A directional control system for a hybrid transportation vehicle for ground and air transportation. The vehicle has at least one steerable wheel for use in ground operation, the wheel being connected to a steering mechanism, wings having moveable control surfaces, and a tail having a moveable control surface. The system has a first shaft having a first control input at one end, wherein the first shaft is linked to the steering mechanism and a second shaft that extends through the first shaft and is independently rotatable and slidable with respect to the first shaft. The second shaft has a second control input at one end, a first linkage configured to transmit a rotational movement of the second shaft to control the moveable control surfaces on the wings, and a second linkage configured to transmit an axial movement of the second shaft to control the moveable control surface on the tail.

A directional control system for a hybrid transportation vehicle for ground and air transportation. The vehicle has at least one steerable wheel for use in ground operation, the wheel being connected to a steering mechanism, wings having moveable control surfaces, and a tail having a moveable control surface. The system has a first shaft having a first control input at one end, wherein the first shaft is linked to the steering mechanism and a second shaft that extends through the first shaft and is independently rotatable and slidable with respect to the first shaft. The second shaft has a second control input at one end, a first linkage configured to transmit a rotational movement of the second shaft to control the moveable control surfaces on the wings, and a second linkage configured to transmit an axial movement of the second shaft to control the moveable control surface on the tail.

A steering assembly includes a movable anchor. Movement of the anchor in a first direction is restricted. A first linkage is coupled to the anchor and a second linkage it rotatably coupled to the first linkage. The second linkage is configured to couple to a contactor. A drive mechanism moves the second linkage relative to the first linkage. At least one of moving the second linkage and moving the anchor maneuvers the contactor to a desired position.

A steering assembly includes a movable anchor. Movement of the anchor in a first direction is restricted. A first linkage is coupled to the anchor and a second linkage it rotatably coupled to the first linkage. The second linkage is configured to couple to a contactor. A drive mechanism moves the second linkage relative to the first linkage. At least one of moving the second linkage and moving the anchor maneuvers the contactor to a desired position.

An efficient system and method are provided wherein aircraft may be retrofitted with non-engine drive means controllable to power landing gear wheels to move the aircraft autonomously during ground movement without engines or tow vehicles so that existing landing gear structures are employed to achieve force distribution and load transfer. Non-engine drive means capable of powering a landing gear wheel to move the aircraft during taxi are integrated into existing landing gear designs so that excess drive forces are transferred and distributed through previously evaluated and certificated landing gear structures, including tow fittings, determined to be capable of handling such forces, which eliminates changes to the landing gear and facilitates retrofit and certification. Engines-off taxi technology can be rapidly designed and developed to be retrofitted on existing aircraft nose and/or main landing gear and then efficiently certificated.

The invention relates to a switch (1) for an operating material, comprising an inlet opening (3) for introducing an operating material into an inlet side (2), and several outlet openings (5) for discharging the operating material to an outlet side (4). An actuator (6) comprising a connecting channel (7) is arranged between the inlet side (2) and the outlet side (4), said actuator can be adjusted such that the connecting channel (7) can connect the inlet opening (3) to one of the outlet openings (5). Said actuator (6) consists of at least two parts (9, 10), and the connecting channel (7) is defined, at least in sections, by both parts (9, 10) of the actuator (31, 32, 33, 34).

The present disclosure relates to unmanned aerial vehicles (“UAVs”), systems, and methods for efficiently and safely landing while improving flight performance. In particular, the disclosure incudes a light-weight, gravity-fed, self-deploying landing gear assembly that aligns to the direction of the runway upon landing. For example, the landing gear assembly can include a pin switch and a tear-through barrier that releases and deploys the landing gear assembly. Additionally, the landing gear assembly can include castering wheels that rotate (i.e., swivel) while the UAV is in flight. Furthermore, the landing gear assembly can include friction-disks to reduce the rotation of the castering wheels when the landing gear assembly contacts the ground and receives the weight of the UAV. Moreover, the landing gear assembly can detect that the UAV has landed and can signal the UAV to initiate a roll stop mechanism.

An electric connector assembly is provided that is designed to provide a simple and reliable electric connection between a source of electric power on an aircraft and a plurality of electrical connections, such as those from stator windings, in an electric drive means powering an aircraft landing gear drive wheel. The plurality of drive means electrical connections are individually connected to power distribution elements designed to significantly reduce the number of connectors required to establish an electrical connection between the drive means and an aircraft power supply. The reduced number of connectors is directed out of the wheel and guided along a path by a path guide element to a connector element designed to connect directly with a wire harness or other connection with an aircraft source of electric power. This electric connector design facilitates disconnection and reconnection when removal and remounting of the drive wheel is required.

A landing gear includes structural parts arranged to connect a wheel to a structure of an aircraft, each structural part including two or more interfaces for connection to one or more other of the structural parts or to the structure of the aircraft and two or more webs which extend so as to face one another while delimiting between them a free space and which connect the two interfaces in order to transmit the forces from one to the other.

A method for maximizing traction in an aircraft drive wheel powered by non-engine drive means controllable to move the aircraft on the ground without reliance on the aircraft's brakes and dependence on friction defined by a mu-slip curve. The non-engine drive means is operated to control wheel speed and maintain the powered drive wheel in a maximized optimal traction condition when driving torques are applied to the drive wheel. Traction can be automatically maximized and maintained within an optimal range defined by a relationship between slippage and braking for maximum efficiency of aircraft ground travel under a wide variety of surface, weather, temperature, tire, and other conditions.