Abstract: An active flow control system for generating pitch control moments for an aircraft during flight. The system includes a nozzle disposed proximate the aft end of the aircraft. The nozzle is configured to discharge a gas stream in the aftward direction. A pressurized air system includes a pressurized air source and one or more injectors configured to selectively inject pressurized air into the nozzle to influence the path of the gas stream. Based upon which injectors are injecting pressurized air into the nozzle, the gas stream exits the nozzle generating no pitch control moment, generating a pitch down control moment or generating a pitch up control moment.

Abstract: A method of operating an automated fiber placement machine including determining an effective length and a steering radius of a localized curved portion of a path and obtaining data including combinations of effective length and steering radius reference values each associated with a corresponding one of maximum speed values. A predetermined defect is avoided when the tape is laid along a curved path characterized by any of the combinations of effective length and steering radius reference values and laid at the corresponding maximum speed value. The method further includes determining a maximum speed based on the maximum speed values of the data in function of a correspondence between the effective length and the steering radius of the curved path and the combinations of effective length and steering radius reference values, selecting a speed for laying the tape being at most the maximum speed, and laying the tape on the surface.

Abstract: A composite core with non-traditional geometries includes multiple elongate tubes arranged in a two-dimensional array. Each tube is made of a composite material. Each tube includes multiple curved sides. Each curved side inwardly curves toward a longitudinal axis passing through a geometric center of the tube to form a valley on an outer surface of the tube. An end of a first curved side connects to an end of a second curved side to form a crest on the outer surface of the tube. At least one crest formed on an outer surface of a first tube in the two-dimensional array contacts at least one valley formed on an outer surface of an adjacent second tube in the two-dimensional array.

Abstract: An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The aircraft has a blended wing body and includes first and second engines, a binary lift fan system, first and second forced air bypass systems and first and second exhaust systems. The engines have turboshaft and turbofan modes. The lift fan system includes ducted fans in a tandem longitudinal orientation. In the VTOL orientation of the aircraft, the engines are in the turboshaft mode coupled to the lift fan system such that the engines provide rotational energy to the ducted fans generating the thrust-borne lift. In the forward flight orientation of the aircraft, the engines are in the turbofan mode coupled to the forced air bypass systems such that the bypass air combines with the engine exhaust in the exhaust systems to provide forward thrust generating the wing-borne lift.

Abstract: One example of a mount for a rotorcraft comprises a structural support member, a bracket, and an elastomer. The bracket is configured to attach to a component of the rotorcraft. The component of the rotorcraft produces vibrations at a first frequency. The structural support member configured to transfer a weight of the component of a rotorcraft to an airframe of the rotorcraft. A rotor system of the aircraft vibrates the airframe of the rotorcraft at a second frequency. The elastomer is located between a structural support member and a bracket. The elastomer is configured to attenuate noise caused by the vibrations at the first frequency by isolating the vibrations at the first frequency from reaching the airframe of the rotorcraft while the airframe vibrates at the second frequency.

Abstract: A tiltrotor aircraft having a propulsion configuration that divorces the engine core power from the thrust fan, using a combined gearbox with a plurality of clutches to couple and decouple one or more rotor systems and one or more thrust fans. The aircraft can be operable for vertical takeoff and landing (VTOL) in a helicopter mode, forward flight in a proprotor mode, and high-speed forward flight in an airplane (jet) mode. The propulsion configuration provides shaft horsepower (SHP) to rotors for VTOL flight, while also providing SHP to the thrust fan for high speed flight. Allowing the rotor and the thrust fan to be clutched on and off, sequentially, enables transition from rotor-borne VTOL flight to wing-borne thrust fan flight, and back.

Abstract: An accessory attachment system comprising a fastening key having an accessory retention cap, a stem extending from the retention cap, and at least one bit extending laterally from a distal end of the stem. The stem configured to be inserted through a key aperture in an accessory to be attached to the vehicle. The system includes a locking bracket connectable to the vehicle adjacent an accessory portal provided in the vehicle. The locking bracket comprises a base plate, a keyhole disposed through the base plate, and at least one inclined securing structure disposed along a circumference of the keyhole. Each securing structure comprises a ramp and a detent. The keyhole is configured to receive the stem distal end and bit(s) therethrough, and each securing structure is configured to engage the bit(s) and interlock the fastening key with the locking bracket upon rotation of the key.

Abstract: One embodiment is an apparatus including a mold configured to manufacture a composite structure at a heated temperature. The mold includes a first mold tool configured to mold a first portion of the composite structure, wherein the first mold tool comprises a plurality of strands of a fiber-reinforced thermoplastic material, wherein the fiber-reinforced thermoplastic material comprises a thermoplastic embedded with a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is aligned within each strand of the plurality of strands; and an anisotropic thermal expansion property, wherein the anisotropic thermal expansion property is based on an orientation of the plurality of reinforcement fibers within the first mold tool; and a second mold tool configured to mold a second portion of the composite structure.

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: An example of a method of manufacturing a component from a composite prepreg includes collecting a specimen from the composite prepreg and quantifying an amount of surface resin of the specimen by submerging the specimen in a container containing a fluid to determine a fluid pickup percentage. Responsive to a determination that the fluid pickup percentage exceeds a predefined threshold value, forming a component from the composite prepreg.

Abstract: A damping landing gear assembly for a vertical takeoff and landing aircraft includes a spring housing forming a spring chamber, a spring disposed in the spring chamber and a plunger slidably coupled to the spring housing and movable between a compressed position and an extended position. The spring biases the plunger into the extended position during flight. The vertical takeoff and landing aircraft experiences a landing force during landing. The landing force compresses the plunger into the compressed position against the bias of the spring, thereby absorbing at least a portion of the landing force.

Abstract: Systems, methods and non-transitory computer readable storage media for airspace management within an airspace region at a node of a peer to peer network having a plurality of nodes and maintaining a blockchain containing a current deconflicted flight schedule for the airspace region. One method includes receiving requests for airspace reservations, each including flight plan data, from other nodes over the peer to peer network, compiling the flight plan data to identify conflicts between the requests and the current deconflicted flight schedule, validating the flight plan data of the requests that do not conflict with the current deconflicted flight schedule to generate validated airspace reservations, creating a block containing the validated airspace reservations and interlinking the block with the blockchain such that the blockchain contains a new deconflicted flight schedule for the airspace region for broadcast to the other nodes over the peer to peer network.

Abstract: A cam-locking system for use with a retractable driveshaft that includes a housing, a cam carrier located at least partially the housing, and a cam rotatably coupled to the cam carrier. Translation of the cam carrier along a central axis allows the cam to rotate into cooperative engagement with a catch recess on an interior surface of the housing, preventing the cam carrier from translating backwards, and thereby maintaining the retractable driveshaft in an engaged position. Further advancement of the cam carrier allows that cam to rotate into and unlocking gap in the interior surface of the housing, which enables the cam carrier to translate backwards along the central axis below the locked position, thereby disengaging the retractable driveshaft.

Abstract: Systems and methods include providing a virtual reality (“VR”) flight emulator system that simulates control, operation, and response of a vehicle. The flight emulator includes a control interface and a head-mounted display worn by a user. Motion, orientation, and/or forces experienced by the simulated vehicle are imparted to a user through a motion-control seat. Multiple flight emulators can be connected to a communication network, and a master flight emulator may teleport into a slave flight emulator in order to observe, overtake, override, and/or assume control of the slave flight emulator. Inputs made via the control interface of the master flight emulator or during playback of a pre-recorded training exercise or flight mission are translated into the control interface, head-mounted display, and motion-control seat of the slave flight emulator to provide real-time feedback to the user of the slave flight emulator.

Abstract: A remote aircraft preflight verification method includes sending a request via a remote interface for data from a sensor onboard an aircraft, transmitting the data from the sensor to the remote interface, processing the data via the remote interface to enable a determination that one or more preflight requirements are met, and presenting the data via the remote interface for enabling verification that the one or more preflight requirements are met. The method steps are repeated for multiple sensors. A remote aircraft preflight verification system includes sensors located onboard an aircraft and a remote interface communicatively coupled to the sensors. The remote interface includes a display for presenting data and an interface enabling verification of preflight readiness. The system may optionally include a wireless access point for coordinating the transmitting and receiving of instructions and data between the sensors and the remote interface.

Abstract: A propulsion assembly includes a rotor assembly, a mast coupled to the rotor assembly and a bull gear coupled to the mast. The bull gear is subject to radial and axial loads. The propulsion assembly includes a flexured standpipe extending through the bull gear and a ball bearing including inner and outer races interposed between the bull gear and the flexured standpipe. The ball bearing is configured to absorb axial loads from the bull gear. The bull gear is rotatably coupled to the flexured standpipe via the ball bearing. The flexured standpipe flexes in response to radial loads from the bull gear.

Abstract: The present invention includes a cooling system for a gearbox, the cooling system comprising: a pressurized housing in fluid communication with the gearbox configured to circulate a pressurized lubricant; and one or more cooling fins about the pressurized housing, wherein heat from the pressurized lubricant within the pressurized housing is actively convected through the one or more cooling fins.

Abstract: A wing assembly for an aircraft includes a torque box sleeve having an open end and a plurality of integral sides including leading, aft, top and bottom sides that jointlessly form a continuous surface having a generally airfoil shape. The wing assembly includes an internal support subassembly having a plurality of ribs coupled to a central spar. The internal support subassembly is formed into a single component outside the torque box sleeve and inserted into the open end of the torque box sleeve as the single component. The internal support subassembly is coupled to an interior of the torque box sleeve.

Abstract: A pneumatic flow-control system and method for an aircraft provide efficient mixing of high-pressure engine bleed air with one or both of low-pressure engine bleed air and ambient air. A controller determines an amount of high- and low-pressure air and ambient air to provide based on ambient air temperature and pressure and a flow rate and temperature of the mixed air for improving engine performance during different phases of flight and for reducing a burden on an environmental control subsystem of the aircraft.

Abstract: An airfoil component assembly for an aircraft includes an additively manufactured flyaway tool including an infill support core and an interface sheet surrounding the infill support core, a spar formed from one or more layers of composite material disposed on the interface sheet of the flyaway tool and a skin formed from one or more layers of composite material disposed on the spar and the interface sheet of the flyaway tool. The flyaway tool, the spar and the skin form the airfoil component assembly for use by the aircraft in flight.