Abstract: Embodiments herein describe UAVs that utilize tail boom assemblies from pre-existing aircraft designs as lift generating elements. In one embodiment, a UAV includes a fuselage having a first end and a second end opposite the first end, a first tail boom coupler disposed at the first end, and a second tail boom coupler disposed at the second end. Each of the first tail boom coupler and the second tail boom coupler are configured to mechanically couple with a plurality of tail boom assemblies procured from a pre-existing aircraft design.

Abstract: An improved rotorcraft of the type having a fuselage and a set of N?4 rotors. The rotorcraft includes a structural support system affixed to the fuselage and mounting the set of rotors. The support system is configured as a set of airfoils that provide lift when the fuselage is in level flight. The fuselage has a central longitudinal axis that defines the direction of forward flight of the rotorcraft. Each of the rotors defines a corresponding rotational plane, that is tilted forward in the direction of the forward flight, when the central longitudinal axis of the fuselage is horizontal. Each airfoil may be positioned so that a majority of its length is disposed beneath the rotational plane of its corresponding rotor. When the rotorcraft is at a cruise speed, the airfoils are configured to provide lift that approximately matches the lift provided by the rotors.

Abstract: Unmanned aircraft have aligned forward and aft propulsion systems possessing different performance and/or noise characteristics. According to some embodiments, unmanned aircraft have a forward engine and a forward tractor propeller and an aft engine and an aft pusher propeller. Selected ones of forward and aft propulsion systems will thus be provided to have greater and lesser operational flight performance characteristics and greater and lesser noise signature characteristics, respectively, as compared to the other. For example, the forward propulsion system may be provided with the greater operational flight performance and higher signature characteristics as compared to the aft propulsion system, while conversely the aft propulsion system may be provided with a lesser flight performance and lower noise signature characteristics as compared to the forward propulsion system.

Abstract: A vertical landing and take-off aircraft VTOL transitions from a vertical takeoff state to a cruise state where the vertical takeoff state uses propellers to generate lift and the cruise state uses wings to generate lift. The aircraft has an M-wing configuration with propellers located on the wingtip nacelles, wing booms, and tail boom. The wing boom and/or the tail boom can include boom control effectors. Hinged control surfaces on the wings, tail boom, and tail tilt during takeoff and landing to yaw the vehicle. The boom control effectors, cruise propellers, stacked propellers, and control surfaces can have different positions during different modes of operation in order to control aircraft movement and mitigate noise generated by the aircraft.

Abstract: A separating element for a platform cabin comprises at least one leaf subjected to a return force toward its open position, and, for the or each leaf, a return member for returning the leaf toward its closed position and comprising a first end articulated at an articulation point movable jointly with the leaf. This return member also comprises a second end mounted movably relative to the partition between an active position and an inactive position, such that when the leaf is open and the second end is in the active position, the return member exerts, on the leaf, a return force returning the leaf toward its closed position, and when the leaf is open and the second end is in the inactive position, the return member is in a second configuration in which it does not exert a force returning the leaf toward its closed position.

Abstract: A boom for an aircraft, and, more particularly, to a tail boom for a helicopter, whereby the tail boom may comprise a watertight compartment and watertight bulkheads. The watertight bulkheads may close at least one end of watertight compartment. Watertight bulkhead may include attachment device, frame, and watertight fabric.

Abstract: A robot including a hybrid fan-based and fluid-based propulsion system to provide thrust, such as deceleration during fall to create a smooth landing or to provide a quick reduction in velocity, and to provide actuation/controlled motion, such as to hover after quick deceleration and to control orientation or pose. The hybrid propulsion system uses discharging of pressurized fluid and exhausted gas (or fluid in some cases) from ducted fans (or propellers, impellers, and the like) to provide controlled thrust and/or lift forces. The hybrid propulsion system uses of pressurized fluid for generating larger or primary thrust and quick changes in velocity. The hybrid propulsion system includes a fan-based propulsion assembly with ducted fans that use environmental air (or fluids) to provide lower or secondary thrust. Both types of propulsion can be integrated into a robot or robotic figure to move the robot during flight (e.g., during falling or hovering).

Abstract: An aerial vehicle safety apparatus includes an expandable object and an ejection apparatus. The ejection apparatus includes a container that accommodates the expandable object and has an opening provided on one end side, a moving member provided in the container, the moving member including an emission base carrying the expandable object on a side of the opening, the moving member being movable along an inner wall of the container, and a driver that ejects the expandable object by moving the moving member toward the opening. A space located opposite to the opening when viewed from the emission base and surrounded by the container and the moving member communicates with a space located outside the space through a communication portion.

Abstract: An aircraft seat includes infinitely adjustable, lateral tilt control within a specified range. The aircraft seat includes a stationary support, a tilting frame rotatably or translatably attached to the stationary base, and a tilt control mechanism to adjust the tilt within the defined range and positively lock the frame without back-driving. The tilt control mechanism may include a plurality of linkages connected to the stationary support and the tilting frame, and to each other via a threaded block; a threaded shaft adjusts the linkages and thereby adjust the tilt. Alternatively, the tilt control mechanism comprises a curved rack and a pinion. The threaded block and threaded shaft, or the rack and pinion define ACME threads to prevent back-driving.

Abstract: A vertical take-off and landing multirotor aircraft with an airframe and at least eight thrust producing units, each one of the at least eight thrust producing units being provided for producing thrust in an associated predetermined thrust direction, wherein at least four thrust producing units of the at least eight trust producing units form a first thrust producing units sub-assembly, and at least four other thrust producing units of the at least eight thrust producing units form a second thrust producing units sub-assembly, the first thrust producing units sub-assembly being operable independent of the second thrust producing units sub-assembly.

Abstract: Lock apparatus and related methods for use with drones are disclosed. A disclosed drone assembly includes a wing, a keel-beam, an adapter positioned on an end of the keel-beam, and a lock configured to receive the adapter. The lock includes a first lock portion coupled to the wing and a second lock portion rotatable relative to the first lock portion between a first position and a second position. The lock is configured to (a) couple the keel-beam to the wing when the second lock portion is in the second position and (b) decouple the keel-beam from the wing when the second lock portion is in the first position.

Abstract: A heating element and conductive element system may include a heater conductive element and a heating element. The heater conductive element and the heating element may be integral components. The heater conductive element and the heating element may be discrete components. The heater conductive element may be configured for enhanced mechanical fatigue compared to typical conductive element.

Abstract: In one embodiment, a dual configuration aircraft lavatory includes a plurality of walls enclosing and defining a lavatory interior space, wherein one of the walls is coextensive with a portion of the cabin. Within the lavatory interior space are a toilet, a washing station and a waste receptacle movable between a first position and a second position. In the first position, the waste receptacle is attached to a wall of the lavatory between the washing station and a door wall. In the second position, the waste receptacle occupies a second predetermined volume of space in the aircraft cabin separated from a first predetermined volume of space occupied by the waste receptacle in the first position. Moving the waste receptacle from the first position to the second position reveals additional space within the lavatory sufficient so that two adult humans simultaneously fit within the lavatory interior space.

Abstract: A deployable cabin attendant seat system may include a primary cabin attendant seat, an auxiliary cabin attendant seat, a main support coupled to at least one of the primary cabin attendant seat or the auxiliary cabin attendant seat, and an actuation assembly coupled to at least the primary cabin attendant seat. The actuation assembly may be configured to actuate the primary cabin attendant seat relative to the auxiliary cabin attendant seat between a stowed seat position and a deployed seat position. The primary cabin attendant seat and the auxiliary cabin attendant seat may be arranged in a side-by-side configuration when the primary cabin attendant seat is in the deployed seat position. The primary cabin attendant seat may be stacked on the auxiliary cabin attendant seat when the primary cabin attendant seat is in the stowed seat position.

Abstract: A lock and release mechanism includes a primary ring with a first surface and a second surface, each surface including a plurality of channels of varying depths. A secondary ring has first and second surfaces, the first surface including a plurality of channels of varying depths. The channels of the secondary ring are aligned with a portion of an opposing channel of the primary ring. Arranged between the primary and secondary rings are a plurality of low friction elements partially arranged within a channel of the primary ring and partially arranged within an opposing channel of the secondary ring. In order to lock and release the mechanism, the primary ring translates relative to the secondary ring such that the bearing balls move within each channel from a first depth to a second depth greater than the first depth.

Abstract: An anti-icing protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud provided with at least one acoustic panel, an air intake lip forming a leading edge of the nacelle, the protection system comprising a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the acoustic panel or panels.

Abstract: An exemplary unmanned aerial vehicle (UAV) mountable to a conductor of an aerial power transmission line system includes a body having a rotor system, a motivation system attached to the body to motivate the UAV along the conductor, a battery carried by the body and electrically connected to at least one of the rotor system and the motivation system, a monitoring tool mounted with the body and an inductive coil carried by the body and in electric connection with the battery, wherein the inductive coil is configured to harvest electricity from the aerial power transmission line system and charge the battery.

Abstract: A method of displacing rotors of an aircraft between a hover mode and an aircraft mode includes rotating a spindle drivingly connected to the rotors about a spindle axis to displace the rotors between the hover and aircraft modes until a component displaceable with the spindle abuts against a downstop of the aircraft and applies a load against the downstop. The method includes passively maintaining the component against the downstop to maintain the load applied against the downstop. An aircraft is also disclosed.

Abstract: A magnetic fire seal for a nacelle may comprise an exterior surface configured to form a sealing interface and an interior surface opposite the exterior surface. A fire-resistant material may be disposed between the exterior surface and the interior surface. A magnet may be located at the interior surface proximate the sealing interface. A portion of the fire-resistant material may be located between the magnet and the exterior surface.

Abstract: An ultra light weight aircraft composite galley architecture system and method comprises composite construction of a partially molded aircraft monument structure based on embedded load bearing hoops and beams used in conjunction with pre formed composite flat panel construction. An upper L shaped structural section mates with a lower inverted L shaped structural section forming a structure upon which additional panels are joined to form the complete composite galley. This system and method of construction produces a high strength aircraft monument capable of maintaining aircraft structural flight and crash load requirements without external monument extrusions for support. This galley architecture system and method of construction creates an aircraft monument with desirable reduction in weight with no loss of required structural strength.