Abstract: A tiltrotor aircraft is described and includes a rotor system, a pylon coupled to the rotor system, a spindle coupled to the pylon, an actuator arm coupled to the spindle, and an actuator. The actuator can cause the actuator arm to rotate, thereby causing the spindle to rotate the pylon and the rotor system. In an example, the actuator is in front of a forward spar of the wing of the tiltrotor aircraft and the actuator arm is about one-half (0.5) of an inch to about five (5) inches from the wing.

Abstract: One embodiment includes a multistage infrared suppression exhaust system for an aircraft, including: a stage one including a first exhaust conduit to receive a first exhaust air flow at a first temperature-pressure product T1P1, a second exhaust conduit to receive a second exhaust air flow at a second temperature-pressure product T2P2, and a flow integrator mechanically configured to mix the first exhaust air flow with the second exhaust air flow in an integration chamber while preventing back flow into the second exhaust conduit; and a stage two including a stage two cooling airflow to cool the mixed first and second exhaust air flows.

Abstract: A system is described and includes a rack for carrying payload disposed in payload bay; a rack extension assembly for affecting linear displacement of the rack between a first position in which the rack is stowed within the payload bay and a second position in which the rack is supported outside the payload bay; a payload actuator system for selectively causing the rack extension assembly to move the rack between the first and second positions; a payload bay door; and a door actuator system for selectively opening and closing the payload bay door.

Abstract: A tiltrotor aircraft includes a propulsion system with a fixed engine and a rotatable proprotor. The engine is located below the wing of the tiltrotor aircraft, and the rotatable proprotor assembly is mounted on the top surface of the wing. The engine and proprotor assembly are connected via a series of one or more gearboxes that route the engine output from the engine to the proprotor.

Abstract: A system is described and includes a rack for carrying payload disposed in a payload bay; and a payload extension assembly for affecting linear translation of the rack between a first position in which the rack is fully retracted within the payload bay and a second position in which the payload extension assembly is fully extended and the rack is supported outside the payload bay. The payload extension assembly comprises forward and aft tracks respectively attached to forward and aft walls of the payload bay; a first stage for providing linear translation of the rack relative to the forward and aft tracks; and a second stage for providing linear translation of the rack relative to the first stage. The system further comprises a payload actuator system for selectively causing the rack extension assembly to move the rack between the first and second positions.

Abstract: One example of a tiltrotor aircraft includes a rotor system, a pylon coupled to the rotor system, a spindle coupled to the pylon, an actuator arm coupled to the spindle, and an actuator. The actuator can cause the actuator arm to rotate, thereby causing the spindle to rotate the pylon and the rotor system. In an example, the actuator is in front of a forward spar of the wing of the tiltrotor aircraft and the actuator arm is about one-half (0.5) of an inch to about five (5) inches from the wing.

Abstract: One embodiment includes a multistage infrared suppression exhaust system for an aircraft, including: a stage one including a first exhaust conduit to receive a first exhaust air flow at a first temperature-pressure product T1P1, a second exhaust conduit to receive a second exhaust air flow at a second temperature-pressure product T2P2, and a flow integrator mechanically configured to mix the first exhaust air flow with the second exhaust air flow in an integration chamber while preventing back pressure into the second exhaust conduit; and a stage two including a stage two cooling airflow to cool the mixed first and second exhaust air flows.

Abstract: A tiltrotor aircraft includes a propulsion system with a fixed engine and a rotatable proprotor. The engine is located on the top surface of the wing of the tiltrotor aircraft, and the rotatable proprotor assembly is also mounted on the top surface of the wing. The engine and proprotor assembly are connected via a series of one or more gearboxes that route the engine output from the engine to the proprotor.

Abstract: A system is described and includes at least one track attached to an upper interior surface of a payload bay and extending along a bottom surface of a vehicle structure external to the payload bay, wherein the track comprises a horizontal flange; a rack moveably connected to the at least one track via at least one carrier assembly; and a payload actuator system for selectively extending the rack from the payload bay along the at least one track to a position from which payload carried by the rack may be safely deployed and retracting the rack into the payload bay along the at least one track.

Abstract: A system is described and includes a rack for carrying payload disposed in payload bay; a rack extension assembly for affecting linear displacement of the rack between a first position in which the rack is stowed within the payload bay and a second position in which the rack is supported outside the payload bay; a payload actuator system for selectively causing the rack extension assembly to move the rack between the first and second positions; a payload bay door; and a door actuator system for selectively opening and closing the payload bay door.

Abstract: A system is described and includes a rack for carrying payload disposed in a payload bay; and a payload extension assembly for affecting linear translation of the rack between a first position in which the rack is fully retracted within the payload bay and a second position in which the payload extension assembly is fully extended and the rack is supported outside the payload bay. The payload extension assembly comprises forward and aft tracks respectively attached to forward and aft walls of the payload bay; a first stage for providing linear translation of the rack relative to the forward and aft tracks; and a second stage for providing linear translation of the rack relative to the first stage. The system further comprises a payload actuator system for selectively causing the rack extension assembly to move the rack between the first and second positions.

Abstract: A system is described and includes at least one track attached to an upper interior surface of a payload bay and extending along a bottom surface of a vehicle structure external to the payload bay, wherein the track comprises a horizontal flange; a rack moveably connected to the at least one track via at least one carrier assembly; and a payload actuator system for selectively extending the rack from the payload bay along the at least one track to a position from which payload carried by the rack may be safely deployed and retracting the rack into the payload bay along the at least one track.

Abstract: An aircraft including a nacelle disposed at a fixed location relative a wing member; a proprotor housing coupled to the nacelle, the proprotor housing configured to selectively rotate between a horizontal orientation and a non-horizontal orientation; a door pivotably coupled to the proprotor housing; and a linkage to connect the door and the nacelle, the linkage configured to move with the door from a closed position when the proprotor housing is in a horizontal orientation to an open position when the proprotor housing is in a non-horizontal orientation. In some embodiments, there can be a hinge member for hingedly coupling the door to the proprotor and/or nacelle. In other embodiments, the door includes a flexure portion. In some embodiments, the nacelle includes a plurality of doors. In other embodiments, proprotor includes a forward portion and a stationary aft portion; wherein the forward portion is configured to selectively pivot.

Abstract: A tiltrotor aircraft includes a rotor system, a pylon coupled to the rotor system, a spindle coupled to the pylon, an actuator arm coupled to the spindle, and an actuator. The actuator can cause the actuator arm to rotate, thereby causing the spindle to rotate the pylon and the rotor system. The actuator is in front of a forward spar of the wing of the tiltrotor aircraft and the actuator arm is about one-half (0.5) of an inch to about five (5) inches from the wing.

Abstract: One example of a tiltrotor aircraft includes a rotor system, a pylon coupled to the rotor system, a spindle coupled to the pylon, an actuator arm coupled to the spindle, and an actuator. The actuator can cause the actuator arm to rotate, thereby causing the spindle to rotate the pylon and the rotor system. In an example, the actuator is in front of a forward spar of the wing of the tiltrotor aircraft and the actuator arm is about one-half (0.5) of an inch to about five (5) inches from the wing.

Abstract: An aircraft includes a first rotor assembly, a second rotor assembly, and a rotor phase angle control system. The system includes a phase adjustor operably associated with the first rotor assembly and the second rotor assembly. The method includes sensing vibrations exerted on the aircraft and offsetting a phase angle of the first rotor assembly and the second rotor assembly to minimize the vibrations.

Abstract: An aircraft includes a first rotor assembly, a second rotor assembly, and a rotor phase angle control system. The system includes a phase adjustor operably associated with the first rotor assembly and the second rotor assembly. The method includes sensing vibrations exerted on the aircraft and offsetting a phase angle of the first rotor assembly and the second rotor assembly to minimize the vibrations.