Abstract: An example reusable high-altitude balloon system includes a balloon with a first end supporting a payload and a second end with an aperture and an apex fitting that is positioned within the aperture. A clamp applies a pressure to a plurality of pleated folds formed in the perimeter of the aperture around the apex fitting to form an air-tight seal against the balloon at the perimeter of the aperture. The reusable high-altitude balloon system further includes control circuitry that controllably releases the apex fitting from the balloon to initiate a descent sequence.

Abstract: A movable object includes a body, one or more propulsion units carried by the body and configured to effect movement of the movable object, and an electrical plug for power and signal transmission. The electrical plug includes at least one signal pin configured to communicate signal, a plurality of power pins configured to transmit electrical power, and a plug substrate configured to support the at least one signal pin and the plurality of power pins. The plurality of power pins include at least one power pin having a first polarity and at least one power pin having a second polarity opposite to the first polarity. The one or more propulsion units are provided with electrical energy via the electrical plug. The plurality of power pins and the at least one signal pin include a first set of power pins and signal pins, and a second set of power pins and signal pins.

Abstract: A battery-powered aerial vehicle has a central controller, one or more propelling modules, and one or more battery assemblies for powering at least the one or more propelling modules. The battery assemblies are at a distance away from the central controller for reducing electromagnetic interference to the central controller. In some embodiments, the aerial vehicle is a fixed-wing unmanned aerial vehicle (UAV) having a central controller, a plurality of rotor units, and one or more battery assemblies. The central controller is in a center unit and the propelling modules are in respective rotor units. Each battery assembly is in a rotor unit in proximity with the propelling module thereof. In some embodiments, the central controller also has a battery-power balancing circuit for balancing the power consumption rates of the one or more battery assemblies.

Abstract: A vehicle includes a first rotor system having a rotor blade having an axis of rotation, a rotatable inboard drive component, and a rotatable outboard drive component. The first rotor system further includes a flexible closed loop component associated with each of the inboard drive component and the outboard drive component. Movement of the closed loop component can selectively cause at least one of rotation of the rotor blade about the axis of rotation and movement of the axis of rotation.

Abstract: Integration driving mechanism for fin control assembly applied for UAV, aerial observation equipment, comprises: the control assembly, the fin root assembly, the fin shaft. The control assembly is small size, high temperature operation, waterproof ability, vibration resistance, easily replacement and reparation that is still warrant the operation condition.

Abstract: The present invention relates to a suite, in particular for an aircraft cabin, comprising: a seat, an ottoman, and a storage cupboard, the suite further comprising a movable table capable of assuming: a stowed state in which the movable table extends in a vertical plane, in which the movable table is arranged between the cupboard and the ottoman, and a deployed state in which the movable table extends in a horizontal plane.

Abstract: Described are examples of a seating arrangement for an aircraft with a first seat in a first accommodation space and a second seat in a second accommodation space, wherein the first and second accommodation spaces are configured to share a common floor space at a floor level of the aircraft. One seating arrangement includes a divider screen located between the first and second accommodation spaces, moveable, by sliding in a direction along the common floor space, between a stowed position permitting passenger egress between the first and second accommodation spaces across the common floor space, and a deployed position preventing passenger egress between the first and second accommodation spaces across the common floor space.

Abstract: A propulsion system for an aircraft comprises a gas turbine engine; a plurality of fuel tanks arranged to contain different fuels to be used to power the gas turbine engine, wherein the fuels have different calorific values; and a fuel manager. The fuel manager is arranged to store information on the fuel contained in each fuel tank and to control fuel input to the gas turbine engine in operation by selection of a specific fuel or fuel combination from one or more of the plurality of fuel tanks based on thrust demand of the gas turbine engine such that a fuel with a lower calorific value is supplied to the gas turbine engine at lower thrust demand.

Abstract: Methods and apparatus to recover unmanned aerial vehicles with kites are disclosed. A disclosed example apparatus includes a tether line to be supported by a kite at a distal end thereof, and a release to deploy and expand a parafoil from at least one of the tether line or the kite in response to the aircraft contacting the tether line.

Abstract: An aircraft including two main landing gears and also a main landing gear bay configured to house, on either side of a vertical median plane, the two main landing gears in a retracted position, the main landing gear bay including a rear transverse wall, a front transverse wall and also an end wall that is approximately perpendicular to the rear and front transverse walls. The main landing gear bay includes at least one strut connecting the rear or front transverse wall and the end wall, approximately positioned in the vertical median plane.

Abstract: Aircraft and related methods are disclosed. In one example, an aircraft comprises an airframe comprising one or more wings, one or more pusher rotors supported by the airframe, and one or more puller rotors supported by the airframe, wherein the one or more puller rotors are positioned behind the one or more pusher rotors. In another example, a method for loading cargo on to an aircraft comprises loading cargo into a fuselage of the aircraft through an upper forward portion of the fuselage.

Abstract: There is provided a vehicle configuration to reduce drag in a fluid stream. The vehicle configuration has a vehicle body. The vehicle configuration further has at least one auxiliary body coupled to, and positioned a distance from, the vehicle body, to form a channel between the at least one auxiliary body and the vehicle body. The vehicle configuration further has one or more exterior profiles of one or more of, the vehicle body and the at least one auxiliary body. The one or more exterior profiles are positioned in proximity to the channel, and are shaped with an aerodynamic shaping, so that the one or more exterior profiles each comprises one or more concave shape portions. When a fluid flow from the fluid stream flows through the channel, the drag resulting from fluid flow interactions between the vehicle body and the at least one auxiliary body is reduced.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. A disclosed example apparatus to recover an aircraft includes a mast extending from a base, a boom extending from the mast at a first end of the boom to a second end of the boom opposite the first end, a tether line extending between the mast to the base and guided by the boom, a portion of the tether line extending between the second end of the boom and the base, and a mount to operatively coupled the a kite to the tether line, the kite to support the tether line as the aircraft contacts the portion for recovery thereof.

Abstract: The present disclosure provides an aircraft monument housing a crew quarters positionable in an aircraft cabin adjacent a longitudinal aisle, and a combination including a passenger suite and an aircraft monument housing a crew quarters. The aircraft monument includes a transverse wall forming part of the monument and separating interior space within the monument from the adjacent passenger suite. The interior space of the monument is divided by a shelf into upper and lower compartments and the crew quarters is positioned in the upper compartment for resting and sleeping use by the cabin crew. The lower compartment may be used by the cabin crew or for locating galley components. The transverse wall may be contoured such that the interior space and the passenger suite nest to maximize density. A footwell serving the passenger suite may be recessed into the transverse wall.

Abstract: A propulsion device for a rotating blade aerodyne with vertical take-off and landing, comprising a hollow chassis and contra-rotating coaxial rotors with fixed-pitch blades. The means for driving the rotation of each rotor comprise motor means and, for each rotor, a rotating part capable of turning about a yaw axis, located in the central opening of the respective rotor and connected to the latter via a ball joint with finger, the centre of which is the intersection of the prospective rotor disc and the yaw axis and for which the prohibited rotation is that about the axis of rotation of the rotor. Means for controlling the inclination of the rotors about the roll and pitch axes. Aerodyne equipped with the propulsion device.

Abstract: A drone-type air mobility vehicle includes a body, a plurality of rotors, and a plurality of rotor arms configured to connect the plurality of rotors to the body. The drone-type air mobility vehicle further includes: a plurality of air flaps provided in the rotor arms, respectively, and configured to be deployed downwards with the respect to the respective rotor arms by gas injected into the air flaps; and a controller configured to determine whether the rotors are abnormal, based on a yaw rate of the mobility vehicle and state information of the rotors, and the controller configured to determine whether to deploy the air flaps according to a result of the determination on whether the rotors are abnormal.

Abstract: A thruster has a first stage and a second stage. The first stage is a plasma source that outputs a plasma. The second stage is an accelerator. In one embodiment, the second stage is a plasma accelerator that accelerates the plasma. In another embodiment, the second stage is an ion accelerator that accelerates the ions from the plasma.

Abstract: A motor vehicle (100) has four centreless wheels (10) drivable for use on the ground and four propellers (16) rotatable within the open centres of the wheels (10) for use in the air. The wheel-propeller assemblies (10, 16) are carried on mounting units (14) secured to a frame (12). The mounting units (14) are rotatable on the frame (12) and the wheel-propeller assemblies (10, 16) are rotatable on their respective mounting units (14), in each case by means of servomotors, to convert the vehicle (1009) from its ground mode shown in FIG. 1 to its air mode as shown in FIG. 2, and also to turn the wheel-propeller assemblies (10, 16) so as to steer the vehicle (100) when on the ground and to tilt the wheel-propeller assemblies (10, 16) so as to direct the vehicle (100) when in the air.

Abstract: A flying robot comprising: a flying body unit; a propulsion portion comprising a plurality of propulsion units configured to cause propulsion to occur by driving rotor blades, the plurality of propulsion units being provided on the flying body unit; a working body unit; a manipulator unit configured to be capable of executing predetermined work and comprising one or more work manipulators provided on the working body unit; and connection units provided on the working body unit and the flying body unit so as to enable the flying body unit to be connected with and disconnected from the working body unit; wherein the flying robot executes the predetermined work by the work manipulators in a state in which the working body unit and the flying body unit are connected at the connection units. The flying robot is caused to execute a wide range of content of work as far as possible.

Abstract: A system for rolling landing gear is illustrated. System includes a skid component attached to an aircraft and comprising at least a skid tube oriented laterally to a longitudinal axis of the aircraft. System also includes at least a wheel journaled on a rotational fulcrum and at least a biasing means attaching the rotational fulcrum to the skid tube, wherein the biasing means comprises at least a leaf spring and exerts a recoil force resisting upward displacement of the rotational fulcrum with respect to the skid tube.