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: 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 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: 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: 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: 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: 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: 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 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 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.

Abstract: A tailsitter aircraft for deploying a tow line includes an airframe having wings with pylons extending therebetween and a thrust array attached to the airframe, the thrust array including propulsion assemblies configured to transition the airframe between a forward flight orientation and a VTOL orientation. The tailsitter aircraft includes an attenuation spool coupled to the airframe and an attenuation cable having a first end coupled to the attenuation spool and a second end coupled to the tow line, the attenuation cable partially or fully wound around the attenuation spool. The tailsitter aircraft also includes a spool sensor to detect movement of the attenuation spool and a flight control system implementing a tow line tension monitoring module in communication with the spool sensor to determine a tow line tension parameter and a tow line tension reaction module to initiate an aircraft response based on the tow line tension parameter.

Abstract: A tandem tiltrotor aircraft in which the tiltrotor assemblies are operably coupled at the forward and aft ends of the fuselage of the aircraft is disclosed. The tiltrotor assemblies are capable of rotating between a vertical lift position and a horizontal flight position. The in-line location of the tiltrotor assemblies allow the aircraft to have the vertical take-off and landing capabilities, and, in combination with the at least one wing, can be used in horizontal flight. The aft rotor assembly can assume a horizontal flight position that places the rotor blades forward of a vertical fin of the aircraft. In another embodiment, a winged triple tiltrotor aircraft is disclosed. In another embodiment, a winged quad tiltrotor aircraft is disclosed.

Abstract: A modular battery system includes an array of battery modules arranged in at least one stack. Each battery module includes a plurality of battery cells, a first side having positive and negative receptacles and a second side, that is opposite of the first side, having positive and negative plugs. The receptacles and plugs are configured such that adjacent battery modules in a side-by-side relationship are electrically coupled together via plug and receptacle connections and such that the battery modules are electrically coupled together in parallel. An interconnection electrically couples each stack of battery modules together via plug and receptacle connections with one of the battery modules in each stack such that the stacks of battery modules are electrically coupled together in parallel. Each of the battery modules includes a thermal conditioning system configured to thermally isolate the battery module from the other battery modules.

Abstract: In one embodiment, a remote controller for a vehicle includes at least one control element for controlling operation of at least one aspect of the vehicle when the vehicle is in a remote-control mode; an actuator connected the at least one control element for controlling a position of the at least one control element when the vehicle is in an autonomous operations mode; and a processing system for receiving a first control signal from the vehicle indicative of a state of operation of the vehicle. In operation, the processing system generates a second control signal to the actuator to cause the actuator to control a position of the control element such that it corresponds to and indicates the state of operation of the vehicle.

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 drive-shaft rotate about a common axis.

Abstract: An electrochemical machining assembly for boring a passage in an electrically conductive workpiece. The electrochemical machining assembly includes an electrochemical machining tool having a telescoping collar with an articulating head coupled thereto. The telescoping collar is actuated between a contracted configuration and an extended configuration to advance the telescoping collar stepwise in the passage. The articulating head is tiltable relative to the telescoping collar to determine a direction of the passage. The electrochemical machining assembly is configured to remove material from the workpiece upon application of a voltage between the articulating head and the workpiece via a circulating electrolyte fluid to lengthen the passage.

Abstract: An exemplary integrated battery cargo platform includes a housing having an exterior surface and a structural strength to support cargo for transit on a top surface, a battery enclosed in the housing with power contacts exposed at the exterior surface.

Abstract: Various implementations described herein are directed to an aircraft having a multi-engine configuration with multiple engines. The aircraft may have a flight control system coupled to the multiple engines with a multi-engine interface. The flight control system may be configured to shutdown at least one engine of the multiple engines during reduced-engine operation by continuously calculating altitude for the reduced-engine operation based on one or more of an aircraft descent rate of the aircraft and an engine restart time of the at least one engine.