Abstract: An exemplary aircraft includes a wing positioned below a vertical rotor, the wing extending to an outboard end, and an anhedral winglet extending from the outboard end through an angular transition to a tip, the anhedral winglet having an external surface exposed to the rotor downwash and the external surface is contoured to generate local wing lift in response to the rotor downwash.

Abstract: Embodiments are directed to systems and methods for controlling a tiltrotor aircraft using a flight control system. A flight control computer is configured to control aircraft effectors in response to inputs from inceptors. The flight control computer stores instructions for controlling aircraft effectors. The instructions cause the flight control computer to perform the steps of converting a signal representing longitudinal motion of a first inceptor into a fore-and-aft translational rate command for the tiltrotor aircraft; converting a signal representing lateral motion of the first inceptor into a side-to-side translational rate command for the tiltrotor aircraft; converting a signal representing longitudinal motion of a second inceptor into a height rate command for the tiltrotor aircraft; and converting a signal representing lateral motion of the second inceptor to a yaw rate command for the tiltrotor aircraft.

Abstract: Various implementations described herein are directed to a device having a puller tool assembly for removing a wear sleeve from a tail-rotor hub assembly of a rotorcraft. The puller tool assembly may have an interior shaft slidably engaged within an exterior cylindrical body. The puller tool assembly may have a restraint cap coupled to the interior shaft at a first end of the exterior shaft with a fastener. The puller tool assembly may have a mandrel coupled to the interior shaft at a second end of the exterior shaft. The exterior cylindrical body may be inserted within the wear sleeve between the restraint cap and the mandrel. The mandrel may expand to grasp the wear sleeve when the exterior shaft is tightened so as to pull the wear sleeve toward the restraint cap.

Abstract: A metal curtain glide includes a spherical metal core coupled to a cable and having a polymer cup formed to fit a base of the metal core. The polymer cup includes a central opening for the cable to extend therethrough. An eyelet having a circular member with a connecting member is coupled to an end of the cable. A first member of a fastener assembly is coupled to the eyelet and configured to be removably secured to a second member of the fastener assembly that is coupled to a curtain. The curtain glide remains functional if the polymer cup fails.

Abstract: Various implementations directed to an aircraft thermal management system are provided. In one implementation, an aircraft may include a fuselage having one or more fuselage sections. The aircraft may also include one or more electric motors configured to drive one or more propulsion systems of the aircraft, where the one or more electric motors are configured to generate thermal energy. The aircraft may further include an aircraft thermal management system configured to transfer the thermal energy generated by the one or more electric motors to the one or more fuselage sections.

Abstract: An aircraft includes a fuselage and an airframe supporting the fuselage. The airframe includes a pair of longitudinally-extending beams. The aircraft further includes a battery assembly including a cold plate secured to the pair of longitudinally-extending beams, and a battery mounted to the cold plate.

Abstract: One embodiment includes a rib structure to be used, for example, in any number of aerospace applications, the rib structure, comprising a first piece having a first curvature in a first plane; and a second piece having a second curvature in a second plane that is different from the first plane. The first piece and the second piece are bonded together to form the rib structure. In certain embodiments, the first piece further comprises a plurality of discontinuous flanges to interface with a plurality of skin surfaces. In other examples, the first piece includes an aft spar interface for bonding to a surface. In some implementations, the first piece includes a forward spar interface for bonding to a surface. Manufacturing of the airframe/aircraft parts, panels, and rib components can include any suitable composites, alloys, titanium, aluminum, artificial materials, sheet metal, etc.

Abstract: A method for heating an unpressurized aircraft includes receiving a desired air temperature, calculating a target duct air temperature based on the desired air temperature, determining an actual duct air temperature via a duct air temperature sensor, calculating a target modulation of one or more ram air valves based on a difference between the target duct air temperature and the actual duct air temperature, modulating one or more of the ram air valves based on the target modulation, introducing a bleed air from a turbine engine to a heat exchanger, introducing a temperature control air from one of the one or more ram air valves to the heat exchanger for cooling the bleed air to provide a temperature-controlled air, mixing the temperature-controlled air from the heat exchanger with an ejector ram air in an ejector, and providing air from the ejector to an occupied compartment of the unpressurized aircraft.

Abstract: Embodiments are directed to systems and methods for estimating wear in aircraft rotor systems. Data associated with loads and motions of a swashplate actuator is collected. The swashplate actuator drives a swashplate and at least one control link is coupled to the swashplate. The loads and motions of the at least one control link is estimated based upon the loads and motions of the swashplate actuator. Using a wear model, the current wear of control link components is estimated due to the loads and motions of the at least one control link. Wear estimates for the components are aggregated across multiple flights and used to determine when maintenance actions should occur.

Abstract: One embodiment is a navigation system for an aircraft including a positioning system to generate information related to a position of the aircraft, a group of cameras mounted to a body of the aircraft, each camera of the group of cameras to simultaneously capture images of a portion of an environment that surrounds the aircraft, and a processing component coupled to the positioning system and the group of cameras, the processing component to determine a current position of the aircraft based on the information related to the position of the aircraft and the images.

Abstract: A headliner trim for a motor vehicle includes a main body, at least one air channel formed in the main body for conducting an air flow through the main body, and at least one air outlet opening formed in the main body, through which air outlet opening the air flow conducted in the air channel can flow into the interior of the motor vehicle. The main body is formed from a particle foam, such as expanded polypropylene (EPP) or expanded polyethylene (EPE).

Abstract: A charge control system includes a lithium battery configured to provide lithium battery power to a set of electrical loads, a user signaling device, and control circuitry coupled with the lithium battery and the user signaling device. The control circuitry is operative to: (A) detect availability of charge from an external charger, (B) in response to detection of the availability of charge from the external charger and prior to controlling the external charger to adjust the amount of charge stored by the lithium battery, perform a set of pre-charging assessment operations, and (C) based on the set of pre-charging assessment operations, provide a user notification via the user signaling device, the user notification indicating whether the lithium battery is properly setup for charge adjustment. When the user signaling device generates the user notification, the user is informed that the utility vehicle is properly connected to the external charger.

Abstract: The invention relates to a battery cooling element having: an outer surface for resting at least in regions against a battery cell and/or for resting at least in regions against a battery module comprising at least two battery cells; an inner chamber for receiving a cooling medium, which inner chamber is surrounded at least in regions by the outer surface; and a cooling medium inlet connected to the inner chamber and a cooling medium outlet connected to the inner chamber, wherein the outer surface is made, at least in regions, of a thermally conductive, flexible film which can be shaped by a fluid pressure of the cooling medium.

Abstract: A self-retaining wear-pad leveler has a first plate having arms on opposing sides and forming an aperture through the first plate. A rear section is coupled to a rear portion of the first plate and has tabs extending from opposing sides of the rear section. The arms are configured for being retained about a ball of a spherical bearing assembly, and the tabs are configured to cause rotation of the leveler about the bearing when engaged by a component coupled to and rotating about the bearing.

Abstract: According to one implementation of the present disclosure, a method is disclosed. The method includes forming one or more aircraft surfaces from at least one of one or more metal materials or metal composite materials; and forming a surface coating, at least partially covering the one or more aircraft surfaces, with one or more materials above a dielectric strength threshold.

Abstract: An electric pushback vehicle includes a frame having a forward portion and a rear portion. The vehicle further includes front drive axle and a rear drive axle configured to communicate power to ground engaging members. A traction battery is housed within the electric pushback vehicle and provides electric power to an electric motor to drive an output shaft. A transmission is connected to receive mechanical power from the electric motor through a torque converter.

Abstract: A tactile signal seat belt sleeve has tactile signal producing elements arrayed along a sleeve that is adapted to fit over a seat belt for a vehicle, such as an aircraft. The elements may be arranged, for example, along the body-facing side of the belt. Each sleeve incorporates a signal-receiving element that allows for the activation of vibration-producing motors embedded in the fabric of the seat belt sleeve or belting. Vibration motors, such as piezoelectric devices, can be used to produce the tactile feedback. The haptic feedback assembly is connected to an interface unit that uses data from aircraft systems to sense, for example, the aircraft altitude and pitch, roll and yaw system. The interface unit generates signal to haptic devices to create appropriate vibrations patterns to the sleeve. The vibrations may be used to indicate directions of turn using output signals from various navigations systems.