Abstract: There is disclosed in one example, one or more tangible, non-transitory computer-readable storage media having stored thereon machine-executable instructions to: receive battery data from at least one sensor connected to a battery bank of an electric vertical takeoff and landing (eVTOL) aircraft, wherein the battery bank comprises a plurality of batteries; compute from the battery data an available flight time remaining for the eVTOL aircraft; compute a nominal flight time remaining, wherein the nominal flight time remaining excludes a reserve flight time; and display the nominal flight time remaining to a pilot in a human-readable format.

Abstract: Embodiments include an aircraft comprising a fuselage; a wing connected to the fuselage; and first and second propulsion systems connected to the wing on opposite sides of the fuselage, wherein at least a portion of each of the first and second propulsion systems and at least a portion of the wing are tiltable between a first position in which the aircraft is in a hover mode and a second position in which the aircraft is in a cruise mode, wherein each of the propulsion systems includes pylon and a rotor assembly comprising a plurality of rotor blades.

Abstract: A technique provides power-limiting regenerative braking to a utility vehicle. The technique involves detecting that the utility vehicle is moving in a forward direction at a first speed. The technique further involves applying a first regenerative braking power level to the utility vehicle in response to detecting that the utility vehicle is moving in the forward direction at the first speed. The technique further involves detecting that the utility vehicle is moving in the forward direction at a second speed which is less than the first speed. The technique further involves applying a second regenerative braking power level to the utility vehicle in response to detecting that the utility vehicle is moving in the forward direction at the second speed. The second regenerative braking power level is lower than the first regenerative braking power level.

Abstract: A linear actuator for axially translating a control tube to change the pitch of rotor blades at a top portion of the control tube, the linear actuator including an outer sleeve fixed in a stationary position with the control tube extending through the outer sleeve, a screw nut connected by a threaded interface to the control tube, and an actuator motor coupled to the screw nut to rotate the screw nut and thereby translate the control tube.

Abstract: Techniques control a utility vehicle. Such techniques involve storing electric power in a lithium battery of the utility vehicle. Such techniques further involve operating a motor controller of the utility vehicle in a normal mode in which the motor controller provides electric power from a lithium battery of the utility vehicle to an electric motor of the utility vehicle to turn one or more ground engaging members of the utility vehicle. Such techniques further involve, after operating the motor controller in the normal operating mode, operating the motor controller in a walkaway mode in which the motor controller configures the electric motor to provide braking torque.

Abstract: A fuel tank has an outer shell, a media guide disposed within the space at least partially defined by the outer shell, the media guide being configured to receive a media within cells of the media guide. The fuel tank further has a spring space disposed between the media guide and the outer shell and a compressible spring disposed within the spring space and connected between the outer shell and the media guide.

Abstract: An aircraft door handle and lighting system for an entryway on an aircraft. The system includes a face plate with recessed areas. One recessed area includes a handle positioned for a user to grasp when entering or exiting the aircraft, and another recessed area includes a light source configured to direct light towards one or more stairs. Another recessed area is configured on the opposite side of the entryway and includes a light source configured to direct light towards the stairs.

Abstract: An aircraft nacelle includes a forward cruise inlet, a forward-cruise-inlet conduit coupled to the forward cruise inlet and operable to supply air from the forward cruise inlet to an engine housed by the aircraft nacelle, an inlet barrier filter, an inlet-barrier-filter compartment coupled to the inlet barrier filter, a plurality of gills coupled between the inlet-barrier-filter compartment and the engine and operable to be in an open state and a closed state, a filter-purge door coupled to the inlet-barrier-filter compartment and operable to be in a closed state and an open state. When the plurality of gills are in the closed state and the filter-purge door is in the open state, air from the filter-purge door flows from the inlet-barrier-filter compartment through the inlet barrier filter.

Abstract: In certain embodiments, an apparatus includes an electrolyte membrane layer (EML), and includes a first electrode catalyst layer (ECL) and a first metallic gas diffusion layer (MGDL) positioned to a first side of the EML such that the first ECL is positioned between the first MGDL and the EML. The first MGDL includes a metal-containing layer and a coating of porous material disposed on a surface of the metal-containing layer of the first MGDL that faces the first ECL. The apparatus further includes a second ECL and a second MGDL positioned to the second side of the EML such that the second ECL is positioned between the second MGDL and the EML. The second MGDL includes a metal-containing layer and a coating of porous material disposed on a surface of the metal-containing layer of the second MGDL that faces the second ECL.

Abstract: According to one implementation of the present disclosure, a method is disclosed. The method includes: detecting, on or proximate to one or more surfaces of an aircraft, a presence of an electric-field above a predetermined threshold; and in response to the detection, activating one or more beam sources to generate an ionized column of charge away from the aircraft.

Abstract: A method and system for controlling a fluid valve are described that avoid the effects of hysteresis. In hysteresis, the power signals associated with a valve position are different on the upstroke and downstroke. As a result, predicting the valve position can be difficult if you only know the current power signal. Instead of using upstrokes and downstrokes, a valve can momentarily be set to zero power, or a rest position when receiving a new command signal. This way the command signal is applied from a zero power or rest position, making the valve position more predictable and accurate.

Abstract: An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A source of electric power is disposed within or attached to the closed wing, fuselage or one or more spokes. A plurality of electric motors are disposed within or attached to the one or more spokes in a distributed configuration. Each electric motor is connected to the source of electric power. A propeller is operably connected to each of the electric motors and proximate to a leading edge of the one or more spokes. One or more processors are communicably coupled to the plurality of electric motors. A longitudinal axis of the fuselage is substantially vertical in vertical takeoff and landing and stationary flight, and substantially in a direction of a forward flight in a forward flight mode.

Abstract: An engine vibration isolation subframe for aircraft includes a forward frame and a forward beam connected to the forward frame. The forward beam includes a first end configured to connect to a first engine and a second end configured to connect to a second engine. An aft frame is disposed aft of the forward frame and includes a first aft beam connected to the aft frame and the first engine and a second aft beam connected to the aft frame and the second engine, where the second aft beam is disposed substantially opposite the first aft beam. At least one forward isolator assembly is connected to the forward frame and at least one aft isolator assembly is connected to the aft frame.

Abstract: A sensor lift mechanism for deploying a sensor from a tail cone of an aircraft includes a frame mounted onto a side wall of the tail cone via a mounting assembly. The frame includes a first roller track and a second roller track aligned with the first roller track. A roller carriage assembly includes a plurality of rollers configured for rolling along the first and second roller tracks. A sensor platform is mechanically coupled to the carriage assembly and configured for mounting the sensor thereto. A drive unit is operatively coupled to the frame. The drive unit translates the roller carriage assembly vertically between the first and second roller tracks to move the sensor platform between a stowed position and a deployed position. A floor of the tail cone includes a track door configured to open for deploying the sensor beneath the tail cone.

Abstract: A back-to-back spherical bearing assembly for a rotary system of a rotary aircraft includes a spherical bearing member having an interior cavity and a spherical bearing surface defining a bearing focal point, a first elastomeric and a second elastomeric bonded to the spherical bearing surface on opposite sides of the bearing focal point, an inboard attachment bonded to the first elastomeric and configured to be secured to a rotor hub of the rotary system, and an outboard attachment bonded to the second elastomeric and configured to be secured to a rotor blade of the rotary system.