Abstract: A method for operating a sensor system includes detecting a first wake trigger by a plurality of sensors for a component disposed in a remote location, generating, by each sensor, sensor service data that includes a battery charge level of the sensor, determining an active sensor according to the sensor service data of each sensor of the plurality of sensors, and assigning the active sensor to enter an active mode assigning each sensor of the plurality of sensors, other than the active sensor, to enter a sleep mode, generating, by the active sensor, sensor reading data for the component until an inactive trigger is detected, sending the sensor reading data using a wireless transmission to a sensor data server, and leaving the active mode by the active sensor and entering a sleep mode in response to the active sensor detecting an inactive trigger.

Abstract: An enclosure including a bottom side having a pass through opening, a connector surface having one or more connector openings, a first side adjacent to the connector surface, and a second side having at least a portion of an access opening, where the first side, the second side, the connector surface and the bottom side bound an interior cavity. The enclosure further includes one or more connectors, each of the one or more connectors disposed in a respective connector opening of the one or more connector openings and extending from the interior cavity, through the connector surface, and a cover attached to an exterior surface of at least the second side, the cover covering the access opening.

Abstract: A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a grip with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard bearing. A folding spindle connects the outboard bearing to an outboard tip of a yoke. The outboard bearing and the spindle fold with the rotor blade relative to the yoke. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

Abstract: Systems and methods of constructing a thermoplastic component include joining a thermoplastic skin to a thermoplastic core by introducing heat at an interface of each of the thermoplastic skin and the thermoplastic core to at least partially melt the thermoplastic skin to a thermoplastic core at the interfaces, applying pressure to at least one of the thermoplastic skin and the thermoplastic core to sandwich the elements, and cooling the interfaces below the melting point of each of the thermoplastic skin and the thermoplastic core to consolidate the thermoplastic skin and the thermoplastic core into a unitary thermoplastic component. An optional thermoplastic film may be disposed between the thermoplastic skin and the thermoplastic core. The thermoplastic skin may be joined to the thermoplastic core to form an intermediate thermoplastic component prior to joining the thermoplastic skin to the intermediate component.

Abstract: A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a yoke with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard shear bearing. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

Abstract: A folding yoke comprising a center yoke pivotally connected to separate foldable flexible yoke arms permits rotor blade fold about a single through bolt connection inboard of a set of bearings. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

Abstract: A yoke split into separate, individual yoke arms permit rotor blade fold about inboard yoke arm bolts in a rotor blade assembly for rotorcraft and tiltrotor aircraft. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

Abstract: A folding yoke comprising a bilateral center yoke pivotally connected to separate foldable yoke arms permits rotor blade fold about a single through bolt connection inboard of a set of bearings. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

Abstract: An in-flight impact protection system for aircraft. An aircraft having a panel, with a sensor disposed on the aircraft and adapted to transmit a signal and receive a reflection of the signal. A controller coupled to the sensor and adapted to receive the reflection from the sensor to determine whether an object is near the aircraft's panel. An inflation device, which includes a tube member, is coupled to the controller and positioned inside the aircraft, proximate the panel. After determining that the object is near the panel, the controller can activate the inflation device so that the tube member inflates, thereby buttressing at least a portion of the panel. The panel can be a windshield, fuselage member, or other suitable component.

Abstract: A rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a yoke with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard CF bearing and the yoke tip. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

Abstract: A rotor yoke manufactured by a process comprising preparing a molded rotor yoke in a closed cavity tool and possibly machining at least one portion of the molded rotor yoke to form the rotor yoke. In the preferred embodiment, the preparing of the molded rotor yoke is accomplished by applying layers of uncured low-flow composite material and a layer of uncured high-flow adhesive; substantially enclosing the uncured molded rotor yoke in the closed cavity tool; and applying pressure so as to compress the uncured molded rotor yoke; and curing the uncured molded rotor yoke. During the curing process, the high-flow adhesive bleeds out of the molded rotor yoke, thereby preventing marcels from forming through movement of the low-flow composite material.

Abstract: A rotating sealing system includes a non-metallic rotating seal configured to be attached to a rotating shaft. The rotating seal is configured to rotate with the rotating shaft about an axis. The rotating sealing system includes a stationary sealing surface configured to be attached to a stationary housing positioned around the rotating shaft. The stationary sealing surface is substantially parallel to the axis. The rotating seal is configured to seal with the stationary sealing surface as the rotating shaft rotates.

Abstract: A battery management system (BMS) controls lithium battery access on a utility vehicle. The BMS includes a battery interface that couples with a lithium battery, a load interface that couples with a set of loads of the utility vehicle, and control circuitry coupled with the battery interface and the load interface. The control circuitry mechanically disconnects the battery interface from the load interface in response to a sleep event. Additionally, after the battery interface is mechanically disconnected from the load interface, the control circuitry mechanically reconnects the battery interface to the load interface in response to a wakeup event. Furthermore, after the battery interface is mechanically reconnected to the load interface, the control circuitry maintains connection between the battery interface and the load interface to convey power from the lithium battery to the set of loads of the utility vehicle through the battery interface and the load interface.

Abstract: In some embodiments, a pod assembly transportation system includes a transportation services provider computing system and a plurality of flying frame flight control systems, wherein the system is configured to receive, at the transportation services provider computing system, a request for transportation of a pod assembly; upload a flight plan to a flight control system of a flying frame including an airframe and a distributed propulsion system coupled to airframe; dispatch the flying frame by air to the current location of the pod assembly; couple the pod assembly to the flying frame; transport the pod assembly by air from the current location of the pod assembly to the destination of the pod assembly including transitioning the flying frame between a vertical takeoff and landing mode and a forward flight mode; and decouple the pod assembly from the flying frame at the destination of the pod assembly.

Abstract: A dual rotor propulsion system for a tiltrotor aircraft having VTOL and forward flight modes. The dual rotor propulsion system includes an engine operable to provide an input torque to a transmission that, responsive thereto, generates an output torque. A first output shaft is coupled to the transmission and is operable to receive a first portion of the output torque. A first rotor assembly is coupled to and rotatable with the first output shaft. A second output shaft is coupled to the transmission and is operable to receive a second portion of the output torque. A second rotor assembly is coupled to and rotatable with the second output shaft. In operation, the first and second rotor assemblies rotate coaxially, the first rotor assembly is a different diameter than the second rotor assembly and the first rotor assembly is stoppable and foldable in the forward flight mode.

Abstract: A landing gear system for an aircraft includes an aft landing gear fitting coupled to the aircraft and a cross tube rotatably coupled to the aft landing gear fitting. The landing gear system also includes first and second wheel fittings coupled to the first and second ends of the cross tube, respectively, and first and second wheels rotatably coupled to the first and second wheel fittings, respectively.

Abstract: Systems and methods of operating a test apparatus to simulate testing a production aircraft component include assembling a test assembly having a test specimen and a wear protection material disposed on opposing sides of the test specimen, an outer plate disposed on each side of the test specimen in contact with the wear protection material, and a bolt disposed through the test specimen and the outer plates and applying a preload against the wear protection material. The test assembly is secured in a test machine, and the test machine is operated to provide a predetermined displacement of the test specimen relative to the outer plates at a predetermined frequency at a determined frequency of displacement cycles. The preload, the predetermined displacement, and the predetermined frequency of displacement cycles are determined through finite element analysis of an analytical model of the production component.

Abstract: Systems, methods and computer-storage media are provided for a touch-screen interface panel (TSIP) of an aircraft. The TSIP may communicate with one or more aircraft systems. In other words, the TSIP is configured to display information of one or more aircraft systems. For example, the TSIP may receive a request for weather information. In response, the TSIP receives weather information from a weather system and displays it via the TSIP screen. In another example, the TSIP may display warnings or alerts that are detected by an aircraft warning system, maintenance system, or the like. Furthermore, information that may have typically been looked up physically or called in to a tower may now be provided via the TSIP by the interfacing of the TSIP with the systems maintaining the information. For example, a charts database may communicate with the TSIP and the information thereof displayed via the TSIP.

Abstract: A system and method for simulating the radio frequency environment of an aircraft is described. Simulated location data and navigational aid data is used to calculate a digital representation of the radio frequency environment of an airplane at the simulated location. The digital representation of the radio frequency environment is converted into an analog signal and provided to the navigational system of the aircraft.

Abstract: In an embodiment, a rotorcraft includes: tail rotor blades; a tail rotor actuator coupled to the tail rotor blades such that the pitch of the tail rotor blades varies according to a current extension of the tail rotor actuator; pilot flight controls electrically coupled to the tail rotor actuator; and a flight control computer electrically coupled to the tail rotor actuator and the pilot flight controls, the flight control computer configured to: determine the current extension of the tail rotor actuator; determine whether the current extension of the tail rotor actuator is within a margin of a maximum extension of the tail rotor actuator; and indicate a first warning to a pilot in response to the current extension of the tail rotor actuator being within the margin of the maximum extension of the tail rotor actuator.