Abstract: In an embodiment, a system for synchronizing the rotation of multiple mainframes of an airship includes multiple belt drive systems configured to mechanically rotate the mainframes, a central control system for sending a timing instruction to cause the mainframes to rotate synchronously about their respective rotational axis, wherein the mainframes are axis-aligned about their respective rotational axes and the timing instruction specifies a desired angular displacement of the mainframes, and multiple control units for controlling the belt drive systems to rotate the mainframes, respectively, wherein, for each mainframe, the associated control unit is configured to: receive the timing instruction from the central control system; determine, according to the timing instruction, a rotation instruction based on a size of the mainframe and the desired angular displacement; and instruct the belt drive system controlled by the control unit to rotate the mainframe based on the rotation instruction.

Abstract: A container retention and release apparatus includes an actuator a swaybrace and retention assembly pivotally coupled to the actuator. The swaybrace and retention assembly pivot relative to the actuator between a first position to retain a container and a second position to release the container.

Abstract: A deicing apparatus for aircraft comprises a passive vortex tube adapted to be mounted at a location at or adjacent a component of an aircraft and adapted to heat the component. A deicing method is also disclosed.

Abstract: Equipment and methods that combine the use of wave powered vehicles and unmanned aerial vehicles (UAVs or drones). A UAV can be launched from a wave-powered vehicle, observe another vessel, and report the results of its observation to the wave-powered vehicle, and the wave-powered vehicle can report the results of the observation to a remote location. The UAV can land on water and can then be recovered by the wave-powered vehicle.

Abstract: An unmanned aerial vehicle system is provided including an unmanned aerial vehicle (UAV) having a fuselage, a tether having a first end secured to a winch system positioned in the UAV and a second end secured to a payload coupling apparatus, a payload coupling apparatus receptacle positioned in the fuselage of the UAV, a payload having a handle, wherein the handle of the payload is positioned within a slot in the payload coupling apparatus. A method of securing a payload to a UAV is also provided.

Abstract: A bracket for connecting a traverse of a landing gear to a cabin of a helicopter. A landing gear retainer is fixed around the traverse coaxially to the longitudinal direction of the traverse and at least one cabin clamp mount is fixed to the cabin. The landing gear retainer is in between the cabin and upper and lower pendulum bolts and upper and lower pendulum bearings. A pendulum is in longitudinal direction of the traverse hinged to the landing gear retainer. The invention is further related to an application of such brackets.

Abstract: Control surface actuator assemblies, aircraft hydraulic systems including the same, and associated aircraft and methods. A control surface actuator assembly includes a flight control surface operatively coupled to a support structure, a torque-generating hydraulic actuator configured to apply a torque to pivot the flight control surface, and a variable horn radius (VHR) hydraulic actuator configured to vary an actuator moment arm length for pivoting the flight control surface. In some examples, an aircraft hydraulic system includes such control surface actuator assemblies, and an aircraft includes such aircraft hydraulic systems. In some examples, a method of operating one or more flight control surfaces of an aircraft includes controlling a selected flight control surface by adjusting, with a VHR hydraulic actuator, an actuator moment arm length corresponding to the selected flight control surface and pivoting, with a torque-generating hydraulic actuator, the selected flight control surface.

Abstract: A cargo restraint system includes a driveshaft having a plurality of drive pins and a plurality of first restraints each configured to actuate between a lowered position and a raised position. Each of the plurality of first restraints includes a head to actuate between the lowered position and the raised position, a drive disk rotatably coupled to the head and having a notch to receive a respective drive pin of the plurality of drive pins, and a locking disk to be received by the drive disk in response to the head being in the raised position. The cargo restraint system further includes a handle coupled to the driveshaft and configured to translate the driveshaft and to actuate such that the respective drive pin is received by the notch of the respective first restraint to move the respective first restraint between the lowered position and the raised position.

Abstract: A fuse is provided with a reversible airbrake intended for a projectile, wherein the airbrake is arranged such that errors which occur in the flight path of the projectile can be corrected by performing one or more extensions and retractions of the airbrake. The airbrake includes at least two braking surfaces symmetrically arranged each behind a respective protective device arranged on the casing surface of the fuse, wherein the brake surfaces can be extended and retracted in a rotational direction behind the at least two protective devices via a twist shaft arranged centrally in the fuse.

Abstract: A window element for an aircraft comprises a window frame which has a frame reveal forming an opening, and a receptacle adjoining the frame reveal, an inner window pane which is configured to be inserted into the receptacle, a holding frame which is configured to be inserted into the receptacle and to fix the inner window pane in the receptacle, and a cover which has an opening and is configured to be attached to the window frame and to conceal the window frame around the frame reveal. An encircling inner edge of the cover that forms the opening of the cover lies radially substantially outside an encircling inner edge of the receptacle.

Abstract: A tip gap control system for a ducted aircraft includes a flight control computer including a blade length control module configured to generate a blade tip actuator command and a proprotor system in data communication with the flight control computer. The proprotor system includes a duct and proprotor blades surrounded by the duct. Each of the proprotor blades includes an active blade tip movable into various positions including a retracted position and an extended position. The tip gap control system also includes one or more actuators coupled to the active blade tips. The one or more actuators move the active blade tips between the various positions based on the blade tip actuator command, thereby controlling a tip gap between the proprotor blades and the duct.

Abstract: A system is described and includes a first track assembly for connecting a top surface of a pallet supporting payload to an upper interior surface of a payload bay of an aircraft; a second track assembly for connecting a side surface of the pallet to a side interior surface of the payload bay; and a pallet actuator system for selectively moving the pallet along the first and second track assemblies between a first position in which the pallet is fully extended from the payload bay and a second position in which the pallet is fully retracted into the payload bay.

Abstract: An unmanned aerial comprises: a motor and a propeller assembly connected to the motor comprising: a first structure fixed to the motor, having a cylindrical wall defining an inner space, with a helical slit formed through the cylindrical wall; a second structure comprising a cylinder portion, a part of which is rotatably positioned in the inner space, and at least one protruding portion protruding from the outer surface of the cylinder portion to the outside of the cylindrical wall through the helical slit; and a propeller comprising a cylindrical hub engaging with the cylinder portion of the first structure, rotating blades extending from the cylindrical hub, and at least one rib extending from the cylindrical hub toward the motor, the propeller being configured such that at least a part of the rib detachably engages with the first structure by the at least one protruding portion of the second structure.

Abstract: A bar for controlling a kite comprises a trimming unit for the control lines (back line trimming unit). A length of the control lines can be adjusted by the trimming unit. The trimming unit is mounted in or on the bar and can be adjusted by means of a motor, preferably an electric motor.

Abstract: A damage recovery system of a fuselage of an aircraft, comprising: a tank containing a polyurethane foam; a main duct fluidically coupled to the tank to receive the foam; secondary ducts fluidically coupled to the main duct; and distribution means adapted to allow an outflow of the foam from the secondary ducts. Graphene powder can be mixed and added to the polyurethane foam. In flight, a possible leak (crack or hole) in the fuselage is plugged by the polyurethane foam with graphene powder.

Abstract: A pollination machine (10) with improved cross-pollination abilities may feature a plurality of pollen recirculation chambers with an air circulation manifold (130A, 131A, 133A, etc.) connecting them in a manner that air in one chamber (30A), together with associated pollen, is removed from the one chamber and redirected to a second (30B), and so on until air is returned to the first (30A). The chambers' initial roller entrances (118) will serve to trip blossoms and release both pistol and pollen but a current in the air circulation manifold contains and will deposit foreign pollen grains on the plants' stigmas before they are inundated by the blossoms' own pollen. The air current also collects the plants' pollen and carries it to other chambers so that other plants will be cross-pollinated.

Abstract: Arrangements for an aircraft passenger cabin including a seating area containing first and second passenger seats, a monument disposed at one end of the seating area, and at least one privacy divider deployable in a longitudinal direction of the seating area to divide at least a portion of the seating area for privacy. In some embodiments, the at least one privacy divider includes a first privacy divider adapted to deploy to divide the seating area forward of the first and second passenger seats and a second privacy divider deployable to the seating area between the first and second passenger seats.

Abstract: A tiltrotor aircraft includes a propulsion system with a fixed engine and a rotatable proprotor. The engine is located below the wing of the tiltrotor aircraft, and the rotatable proprotor assembly is mounted on the top surface of the wing. The engine and proprotor assembly are connected via a series of one or more gearboxes that route the engine output from the engine to the proprotor.

Abstract: A man-made vitreous fibre (MMVF) plant growth substrate is provided. The substrate has properties including a volume of 3 to 20 litres, two layers of differing density, and the use of an organic binder selected from formaldehyde free binders. This is found to provide a substrate which allows excellent control of the water and/or nutrient contents within the substrate when used for plant growth.

Abstract: Apparatus and methods for marine capture of an unmanned aerial vehicle (UAV) using water for braking and damping are described. An example capture device is for capturing a UAV aboard a marine vessel located in a body of water. The capture device includes a mounting frame and a capture frame. The mounting frame is configured to be coupled to the marine vessel. The capture frame is configured to be rotatably coupled to the mounting frame. The capture frame is rotatable relative to the mounting frame about an axis of rotation. The capture frame includes a braking member configured to be submerged in the body of water. The braking member is configured to oppose rotation of the capture frame relative to the mounting frame based on a braking force to be applied to the braking member by the body of water.