Abstract: A clutch has an inner race, an outer race spaced from the inner race and forming a radial cavity between the races, and a plurality of sprags disposed in the radial cavity. The sprags have a different coefficient of thermal expansion (CTE) from the inner race, the outer race, or both races, and a sprag cage retains the sprags at a uniform spacing within the radial cavity. When the clutch is at a first temperature, a gap exists between the sprags and the inner race, between the sprags and the outer race, or between the sprags and both races, and the clutch is disengaged. When the clutch is at a second temperature the sprags are in contact with both the races, and the clutch is engaged.

Abstract: An adhesive bond test resonance array provides inspection of adhesively bonded composite laminate structures with improved productivity and higher reliability. A holder has multiple slots arranged in a two-dimensional array for holding transducers in respective slots. The holder is adapted to position a probe end of each of the transducers adjacent a component for scanning and has a material hardness adapted for enabling flexing while scanning curved composite parts. A fluid channel is adapted for delivering a couplant to the probe end of the transducers such that the couplant is automatically delivered during scanning of the component to inspect bond integrity.

Abstract: A field deployable infrared imaging (FDIR) system and method for inspecting a composite component comprises a hand-held long-wave IR camera to capture a thermal image of the composite component, wherein the camera has an adjustable temperature control that captures an image with a 10 degree working range, a frame capture rate of at least 1 second for a length of time of not less than 90 seconds; and a processor for post-processing the thermal image using a second order derivative algorithm wherein the post-processed thermal image shows the defect better than the captured infrared image, and detects the one or more defects in the composite component.

Abstract: Systems and methods include providing an aircraft with a ducted rotor assembly. The ducted rotor assembly includes a housing having a duct, a rotor drive mechanism coupled to a rotor system, and a plurality of stators that both structurally support the rotor drive mechanism within the duct of the housing and carry a fluid through internal fluid passages in the plurality of stators to provide cooling to the rotor drive mechanism. Some of the stators carry fluid to the rotor drive mechanism, where the fluid absorbs heat from the rotor drive mechanism, and some of the stators carry fluid away from the rotor drive mechanism. The rotor system generates an airflow over the stators carrying fluid away from the rotor drive mechanism to effect transfer between the fluid and the airflow.

Abstract: A modal restraint system for an occupant of a seat of an aircraft having a mechanical failure sensor includes a strap feeder unit and a strap selectively retractable into and extendable from the strap feeder unit. The strap is positionable adjacent to the occupant. The strap feeder unit is adapted to switch between a plurality of modes including an unfixed mode and a fixed mode. The strap is extendable from and retractable into the strap feeder unit in the unfixed mode. The strap is substantially unextendable from the strap feeder unit in the fixed mode. The strap feeder unit is in the unfixed mode by default. The strap feeder unit is operable to switch to the fixed mode in response to a precautionary event including detection of an aircraft mechanical failure by the mechanical failure sensor, thereby reducing freedom of movement of the occupant relative to the seat.

Abstract: A versatile door system for an aircraft includes forward and aft door assemblies. The forward door assembly includes a forward hingeable door hingeably coupled to the airframe proximate a forward location of an aircraft opening and a forward slidable door slidably coupled to the forward hingeable door. The aft door assembly includes an aft hingeable door hingeably coupled to the airframe proximate an aft location of the aircraft opening and an aft slidable door slidably coupled to the aft hingeable door. In a closed configuration, the forward hingeable door, the forward slidable door, the aft hingeable door and the aft slidable door are securably disposed within the aircraft opening. In operation, the forward hingeable door, the forward slidable door, the aft hingeable door and the aft slidable door are individually operable to collectively provide access to a selectable width of the aircraft opening.

Abstract: A package delivery system uses unmanned aircraft operable to transition between thrust-borne lift in a VTOL configuration and wing-borne lift in a forward flight configuration. Each of the aircraft includes an airframe having at least one wing with a distributed thrust array coupled to the airframe. The distributed thrust array includes a plurality of propulsion assemblies configured to provide vertical thrust in the VTOL configuration and a plurality of propulsion assemblies configured to provide forward thrust in the forward flight configuration. A package delivery module is coupled to the airframe. A control system is operably associated with the distributed thrust array and the package delivery module. The control system is configured to individually control each of the propulsion assemblies and control package release operations of the package delivery module. The system includes a ground station configured to remotely communicate with the control systems of the aircraft during package delivery missions.

Abstract: A method of autonomous flight path planning for a group of cooperating aircraft operating in formation includes: receiving information related to obstructions that interfere with an aircraft of the group continuing on a flight path; calculating a velocity obstacle for each obstruction; calculating a plurality of candidate velocities outside of the velocity obstacles; selecting a first velocity from the candidate velocities and operating a leader of the group at the first velocity; calculating, based upon keeping a follower aircraft in formation, a second velocity for the follower; determining whether the second velocity is inside one of the velocity obstacles; operating the follower at the second velocity when the second velocity is outside the velocity obstacles; and calculating a revised velocity that is outside of the velocity obstacles and operating the follower at the revised velocity when the second velocity is inside one of the velocity obstacles.

Abstract: The present invention achieves technical advantages as a vehicle cabin, comprising a floor system formed of removable and reconfigurable floor segments extending from a vehicle frame, and a ceiling system formed of removable and reconfigurable ceiling segments disposed in the ceiling of the vehicle cabin. Floor segments that can be positioned to form a floor channel, therebetween. A fixture interface adapted to releasably secure a fixture to the floor system. The fixture can be slidably repositioned within the vehicle along the floor channel. One of the ceiling segments includes one or more of a lighting module, a ventilation outlet, a ventilation inlet, a display screen, or a touch control panel. The ceiling segments can be hexagonal.

Abstract: A bimodal tuned vibration absorber includes a first beam arranged lengthwise in a longitudinal direction. The first beam has an attachment mechanism adapted for mechanically coupling the first beam to a structure. A second beam is arranged lengthwise in a transverse direction, perpendicular to the longitudinal direction. The second beam is mechanically coupled to a first end of the first beam via a first connector. A third beam is arranged lengthwise in the transverse direction and is mechanically coupled to a second end of the first beam, opposite the first end, via a second connector. A two-mode tuned vibration absorber includes a first beam aligned longitudinally with a second beam. A connector is aligned longitudinally and disposed between the first beam and the second beam for mechanically coupling the first beam with the second beam. The connector is adapted for enhancing the bending mode of the two-mode tuned vibration absorber.

Abstract: A method and system to measure a parameter associated with a component, device, or system with a specified accuracy, including: providing one or more sensors operably disposed to detect the parameter; obtaining a coarse measurement of the parameter within a first range using the one or more sensors, wherein the first range includes minimum and maximum values for the parameter; obtaining a fine measurement of the parameter within a second range using the one or more sensors, wherein the second range is smaller than the first range and has a specified ratio to the first range that provides the specified accuracy; determining a current value of the parameter by combining the coarse and fine measurements; and providing the current value of the parameter to a communications interface, a storage device, a display, a control panel, a processor, a programmable logic controller, or an external device.

Abstract: An advancing blade concept rotorcraft includes an airframe and a pylon assembly subject to vibration. The pylon assembly includes a dual rotor system having coaxially disposed top and bottom rotor assemblies that counter rotate relative to one another. The advancing blade concept rotorcraft includes a vibration isolation system including at least one pylon link coupled to the airframe and the pylon assembly. The pylon link includes a Liquid Inertia Vibration Eliminator unit operable to reduce transmission of the pylon assembly vibration to the airframe. The advancing blade concept rotorcraft includes active force generators adjacent to the pylon assembly. The active force generators include a first active force generator producing a force in a first direction and a second active force generator producing a force in a second direction to counteract multidirectional oscillations of the pylon assembly, thereby reducing vibration of the advancing blade concept rotorcraft.

Abstract: An example of a hub for a tail rotor includes a body configured to couple to a mast of a rotor system, a trunnion disposed within the body, first and second shafts disposed on opposite sides of the trunnion, first and second end plates secured to the body, and first and second end bearings, the first end bearing disposed between the first shaft and the first end plate and the second end bearing disposed between the second shaft and the second end plate.

Abstract: A landing gear assembly for an aircraft includes a landing member and an actuation mechanism coupled to the landing member. The actuation mechanism is configured to selectively actuate the landing member into a first landing position and a second landing position. The landing member is configured to support the aircraft in either the first landing position or the second landing position.

Abstract: A vibration attenuator for an aircraft has first and second coaxial spinners configured for rotation about a mast axis and relative to a rotor. Upper and lower weights of each spinner are spaced radially from the axis and positioned 180 degrees from each other about the axis. The weights of each spinner are spaced from each other a distance parallel to the mast axis, each weight rotating about the mast axis in a different plane. The spinners rotate together relative to the rotor at a selected angular rate and are selectively rotatable relative to each other between a minimum-moment configuration, in which the upper weight of each spinner is angularly aligned with the lower weight of the other spinner, and a maximum-moment configuration, in which the upper weights are angularly aligned and the lower weights are angularly aligned, producing a whirling moment about the mast axis as the spinners rotate.

Abstract: A bearing system includes an inboard bearing assembly and an outboard bearing assembly. The inboard bearing assembly includes an inboard fitting and an inboard race. The inboard fitting includes a plate with a convex mating surface and a first aperture formed through the plate for receiving a blade root of a rotor blade. The inboard race comprising a concave mating surface configured to receive the convex mating surface a second aperture formed the inboard race. The outboard bearing assembly includes an outboard bearing assembly comprising an outboard fitting having an aperture formed therethrough for receiving the blade root of the rotor blade.

Abstract: An example of a collapsible pylon for a drone aircraft includes a bore extending through a length of a barrel, a first and a second flex-pin bore formed through a wall of the barrel, a first arm slidably positioned within a first end of the bore, a first flex pin disposed on the first arm to engage the first flex-pin bore, a second arm slidably positioned within a second end of the bore, and a second flex pin disposed on the second arm to engage the second flex-pin bore.

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 compound helicopter includes a fuselage including a fuselage airframe, a translational thrust system coupled to the fuselage airframe and a pylon assembly subject to vibration. The pylon assembly includes a transmission and a rotor system having a main rotor assembly. The compound helicopter also includes a main rotor vibration isolation system including a plurality of augmented liquid inertia vibration eliminator units each having an isolation frequency and each coupled between the fuselage airframe and the pylon assembly to reduce transmission of the pylon assembly vibration to the fuselage airframe at the isolation frequency. Each augmented liquid inertia vibration eliminator unit includes at least one active tuning element movable to tune the isolation frequency thereof.

Abstract: A rotorcraft comprising a rotor blade designed to flap about a hinge point, a measurement system designed to measure blade flapping, and a processing system designed to alter blade flapping measurements. The processing system further comprises a correction process to alter a blade flapping measurement dependent on rotor RPM or rotor torque.