Abstract: A flying robot (10) with projector, including a movable end (100) and a fixed end (200). A distributed working mode is used on the movable end (100) and the fixed end (200). The movable end (100) includes a top (110), a main body (120) and a bottom (130). The top (110) includes a lift system (112) and one or more proximity sensors (114); the main body (120) is a sealed hollow spherical body or spheroid body made of a film material capable of being used as a rear projection screen, and is filled with a gas of which the density is less than that of the air. The bottom (130) includes one or more rear projectors (131), a wireless communication module (132), a microcontroller (133), a battery (134), a direction and steering controlling device (135), a camera device (136), a sound capturing and reproduction device (137), a height sensor (138) and other sensors, etc. The fixed end (200) includes a wireless communication module (220), a control apparatus (240), a charging port (260), and other data interfaces, etc.

Abstract: An apparatus providing continuous tilt and variable pitch for rotors on a fixed wing VTOL aircraft. An actuator on a housing rotates a first pivot point on a motor mount to tilt a motor to horizontal and vertical positions. Simultaneously, an actuator on the motor mount rotates a fork on a second pivot point on the motor mount to adjust the pitch of the rotors attached to a free end of the motor's drive shaft. A lower swash plate on the drive shaft is attached to the fork. An upper swash plate on the drive shaft is attached to the rotors. The swash plates are attached to each other with a shaft bushing attached to a shaft ball bearing. The shaft bushing allows both swash plates to move linearly along the shaft when the fork is rotated. The shaft ball bearing allows the upper swash plate to rotate with the drive shaft while the lower swash plate remains stationary.

Abstract: In-flight recovery of an unmanned aerial vehicle (UAV). A towline may be deployed by a host aircraft in-flight in order to recover a target UAV that is also in-flight. A reel on the host aircraft may pay out the towline having a fitting thereon. A catch on the target UAV may engage with the fitting on the towline, and the reel may then retract the towline to thereby pull in the target UAV to the host aircraft. The target UAV may then securely attach with the host aircraft.

Abstract: An apparatus for applying a desired amount of mechanical abrasion to plants and selective cutting of undesirable plant material. The apparatus includes a base, a brush and an elevation device for maintaining the base at desirable height. The base has a first longitudinal axis and a plurality of grooves, the grooves being oriented approximately perpendicular to the first longitudinal axis. The brush has a second longitudinal axis and a plurality of bristles and/or blades extending outwardly from the second longitudinal axis. The brush is attached to the apparatus such that the second longitudinal axis is substantially parallel to the first longitudinal axis and the brush is rotatable about the second longitudinal axis. The brush is spaced from the base such that the plurality of bristles engage the plurality of grooves. The base is adjustable enabling the operator to move the base closer or further from the rotating brush/blades.

Abstract: Passenger seat assemblies may be used in vehicles such as aircraft. The passenger seat assembly includes a first wall, a second wall opposite from the first wall, and a passenger seat having a first side and a second side opposite from the first side. The passenger seat is positioned between the first wall and the second wall. The passenger seat assembly is positionable between a forward-facing configuration and an aft-facing configuration. In both the forward-facing configuration and the aft-facing configuration, the first wall is proximate to the first side of the passenger seat and the second wall is proximate to the second side of the passenger seat.

Abstract: A tail rotor assembly coupled to a tailboom of a helicopter includes a tail rotor gearbox having top, bottom and aft sides and a shroud surrounding the tail rotor gearbox. The shroud includes a shroud airframe having top and bottom portions. The tail rotor assembly includes a tail rotor gearbox support assembly configured to support the tail rotor gearbox within the shroud. The tail rotor gearbox support assembly includes a support column coupling the aft side of the tail rotor gearbox between the top and bottom portions of the shroud airframe, an upper support crossbar coupling the top side of the tail rotor gearbox between the support column and the tailboom airframe and a lower support crossbar coupling the bottom side of the tail rotor gearbox between the support column and the tailboom airframe.

Abstract: An aircraft includes: an aircraft body including rotating wings and motors that rotates the rotating wings; wheels arranged on both sides of the aircraft body and rotatably supported around an axis that extends in a left and right direction of the aircraft body; rollers that protrude forward and upward with respect to each of the wheels when the aircraft body is in a horizontal state, and are rotatably supported around an axis that extends in a tangential direction of each of the wheels; and a controller that controls a rotation speed of the motors such that, when the aircraft body is moved in the left and right direction along a vertical wall surface, the aircraft body is inclined forward to bring the rollers into contact with the vertical wall surface, and the aircraft body is inclined to a side where the aircraft body moves in the left and right direction.

Abstract: A protector device includes a plurality of pairs of multi-pronged elements. Each pair of multi-pronged elements includes a first multi-pronged element having a first C-shaped element that has a first straight section, a first end forming a first end spike, and a second end forming a second end spike, and a first connecting element attached to and perpendicular to the first C-shaped element. Each pair of multi-pronged elements also includes a second multi-pronged element including a second C-shaped element connected to the first connecting element of the first multi-pronged element, the second C-shape element having a second straight section, a third end forming a third end spike, and a fourth end forming a fourth end spike, and a second connecting element attached to and perpendicular to the second C-shaped element.

Abstract: An unmanned aerial vehicle, including: a propelling device configured to generate a downward airstream; a package carrier; and wheels arranged so as to allow the package carrier to stand alone. The package carrier includes: vertical members which surround a package in a horizontal direction to prevent falling of the package; support members configured to support a load of the package at positions; and a coupling device configured to hold vertical members so as to enable relative horizontal movement. The support members are each fixed to a corresponding one of the vertical members. The wheels are each mounted to the corresponding one of the vertical members, and enable the relative horizontal movement of the vertical members under a state in which the wheels are on the ground. Through the relative horizontal movement of the vertical members, the package is separable from the support members.

Abstract: In a hybrid flight vehicle, having four rotors attached to a frame and configured to produce propelling force to propel the frame, a gas turbine engine attached to the frame and configured to rotate when fuel is supplied, a generator connected to an output shaft of the engine and configured to generate electric power when driven by the engine, a battery configured to store the electrical power generated by the generator, and four first electric motors each connected to the rotors to drive associated one of the rotors when the electric power is supplied from the battery, and an electronic control unit configured to control flight by regulating driving of the four rotors by the first electric motors. In the vehicle, the output shaft of the engine is attached parallel to at least one among yaw axis, pitch axis and roll axis of the frame.

Abstract: A temperature control equipment, adapted to control the temperature of a docking station for a UAV, wherein a cover of the docking station includes a first and a second vents. The temperature control equipment includes a first and a second temperature control devices. The first temperature control device includes a first and a second airflow openings, and the second temperature control device includes a third and a fourth airflow openings. The first, second, third, and fourth airflow openings, and the first and second vents form a first airflow path; or the first and second airflow openings, the first vent, and a third vent of the cover form a second airflow path; or the first, second, third, and fourth airflow openings, the first, second, and third vents, a fourth vent of the cover form a third airflow path. A heater is located on the first, second or third airflow path.

Abstract: A system comprising a reel, a tether configured to be wound about the reel, and at least one unmanned aerial vehicle attached to the tether. When unmanned aerial vehicle is at rest, the unmanned aerial vehicle resides on the reel. Related methods of operating such a system can be used to extract crop from a field.

Abstract: A cabin of a vehicle for transporting passengers includes a plurality of units, each unit including a seat and a modular seat extension arranged staggered in the units. Each extension includes a shell having a front bottom and a rear opening determined by a hollow volume open towards the rear and a footrest area inside the hollow volume suitable for receiving the feet of a passenger. The shell of each extension includes an invariant portion and a modular portion located in front of the invariant portion. The modular portion making it possible during the fastening thereof to the invariant portion to obtain an extension with a length that can be modified between the opening and the bottom of the shell and, a width of passage towards the aisle between the seats and the extensions of the units is maintained constant during the use of the extensions by the passengers.

Abstract: An apparatus for controlling conditions in a plant cultivation facility includes a lighting system arranged in connection with plants present in an environmentally sealable and closable cultivation facility; a hydronic cooling arrangement for lowering or impeding the rise of temperature in the cultivation facility, the cooling arrangement comprising a cooling manifold present in connection with plants in the cultivation facility and a heat recovery arrangement for utilizing excess heat generated in the cultivation facility. The heat recovery arrangement includes a heat storing system. The heat recovery arrangement includes one or more condenser dryers/coolers for collecting water and/or heat absorbed in the indoor air of a cultivation facility and a heat pump assembly for transferring the heat, accumulated in the heat storing system by way of the cooling arrangement's circulation water and/or the condenser dryer's/cooler's circulation water, into an independent secondary circuit.

Abstract: A launch vehicle to transport at least one payload into an earth orbit, wherein the launch vehicle comprises a plurality of solar cells on its outer surface. Furthermore, a manufacturing method for a launch vehicle with a plurality of solar cells on its outer surface and a transport method for at least one payload using a launch vehicle with a plurality of solar cells on its outer surface are provided.

Abstract: A system for docking an aerostat on a receiving structure, including an unmanned aerial vehicle that can be controlled so as to move between the aerostat and the receiving structure, carrying a first end of a cable that has a second end fixed to the aerostat or the receiving structure, and to attach said first end to the receiving structure or to the aerostat such that the cable connects the aerostat to the receiving structure.

Abstract: A representative spacecraft system includes a launch vehicle elongated along a launch vehicle axis and having at least one stage carrying a corresponding rocket engine. The representative system further includes an annular support structure carried by the at least one stage and positioned to support a cargo spacecraft having a service module and a cargo module. The cargo module of the cargo spacecraft is positioned along the launch vehicle axis in a direction distal from the support structure, and at least a portion of the service module of the cargo spacecraft positioned within an annulus of the support structure.

Abstract: A representative spacecraft system includes a connecting device, which in turn includes a housing having a common port opening, a first connecting element carried by the housing and positioned to connect with a corresponding first spacecraft connecting structure having a first configuration, and a second connecting element carried by the housing and positioned to connect with a corresponding second spacecraft connecting structure having a second configuration different than the first configuration. At least one of the first and second connecting elements is moveable relative to the other between an operational position and a non-operational position, and each of the first and second connecting elements, when connected to the corresponding first or second spacecraft connecting structure, is positioned to allow transport through the common port opening.

Abstract: A tethered aerial vehicle, connected to an anchorage system in the ground level through a cord, comprising a pair of fixed wings; and a drive assembly. The drive assembly comprises at least two actuators configured to tilt the axle of the propellers. The fixed wings define a center hole located close to a gravitational center of the aerial vehicle. Within the edges of the center hole located close to the gravitational center of the aerial vehicle is a gimbal anchored to the fixed wings' structure. The drive assembly is located within the edges of the center hole and attached to the gimbal in a manner that the gimbal interfaces the connection between the fixed wings and the drive assembly. The drive assembly comprises of at least two propellers mounted on the same axle (“coaxial propellers”) driven by a counter-rotating motor. The coaxial propellers are configured to rotate in opposite directions with respect to each other.

Abstract: A flow body for a vehicle having a flow surface, as well as a skin system attached to the flow surface is proposed. The skin system has a top layer and a foam arrangement positioned between the flow surface and the top layer, wherein the top layer includes an elastic, surface-like material, wherein the foam arrangement includes a first layer of an elastic, compressible open cell foam, wherein the foam arrangement is bonded to the top layer. The skin system has a static shape in an unloaded state, in which the shape defines an outer surface geometry that directly follows the geometry of the respective flow surface, and the skin system has a deflected shape when the flow body is subjected to turbulent air flow. The deflected shape at least temporarily compresses the foam arrangement.