Abstract: A propulsion assembly for a rotorcraft. The propulsion assembly includes a mast having an internal ledge, a raceway station and an external ridge with at least a portion of the raceway station positioned axially between the internal ledge and the external ridge. A nonintegral raceway is receivable by the raceway station to form a press fit joint between the mast and the nonintegral raceway. A mast bearing assembly includes a plurality of bearings configured to engage an outer surface of the nonintegral raceway. The internal ledge is configured to generate a nonuniform normal force between the mast and the nonintegral raceway along the raceway station that axially biases the nonintegral raceway toward the external ridge, thereby securing the nonintegral raceway at the raceway station.

Abstract: A multi-mode aircraft power-split-transmission system includes a rotational power input and a power-split transmission. The power-split transmission includes a sun gear, a planetary carrier, a ring gear, a first rotational power output, and a second rotational power output. The multi-mode aircraft power-split-transmission system also includes a first resistance device coupled to the first rotational power output and fixed to an airframe of the multi-mode aircraft and a second resistance device coupled to the second rotational power output and fixed to the airframe. Operation of the first resistance device causes power received from the rotational power input to be directed to the second rotational power output.

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: An ejectable battery system for an aircraft is presented. In one embodiment, the present disclosure provides for a battery pack that can be ejected from the aircraft in the event of a thermal runaway, aircraft malfunction, or impending crash. After ejection the battery can remain attached to the aircraft through a retaining tether. A shock absorber in-line with the tether can decrease tether loads. The present disclosure provides an ejectable battery system capable of detecting a battery pack thermal runaway, aircraft malfunction, or impending crash, opening an aircraft battery hatch, ejecting the battery pack from the aircraft, and retaining the battery pack outside of the aircraft via a tether.

Abstract: An aircraft comprises a fuselage, first and second wing segments each having a leading edge and a trailing edge, a plurality of spokes coupling the fuselage to the first and second wing segments, one or more motors disposed within or attached to the plurality of spokes, and three or more propellers proximate to a leading edge of the plurality of spokes, distributed along the plurality of spokes, and operably connected to the motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight. When the aircraft is in vertical takeoff and landing and stationary flight, the fuselage is approximately vertical. When the aircraft is in forward flight, the fuselage is approximately in the direction of the forward flight and extends forward beyond the leading edges of the first wing segment and the second wing segment.

Abstract: The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.

Abstract: In an embodiment, an aircraft includes first and second wings. The aircraft also includes a plurality of propulsion assemblies, the plurality of propulsion assemblies including a propulsion assembly connected to each end of each of the first and second wings. The aircraft also includes first and second vertical supports disposed between the first and second wings. The aircraft also includes a storage pod disposed between the first and second vertical supports. The storage pod includes a nose portion that extends forward of the plurality of propulsion assemblies. The nose portion includes at least one radar and at least one camera. Other embodiments of this aspect include corresponding computer systems, apparatus, and computer programs recorded on one or more computer storage devices, each configured to perform the actions of the methods.

Abstract: An electric temperature control system for unpressurized aircraft and methods for operating are disclosed. The electric temperature control system may be electrically powered and used on all-electric aircraft or hybrid aircraft. The electric temperature control system may comprise a vapor cycle cooling system for cooling air and an electric heater for heating air. The electric heater may be a PTC electric heater with individually-controllable heating elements. Various input devices may be disposed in the aircraft allowing an operator to set a compartment temperature, an air source, and a fan speed. A controller controls operations of the electric temperature control system based on feedback received from a plurality of feedback devices and the operator inputs.

Abstract: A transition duct assembly includes a shared connector, and a plurality of primary cooling pathways for cooling one or more systems or components. Each primary cooling pathway includes a transition duct in fluid communication with the shared connector, and a transition connector in fluid communication with the transition duct.

Abstract: A latching mechanism configured to secure a first component and a second component. The latching mechanism includes a locking plate that operatively engages a first latch plate and a second latch plate. The plates each include an end that inserts into a slot located on the second component, therein securing the first component to the second component. Actuation of the latching mechanism displaces the plates, therein releasing the ends from the slot and allowing for movement of the first component in relation to the second component.

Abstract: Rapid harness fabrication uses pins having a positioning head, which may include (define) a paper punch end and a magnetic collar disposed between the positioning head and a shaft of the pin. A perforated metal board may have a sheet of perforable material (paper) disposed over it and the magnetic pins may be located in a harness configuration on the sheet by punching the positioning head of each of the pins through the sheet with the collar magnetically engaging the metal board. Harness components may be routed and/or disposed in the harness configuration, with the pins holding the harness components in the harness configuration. Stops secured to distal ends of pin shafts may retain a harness component in the harness configuration. The harness configuration may be projected on the sheet. at a one-to-one scale, by (a) system projector(s) and/or the harness routing may be printed on the sheet.

Abstract: Embodiments are directed to a pourable foam comprising a first resin component comprising a polymeric methylene diphenyl diisocyanate, a second resin component comprising a polyol, and a barium sulfate powder component. The barium sulfate powder component is combined with the second resin component prior to combining the first and second resin components. The barium sulfate component may comprise between 1% and 50% of the pourable foam. The pourable foam may be used to repair or create aircraft components.

Abstract: A rotorcraft includes a fuselage, a flight control computer, an auxiliary flight controller having one or more flight control inputs in the noncockpit section of the fuselage and a relay interposed between the flight control computer and the auxiliary flight controller such that the auxiliary flight controller is in data communication with the flight control computer via the relay. The relay prevents electromagnetic interference affecting the auxiliary flight controller from affecting the flight control computer.

Abstract: Embodiments are directed to a rotorcraft comprising an airframe having an engine compartment, an engine disposed within the engine compartment, at least one fire bottle configured to hold a fire extinguishing agent, at least one agent tube coupled to the fire bottle and configured to carry the fire extinguishing agent to the engine compartment, and a nozzle on the at least one agent tube, the nozzle positioned below the engine and oriented in a upward-facing direction. The nozzle has at least one opening that is closed by a spring-loaded valve.

Abstract: Systems and methods include providing an aircraft with a direct drive dual-concentric valve (D3V) having a body, an outer secondary spool coaxially located within a bore of the body and linearly displaceable relative to the body, an inner primary spool coaxially located within a bore of the secondary spool and linearly displaceable relative to the secondary spool and the body. A plurality of piezo stacks is coupled to a first end of the primary spool, and applying a voltage to at least one of the piezo stacks causes an output stroke of the plurality of the piezo strokes for displacing the primary spool. The secondary spool is displaced together with the primary spool relative to the body if displacement of the primary spool relative to the secondary spool cannot occur.

Abstract: An electric-motor system includes a forward electric-motor assembly, a rear electric-motor assembly arranged in series relative to the forward electric-motor assembly, a forward electric-motor driveshaft splined to the forward electric-motor assembly and comprising a forward electric-motor drive-shaft shear section, and a rear electric-motor driveshaft splined to the rear electric-motor assembly and comprising a rear electric-motor drive-shaft shear section, at least a portion of the rear electric-motor driveshaft arranged concentrically within the forward electric-motor driveshaft. The forward electric-motor driveshaft and the rear electric-motor driveshaft rotate about a common axis.

Abstract: An external power assist system for an eVTOL aircraft having one or more onboard batteries includes a subsurface power source and a power transfer interface electrically coupled to the subsurface power source. The power transfer interface is movable between various positions including a deployed position and a stowed position. The power transfer interface is configured to transfer power to the onboard batteries of the eVTOL aircraft in the deployed position. The power transfer interface is moved at least partially subsurface in the stowed position.

Abstract: A removable passive airflow oscillation device can be disposed within a pressurized wing structure utilized as a plenum. The passive airflow oscillation device can be a removable insert disposed into exterior vehicle surfaces with pressurization of a sealed chamber to provide the airflow. The device can include a cavity configured to receive the airflow from an ingress opening, direct the airflow therethrough to generate a predetermined oscillating airflow, and expel the oscillatory airflow from the egress opening. The removable passive airflow oscillation devices can provide quick and simple replacement and maintenance of damaged or clogged devices. The aft chamber of the flap seal can be sealed and pressurized to serve as a plenum providing the airflow to the actuators. The device can receive airflow, such as compressor air, and expel an oscillating airflow. Because each device is self-contained the number of devices and location thereof can vary by application.

Abstract: A vehicle has a pod carrier, a pod rotatably connected to the pod carrier, and an energy attenuating system (EAS) disposed between the pod and the pod carrier to attenuate forces associated with a deflection of the pod relative to the pod carrier. A method of operating an energy attenuating system (EAS) is provided for attenuating energy associated with movement between a pod and a pod carrier. The method includes providing a vehicle having a pod carrier and providing the pod carrier with an EAS configured in an undeflected state.

Abstract: A drive system for an aircraft includes a first gearbox assembly and a second gearbox assembly that is in mechanical communication with the first gearbox assembly. A first pressurized lubrication system is configured to circulate a first lubricant through the first gearbox assembly. A second pressurized lubrication system is configured to circulate a second lubricant through the second gearbox assembly. An emergency lubrication system is configured to autonomously supply a portion of the first lubricant to the second gearbox assembly responsive to a loss of pressure in the second pressurized lubrication system. The emergency lubrication system is also configured to autonomously supply a portion of the second lubricant to the first gearbox assembly responsive to a loss of pressure in the first pressurized lubrication system.