Abstract: A system and method to inspect flaws associated with a part. The system includes a first image capturing device configured to capture a first set of images of the part and a computer operably associated with first image capturing device and configured to receive and analyze the first set of images. The method includes treating the part with a magnetic particle and fluorescent penetrant processing, capturing a first set of images of an outer surface of the part with the first image capturing device, and identifying a part defect with an algorithm associated with the computer.

Abstract: A method for calculating torque through a rotor mast of a propulsion system of a tiltrotor aircraft includes receiving the torque being applied through a quill shaft of the rotorcraft. The quill shaft is located between a fixed gearbox and a spindle gearbox, and the spindle gearbox is rotatable about a conversion access. The torque through the rotor mast is determined by using the torque through the quill shaft and the efficiency loss value between the quill shaft and the rotor mast.

Abstract: A pylon assembly for a tiltrotor aircraft includes a fixed pylon having an outboard end. A rotor assembly is rotatably coupled to the fixed pylon and is operable to rotate between a generally vertical orientation in a vertical takeoff and landing mode and a generally horizontal orientation in a forward flight mode. The rotor assembly includes a proprotor operable to produce a generally vertical slipstream in the vertical takeoff and landing mode and a generally horizontal slipstream in the forward flight mode. A wing extension is rotatably coupled to the outboard end of the fixed pylon. The wing extension is operable to rotate generally with the rotor assembly such that a minimal dimension of the wing extension remains in the slipstream of the proprotor.

Abstract: A tri-wing aircraft includes a fuselage having a longitudinally extending fuselage axis. Three wings extend generally radially outwardly from the fuselage axis and are circumferentially distributed generally uniformly about the fuselage at approximately 120-degree intervals. The wings have airfoil cross-sections including first and second surfaces having chordwise channels therebetween. A distributed propulsion system includes a plurality of propulsion assemblies. Each propulsion assembly includes a variable thrust cross-flow fan disposed within one of the chordwise channels of one of the wings. At least two variable thrust cross-flow fans are disposed within the chordwise channels of each of the wings. A flight control system is operably associated with the distributed propulsion system such that the flight control system and the distributed propulsion system are operable to generate a triaxial dynamic thrust matrix.

Abstract: A tail sitter aircraft includes a fuselage having a forward portion and an aft portion. The forward portion of the fuselage includes first and second rotor stations. A first rotor assembly is positioned proximate the first rotor station. A second rotor assembly is positioned proximate the second rotor station. A tailboom assembly extends from the aft portion of the fuselage. The tailboom assembly includes a plurality of landing members. In a vertical takeoff and landing mode of the aircraft, the first and second rotor assemblies rotate about the fuselage to provide vertical thrust. In a forward flight mode of the aircraft, the first rotor assembly rotates about the fuselage to provide forward thrust and the second rotor assembly is non-rotatable about the fuselage forming wings to provide lift.

Abstract: A tiltrotor aircraft includes a fuselage supporting first and second wings each having an outboard end. First and second nacelles are respectively coupled to the outboard ends of the first and second wings. The first and second nacelles each have an outboard end. First and second wing extensions are rotatably coupled, respectively, to the outboard ends of the first and second nacelles. First and second actuators are operable to respectively move the first and second wing extensions to dampen a mode of the first and second wings, thereby stabilizing the tiltrotor aircraft.

Abstract: A tail sitter aircraft includes a fuselage having a forward portion and an aft portion. The forward portion of the fuselage includes first and second rotor stations. A first rotor assembly is positioned proximate the first rotor station. A second rotor assembly is positioned proximate the second rotor station. A tailboom assembly extends from the aft portion of the fuselage and includes a plurality of landing members. A pusher propeller extends from the tailboom assembly. In a vertical takeoff and landing mode, the first and second rotor assemblies rotate about the fuselage to provide vertical thrust. In a forward flight mode, rotation of the pusher propeller provides forward thrust and the first and second rotor assemblies are non-rotatable about the fuselage forming a dual wing configuration to provide lift.

Abstract: In some embodiments, an aircraft includes a fuselage having a forward portion and an aft portion. First and second ducted fans are supported by the forward portion of the fuselage. The first and second ducted fans are tiltable relative to the fuselage between a generally horizontal orientation, in a vertical takeoff and landing mode, and a generally vertical orientation, in a forward flight mode. A tailboom having an aft station extends from the aft portion of the fuselage. A cross-flow fan is disposed in the aft station of the tailboom and is operable to generate a pitch control moment.

Abstract: An emergency lighting system (ELS) for an aircraft has a capacitor, at least one of an onboard power system and a ground power unit configured to charge the capacitor, and a light emitting diode (LED) selectively powered by the capacitor.

Abstract: A method to remove a bushing from a bore includes an alignment tool that fits within an inner cavity of the bushing and a cutter tool aligned by the alignment tool. The method includes forming a groove on an inner surface of the bushing with the cutter tool and guiding the cutter tool with a guide associated with the alignment tool.

Abstract: A method, system, and device for diagnosing an anomaly of a monitored component in a drive train, the method including obtaining original data based on samples of a vibration signal; converting the original data to an analytical signal having a real component and an imaginary component; determining complex magnitudes of the analytical signal; processing the complex magnitudes of the analytical signal to produce a frequency-domain signal; and determining complex magnitudes of the frequency-domain signal to generate a shock spectrum.

Abstract: A tail sitter aircraft includes a fuselage having a forward portion, an aft portion and a longitudinally extending fuselage axis. A main lifting surface is supported by the forward portion of the fuselage. A propulsion system is operably associated with the main lifting surface and operable to provide thrust during forward flight, vertical takeoff, hover and vertical landing. A tailboom assembly extends from the aft portion of the fuselage. The tailboom assembly includes a plurality of rotatably mounted tail arms having control surfaces and landing members wherein, in a forward flight configuration, the tail arms are radially retracted to reduce tail surface geometry and provide yaw and pitch control with the control surfaces and, wherein, in a landing configuration, the tail arms are radially extended relative to one another about the fuselage axis to form a stable ground contact base with the landing members.

Abstract: A method, system, and device for diagnosing an anomaly of a monitored component in a drive train, the method including obtaining rotational information associated with the component; receiving original data indicating the toothmesh frequency of the drive train; filtering the original data to remove energy above the toothmesh frequency; interpolating the filtered original data to generate an integer number of samples per tooth passage; and generating an amplified differential coherence (ADC). In some embodiments, an amplified differential coherence gearbox arrangement value (ADCT) is generated.

Abstract: A liquid inertia vibration elimination (LIVE) system having an upper end cap, a lower end cap, a spindle located between the upper end cap and the lower end cap, and an external tube connected between the upper end cap and the lower end cap.

Abstract: In some embodiments, a rotorcraft includes a fuselage having a rotor hub assembly protruding therefrom that is rotatable relative thereto. A generator having an armature is mechanically coupled to the rotor hub assembly such that the armature is rotatable in response to rotation of the rotor hub assembly. A braking unit is in selective electrical communication with the generator. The braking unit is adapted to apply an electrical resistance to rotation of the armature, thereby reducing a rotational speed of the rotor hub assembly.

Abstract: A method of controlling an audio system includes generating a situation response model for a situation parameter, determining a situation parameter value, and at least one of (1) providing an audio system output as a function of the situation response model and the situation parameter value and (2) receiving an audio system input as a function of the situation response model and the situation parameter value.

Abstract: The present disclosure provides a utility vehicle front body cowl assembly. The cowl assembly generally comprises a front body cowl and a cargo rack disposed within a reservoir of the front body cowl. More particularly, the front body cowl is connectable to at least a portion of a utility vehicle chassis forward of a passenger compartment dash console of the vehicle, and comprises a pair of opposing shoulders and a rack reservoir or recess provided between the shoulders. The cargo rack is disposed within the reservoir/recess such that the cargo rack and any gear disposed with cargo rack create little or no impedance to a line-of-sight an operator of the vehicle 10. Accordingly, the front cowl assembly provides good visibility and a substantially unimpeded field-of-view for the vehicle operator.

Abstract: A rotor hub can include a yoke, a mast, and one or more radially oriented actuators. The first radial actuator and the second radial actuator each have a piston configured to impart a translation of the yoke relative to the mast. The radial actuators are configured to attenuate in-plane whirling vibrations. The rotor hub can also have actuators coupled between the mast and the yoke for attenuating flapping and vertical vibrations.

Abstract: A compression-molded part has a conductive layer embedded in the part during molding of the part. The conductive layer is generally adjacent an outer surface of the part and is preferably formed from a mesh, a foil, a pulled screen, or multiple layers of conductive elements. The part is preferably optimized for use on the exterior of an aircraft for lightning-strike or EMI protection or for use as an antenna. Methods for forming the panels of the invention include placing the conductive layer against a mold surface of a compression mold, then forming the compression-molded part with the conductive layer embedded in the part.