Abstract: The present invention includes an a plurality of first variable speed motors mounted on a tail boom of the helicopter; one or more fixed pitch blades attached to each of the plurality of first variable speed motors; and wherein a speed of one or more of the plurality of first variable speed motors is varied to provide an anti-torque thrust.

Abstract: A protective hood for air travel including a plurality of deformable partitions coupled to each other defining an inner cavity, wherein in a folded position the inner cavity is collapsed to a negligible size and in an unfolded position the inner cavity is configured to comfortably confine an human head, wherein one of the partitions includes a deformable opening configured to be stretched and fit over a head, and at least one coupling mechanism configured to attach one of the deformable partitions to an aircraft seat.

Abstract: A system for cushioning airdropped cargo includes a pallet supporting associated cargo. At least one lower inflatable impact attenuator in the form of a pneumatic cushion is positioned between the pallet and the cargo. A compression pad is positioned between the lower pneumatic cushion and the cargo. At least one upper pneumatic cushion is positioned atop the cargo. A parachute is connected by parachute rigging to the pallet.

Abstract: Described is an apparatus and method of an aerial vehicle, such as an unmanned aerial vehicle (“UAV”) that can operate in either a vertical takeoff and landing (VTOL) orientation or a horizontal flight orientation. The aerial vehicle includes a plurality of propulsion mechanisms that enable the aerial vehicle to move in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll) when in the VTOL orientation. The aerial vehicle also includes a ring wing that surrounds the propulsion mechanisms and provides lift to the aerial vehicle when the aerial vehicle is operating in the horizontal flight orientation.

Abstract: Aerostructure actuator systems include first and second shaft portions having respective first and second mandrels and a clutch assembly arranged within the first mandrel and connecting the shaft portions. The clutch assembly includes a post with a post extension fixedly connected to the second mandrel. A first bearing is installed on the post extension to frictionally engage with a portion of the post. A second bearing is installed on the post. A spacer is arranged between the bearings and is fixedly attach to the first mandrel. A load setting nut is configured to engage with the post extension and apply a compressive force to the bearings and spacer against the post. The compressive force defines a coupling limit between the shaft portions. The clutch assembly is configured to rotationally decouple the shaft portions from each other if a relative rotational speed between the shaft portions exceeds the coupling limit.

Abstract: Features for in-flight recovery of an unmanned aerial vehicle (UAV). A towline may be deployed by a host aircraft in-flight to recover an in-flight target UAV. The towline or portion thereof may be oriented nearly vertical. The towline may have a fitting thereon. A capture mechanism on the target UAV may have one or more deployable flaps that engage with the near vertical towline and fitting. The flaps may stow to secure the target aircraft to the towline and fitting. The host aircraft may then retract the towline to pull in the target UAV to the host aircraft using a hoist system having a winch. A latching system located in a pylon of the host aircraft, which may be under a wing, may have a towline connector that engages with and secures the target UAV. The host aircraft may have multiple hoist systems for deployment and/or recovery of multiple target UAV's.

Abstract: A tethered uni-rotor network of satellite vehicles, is made up of a central hub with multiple tethers radiating outward in a hub-and-spoke arrangement. Each tether attaches to a satellite vehicle; each having lifting airfoil surfaces, stabilizers, control surfaces, fuselages, and propulsion systems. The entire system operates in a persistent state of rotation, driven by the propulsion units on each satellite vehicle, so the airfoils generate lift which supports each satellite vehicle and a distributed portion of the weight of the central hub. As the system rotates, centrifugal forces pull each satellite vehicle outwards, which keeps each tether taught and applies tension across each of the lifting surfaces, thereby alleviating the bending moment common to fixed-wing aircraft.

Abstract: A canopy for an aircraft includes a pivot assembly including a first hinge and a second hinge opposite from the first hinge. The first hinge includes a first pivot slot having a first length. The first pivot slot is configured to retain a first aft pin of a fuselage of the aircraft. The second hinge includes a second pivot slot having a second length. The second pivot slot is configured to retain a second aft pin of the fuselage of the aircraft. The first length differs from the second length.

Abstract: A life preserver head restraint may be configured to inflate in response to deployment of a parachute assembly. The life preserver head restraint may comprise an inflatable volume and a charge tank fluidly coupled to the inflatable volume. In an inflated state, the life preserver head restraint may restrict head movement during line stretch of the parachute assembly.

Abstract: A remotely controlled multirotor aircraft having a frame that includes a first and a second peripheral portions, to which at least one first and one second motor can be respectively coupled, and a central portion including a first end and a second end, to which the first peripheral portion and the second peripheral portion are respectively coupled, so that the first peripheral portion develops in a plane that is different from that in which the second peripheral portion develops; furthermore, the central portion also includes a coupling mechanism allowing the coupling between the central portion and a mobile device having video acquisition ability.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed for a first link to rotate about a pin joint, a second link rotatably coupled to the first link, the second link having a nozzle at a first end and a weight at a second end opposite the first end, and a fluid inlet including a funnel portion and an opening, the funnel portion having a conical taper converging towards the opening.

Abstract: An ejection system may comprise an ejection seat and a rail assembly. A plurality of sliders may be coupled to the ejection seat. The rail assembly may include a rail defining a channel and a rail insert located in the channel. The rail insert may define an insert channel configured to receive the plurality of sliders.

Abstract: Disclosed are various embodiments for an electromagnetic automatic deactivation device (ADD). An ADD may be used with an ejector-spring static line reserve parachute, common in low-altitude military jumps. Activating a reserve parachute from within an aircraft, while being towed by an aircraft, or when trapped inside another parachute, can result in significant injury, and may be fatal. An ADD may be added to the internal packaging of a reserve parachute to prevent its accidental activation. An ADD may be configured to sense ambient pressure, linear and rotational motion, and other data, to identify hazardous environmental conditions. An ADD may be further configured to support a towed jumper whose static line is cut, by strategically deactivating the electromagnetic assembly, and therefore activating the reserve parachute. The ADD may be modified to include the ability to override the ADD with a secondary pull on the ripcord handle.

Abstract: A lumbar support system for use in an ejection seat of an aircraft, comprising may comprise a pump; a plurality of bladders fluidly coupled to the pump; and a controller electrically coupled to the pump, the controller operable to: select a bladder in the plurality of bladders to fluidly isolate the bladder from a remainder of bladders in the plurality of bladders; and command the pump to inflate the bladder.

Abstract: The presently disclosed embodiments relate to vertical takeoff and landing (VTOL) aircraft that have the capability of hovering in both a “nose forward” and a “nose up” orientation, and any orientation between those two. The disclosed aircraft can also transition into wing born (non-hovering) flight from any of the hovering orientations. In addition, certain of the disclosed embodiments can, if desired, use only vectored thrust control to maintain stable flight in both hover and forward flight. No control surfaces (e.g. ailerons, elevators, rudders, flaps) are required to maintain a stable vehicle attitude. However, the disclosure contemplates aircraft both with and without such control surfaces.

Abstract: A lateral support system for use in an ejection seat of an aircraft may comprise a pump; a first side bladder fluidly coupled to the pump; a second side bladder fluidly coupled to the pump, the second side bladder configured to be disposed opposite the first side bladder. The first side bladder and the second side bladder may be coupled to a seat pan pad or a seat back pad. The lateral support system may further include a third side bladder and a fourth side bladder coupled to a seat pan pad, and the first side bladder and the second side bladder may be coupled to a seat back pad.

Abstract: A control system for an ejection system may comprise an ejection seat, a canopy jettison system, a sensor, a controller, and a tangible, non-transitory memory configured to communicate with the controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising receiving an eject command, polling the sensor for a sensor data, receiving the sensor data, passing the sensor data to a time delay logic, determining via the time delay logic a time delay based on the sensor data, and actuating the ejection seat based on the time delay.

Abstract: Linkage assemblies for moving tabs on control surfaces of aircraft are disclosed herein. An example aircraft includes a wing including a fixed wing portion and a trailing edge control surface. The trailing edge control surface includes a fore panel rotatably coupled to the fixed wing portion and an aft panel rotatably coupled to the fore panel. The wing also includes a linkage assembly including a rocking lever rotatably coupled to a bottom side of the fore panel, a trailing edge link having a first end rotatably coupled to the fixed wing portion and a second end rotatably coupled to the rocking lever, and an aft panel link having a first end rotatably coupled to the rocking lever and a second end rotatably coupled to a bottom side of the aft panel.

Abstract: A Stability and Control Augmentation System (“SCAS”) module comprising one or more SCAS actuators, the or each SCAS actuator comprising a mechanical component that translates rotational motion to linear motion along a first axis of said SCAS; one or more electric motors for driving linear movement of the mechanical component in response to a command signal; and one or more angular transducers to detect the position of the SCAS actuator along the first axis.

Abstract: A supplemental oxygen assembly for a vehicle can include a container and a flow assembly attached to and/or configured to be contained within the container in a stowed position and to extend from the container in a deployed position. The flow assembly can be configured to be connected to an oxygen supply to supply oxygen to a person in the deployed position. The supplemental oxygen assembly can include an extension device connected to the flow assembly. The extension device can be configured to extend or allow extension of the flow assembly toward an aisle of the vehicle to aid the flow assembly in being reached from or moveable toward an aisle of the vehicle by a person in the aisle.