Abstract: A propulsion device, including a platform configured to support a passenger thereon; a thrust engine coupled to the platform, wherein the thrust engine is configured to provide a thrust output substantially along a first axis; a deflector assembly positioned proximate the thrust output, wherein the deflector assembly includes two deflecting guides to divert the thrust output into at least two thrust vectors angled with respect to the first axis; an actuator coupled to each deflecting guide to controllably adjust a position of the deflecting guides with respect to the thrust engine; and a controller in communication with the actuator, wherein the controller is configured to operate the actuator in response to one or more signals from at least one of the passenger and a sensor coupled to the platform.

Abstract: A galley system within an internal cabin of an aircraft includes one or more inboard cart compartments that are configured to removably retain one or more first galley carts, and one or more outboard cart compartments. The outboard cart compartment(s) are configured to removably retain one or more second galley carts. The inboard cart compartment(s) extend forwardly and/or rearwardly in relation to the outboard cart compartment(s).

Abstract: An aircraft capable of carrying at least 400 pounds of payload, has four rotors systems, each of the rotor systems being independently driven by an electric motor or other torque-producing source. Each of the rotor systems provide sufficient thrust such that the aircraft is capable of controlled vertical takeoff and landing, even if one of the variable pitch rotor is inoperable. An electronic control system is configured to control the rotational speed and pitch of at least one of the rotor systems in each of the first and second rotor pairs. The rotors may be arranged in coaxial stacks or maybe otherwise configured.

Abstract: A counter-attack unmanned aerial vehicle (UAV), for aerial neutralization of a detected target aerial vehicle, comprises a flight body and a flight control system to intercept the detected target aerial vehicle, and comprises an aerial vehicle capture countermeasure (e.g., a net) operable to capture the detected target aerial vehicle. The aerial vehicle capture countermeasure can comprise a net deployable from the counter-attack UAV, and a captured target aerial vehicle can be delivered to a particular location. A system for aerial neutralization of a detected target aerial vehicle comprises an aerial vehicle detection system comprising at least one detection sensor operable to detect the target aerial vehicle, and operable to provide command data (including location data) to at least one counter-attack UAV for neutralization of the target aerial vehicle. The counter-attack UAV and systems may be autonomously operated. Associated systems and methods are provided.

Abstract: A stowable cabin attendant seat assembly includes a frame assembly mountable within a wall recess, a backrest mounted for reciprocating vertical translation within the frame assembly, a seat pan mounted for pivoting motion relative to the frame assembly, and at least one link connecting the seat pan to the backrest. The at least one link coordinates the seat pan and backrest motions such that upward lifting motion on the seat pan pushes the backrest vertically up for compact stowing and downward pivoting motion on the seat pan pulls the backrest vertically down.

Abstract: Apparatus, systems, and methods for protecting a vehicle from a radiation source (e.g., the sun) are provided. One apparatus includes a set of first wires and a set of second wires located proximate to the set of first wires. The set of first wires maintains a positive voltage and the set of second wires maintains a negative voltage. The set of first wire and the set of second wires are arranged to generate an electrostatic field (ESF) between the vehicle and the radiation source. A system includes a spacecraft and a field generator that generates an ESF between the spacecraft and a radiation source. A method includes tracking a location of a spacecraft relative to a radiation source and generating an ESF between the spacecraft and the radiation source.

Abstract: A public transportation system combines a unique combination of components that includes interoperable electric-powered vehicles, facilities, hardware and software having specifications, standards, processes, capabilities, nomenclature, and concepts of operations that together include a concerted, comprehensive, multi-modal, future system for moving people and goods that is herein named Quiet Urban Air Delivery (QUAD) and in which uniquely-capable, ultra-quiet, one to six-seat, electrically-powered, autonomous aircraft (SkyQarts) fly sub-193 kilometer trips on precise trajectories with negligible control latency and perform extremely short take-offs and landings (ESTOL) with curved traffic patterns at a highly-distributed network of very small, airports (“SkyNests”) that themselves have standardized compatible facilities that interoperate with SkyQarts as well as with versatile, autonomous electric-powered payload carts (EPCs) and robotic delivery carts (RDCs) to provide safe, fast, on-demand, community-accep

Abstract: An autonomous cargo container retrieval and delivery system locates a select cargo container and maneuvers an unmanned aerial vehicle proximate to the container for retrieval. The vehicle positions itself to engage the cargo container using a grasping mechanism, and, responsive to engaging the cargo container, retracts the cargo container toward the vehicle. As the cargo container is retracted toward the vehicle, weight sensors within the retrieval mechanism sense the weight and the weight distribution of the cargo container, and, can modify the cargo container's location on the vehicle to optimize vehicle flight operations or replace the container on the ground and alert the operator that the cargo container is too heavy or has an improper weight distribution. Upon mating the cargo container with the vehicle, a coupling mechanism latches or secures the cargo container to the vehicle for further flight and/or ground operations.

Abstract: An aircraft includes a fuselage, a wing extending out from the fuselage, and a joint coupling the wing to the fuselage. The joint includes a first fitting fixed to the fuselage, a second fitting fixed to the wing, a link assembly pivotably coupled to the first fitting and to the second fitting, and a strap coupled to the link assembly at the first fitting and at the second fitting based on the free play clearance as defined by the manufacturing of the link assembly. The link assembly is configured to support the wing during operation of the aircraft and has a free play clearance defined by a manufacturing of the joint falling within a designed dimensional tolerance of the joint. The strap is further configured to bias the link assembly to restrict movement of the link assembly within the free play clearance during load reversal in the joint.

Abstract: An assembly for an aircraft including a pylon having a lateral wall with a window passing through it, at least one reservoir, each reservoir being in the shape of an elongate ellipsoid with three semi-axes. The dimension of the reservoir along a first semi-axis differs from the dimension of the reservoir along at least one other semi-axis. The reservoir extends parallel to the semi-major axis, between a first end and a second end. The reservoir is equipped with a discharge head at the second end. The reservoir is equipped with a fastening arrangement disposed on the side of the second end and fastening the reservoir to the pylon. The reservoir is positioned through the window with the first end housed in the pylon and the second end outside the pylon.

Abstract: An assembly is provided for active laminar flow control. This assembly includes a panel, which panel includes an outer skin, an inner skin and a plurality of plenums between the outer skin and the inner skin. Each of the plurality of plenums is fluidly coupled with a respective array of perforations through the outer skin. The panel is constructed from fiber-reinforced composite material.

Abstract: A nose landing gear system is disclosed. In various embodiments, the nose landing gear system includes an electric motor; a hydraulic pump connected to the electric motor; a gearbox connected to the electric motor; and a clutch configured to mechanically couple the gearbox to a steering collar.

Abstract: Described are aircraft cabin arrangements (12) with at least one lavatory unit (14) with a first side wall (1402) and at least one seat unit (16) positioned adjacent the first side wall. A separate wall is not positioned between the first side wall and the at least one seat unit. The first side wall includes a recessed portion, and the at least one seat unit includes a foot support surface (1606) incorporated into the recessed portion of the first side wall.

Abstract: An ejection seat for an aircraft is disclosed. In various embodiments, the ejection seat includes a seat frame; and a moveable headrest attached to the seat frame, the moveable headrest including a first piercer assembly configured for fracturing a canopy.

Abstract: An aircraft water tank is provided. With an aircraft water tank being suspended by a fuselage via bushes, a load applied to each of the bushes is transferred from the bush and an attachment hole to a metal plate. The load transferred to metal plate is transferred to a total of four prepreg projection portions at a section of a thick wall portion of the metal plate and transferred to a total of eight prepreg projection portions at a section of a thin wall portion.

Abstract: An unmanned aerial vehicle includes a central body and a plurality of arms extendable from the central body. Each of the plurality of arms is configured to support one or more propulsion units. Each of the plurality of arms is configured to transform between (1) a flight configuration in which the arm is extending away from the central body and (2) a compact configuration in which the arm is folded against the central body. At least one of the plurality of arms is configured to rotate about a first rotational axis and at least a portion of the at least one of the plurality of arms is configured to rotate about a second rotational axis not parallel to the first rotational axis.

Abstract: A galley cart stowage system includes lower and upper cart compartments defining lower and upper galley cart cavities receiving the galley carts. The lower galley cart cavity is defined by walls and the upper galley cart cavity is defined by walls. A vertical conveyance device extends between the lower and upper cart compartments to move galley carts therebetween. A galley workspace has a countertop and a workspace volume located above the lower cart compartment and located below the upper cart compartment.

Abstract: An automated drone-based surface treatment material delivery system includes a drone having a body, at least one propeller rotatably supported by the body, at least one propeller motor supported by the body and configured to selectively apply motive power to the at least one propeller, and a controller supported by the body and configured to control a flight path of the drone at least by manipulating a speed of the at least one propeller. The drone also has a rotary atomizer supported by the body for movement therewith. The rotary atomizer includes a rotating dispersion structure configured to disperse a surface treatment material from a material supply.

Abstract: To facilitate the assembly of the wing unit of an aircraft, this wing unit includes two wings each having a lateral wing box extended toward the interior by a center wing box half having an interior end, the two wings being attached to one another using attachment bolts linking the two interior ends of the two center wing box halves, and passing through an intermediate wall connecting two fuselage frame walls.

Abstract: An exemplary electric distributed propulsion system includes two or more rotors that are individually controlled by the rotational speed of associated motors, an input control connected to the associated motors to provide rotational speed control to the two or more rotors to produce a desired net thrust, and a logic connected to the input control and the associated motors, the logic for controlling speed and direction of the two or more rotors to achieve the desired net thrust and to avoid a motor speed condition.