mast. A lock assembly has first and second lock members. The first lock member is coupled to and rotatable with the mast. The second lock member is coupled to the proprotor gearbox housing. The lock assembly has a first position in which the first and second lock members are disengaged, thereby allowing rotation of the proprotor assembly. The lock assembly has a second position in which the first and second lock members are engaged, thereby preventing rotation of the proprotor assembly. The lock assembly is actuatable between the first and second positions.

Abstract: A power system for an aircraft includes a plurality of power consumers each operable to consume power in a range from zero to maximum power demand and collectively capable of consuming a combined maximum power demand, a power source operable to output power to the power consumers and a power allocation system operable to allocate power from the power source to the power consumers based on an operational parameter of the aircraft. The power allocated by the power allocation system is less than the combined maximum power demand of the power consumers, thereby allowing the power source to have a maximum power output less than the combined maximum power demand of the power consumers.

Abstract: A clutch that has a synchronizer for matching a rotational velocity of a drive input with a rotational velocity of a driven output prior to engagement of a locking mechanism.

Abstract: An engine reduction gear system includes at least two self-contained, independent engine reduction gearboxes, each capable of connecting to an aircraft engine. Each of the engine reduction gearboxes provides redundant, reduced speed to a main rotor gearbox via a shaft.