Abstract: An aircraft is described and includes a fuselage; wings attached to the fuselage; and a torque box within the fuselage, the torque box including a side panel, the side panel comprising a composite laminate material including a plurality of stiffening beads integrated therewith. The plurality of stiffening beads may be integrated with the side panel and extend parallel to one another.

Abstract: An aircraft is described and includes a fuselage; wings attached to the fuselage; and a torque box within the fuselage, the torque box including a side panel, the side panel comprising a composite laminate material including a plurality of stiffening beads integrated therewith.

Abstract: An aircraft is described and includes a fuselage; wings attached to the fuselage; and a torque box within the fuselage, the torque box including a side panel, the side panel comprising a composite laminate material including a plurality of stiffening beads integrated therewith.

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: A method of fabricating a panel includes laying up a first laminate on a tooling surface, laying a first layer of thermoplastic on an inner surface of the first laminate, laying a large cell carbon core on the first layer of thermoplastic, laying a second layer of thermoplastic across the large cell carbon core, laying a second laminate on the second layer of thermoplastic, creating a sealed core pocket by bonding the edges of the first and second layers of the thermoplastic surrounding a perimeter of the core, increasing pressure within the core pocket, increasing pressure on the outer surface of the second laminate, heating the panel to a desired curing temperature, and maintaining the increased pressures and temperature for a desired curing duration.

Abstract: A folding step system includes a housing forming an interior space and a step comprising a step surface. The step is movable between a stowed configuration in which substantially all of the step surface is disposed within the interior space and a deployed configuration in which at least a portion of the step surface is disposed outside of the interior space and at least a portion of the step surface is disposed within the interior space.

Abstract: An aircraft includes a fuselage having a former therein and a work platform system. The work platform system includes a platform that is moveable between a stowed configuration and a deployed configuration. The work platform system also has a hinge pin received by the platform. A platform stop is carried by the former and configured to inhibit rotation of the platform about the hinge pin when the platform is in the deployed configuration. The hinge pin is carried by the former.

Abstract: A tail rotor assembly coupled to a tailboom of a helicopter includes a tail rotor gearbox having top, bottom and aft sides and a shroud surrounding the tail rotor gearbox. The shroud includes a shroud airframe having top and bottom portions. The tail rotor assembly includes a tail rotor gearbox support assembly configured to support the tail rotor gearbox within the shroud. The tail rotor gearbox support assembly includes a support column coupling the aft side of the tail rotor gearbox between the top and bottom portions of the shroud airframe, an upper support crossbar coupling the top side of the tail rotor gearbox between the support column and the tailboom airframe and a lower support crossbar coupling the bottom side of the tail rotor gearbox between the support column and the tailboom airframe.

Abstract: One embodiment includes a rotary aircraft, including: a rotary propulsion system; a body; and a pair of wings connected on opposite sides of the body, wherein each of the wings includes a flap rotatably connected to a trailing edge thereof and configured to rotate downward relative to the wing during low speed and stationary flight of the aircraft, and to rotate upward relative to the wing during high-speed flight of the aircraft.

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: 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 rotary aircraft, including: a rotary propulsion system; a body; and a pair of wings connected on opposite sides of the body, wherein each of the wings includes a flap rotatably connected to a trailing edge thereof and configured to rotate downward relative to the wing during low speed and stationary flight of the aircraft, and to rotate upward relative to the wing during high-speed flight of the aircraft.

Abstract: A tail rotor assembly coupled to a tailboom of a helicopter includes a tail rotor gearbox having top, bottom and aft sides and a shroud surrounding the tail rotor gearbox. The shroud includes a shroud airframe having top and bottom portions. The tail rotor assembly includes a tail rotor gearbox support assembly configured to support the tail rotor gearbox within the shroud. The tail rotor gearbox support assembly includes a support column coupling the aft side of the tail rotor gearbox between the top and bottom portions of the shroud airframe, an upper support crossbar coupling the top side of the tail rotor gearbox between the support column and the tailboom airframe and a lower support crossbar coupling the bottom side of the tail rotor gearbox between the support column and the tailboom airframe.

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 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 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 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 retractable landing gear system configured to contour an aircraft fuselage includes a landing wheel having an axle, a wheel rotation strut assembly coupling the landing wheel to the aircraft fuselage and an actuation strut assembly configured to move the wheel rotation strut assembly between various positions including a deployed position and a stowed position. The axle of the landing wheel is pivotably coupled to a distal end of the wheel rotation strut assembly and configured to pivot relative to the wheel rotation strut assembly as the actuation strut assembly moves the wheel rotation strut assembly between the deployed and stowed positions such that the landing wheel generally contours the aircraft fuselage when the wheel rotation strut assembly is in the stowed position.