An embodiment of the present invention provides an aircraft that includes a fuselage and a rotatable wing disposed above the fuselage. At least one cross-wing driveshaft is disposed within the wing and is driven in rotation by a drive system connected to first and second engines that are located at respective sides of the fuselage beneath the wing. The drive system is so configured that one or both of the first engine and the second engine can drive the at least one cross-wing driveshaft in the event of failure of an engine.

An embodiment of the present invention provides an aircraft that includes a fuselage and a rotatable wing disposed above the fuselage. At least one cross-wing driveshaft is disposed within the wing and is driven in rotation by a drive system connected to first and second engines that are located at respective sides of the fuselage beneath the wing. The drive system is so configured that one or both of the first engine and the second engine can drive the at least one cross-wing driveshaft in the event of failure of an engine.

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.

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.

An unmanned vehicle having a launch configuration and one or more operational configurations. In the launch configuration, one or more engines resides within an engine bay. The unmanned vehicle is generally shaped like a projectile and can be launch from any tube-shaped deployment system using an initial propulsor. The engine bay can be opened, and the engines can be moved into a generally external position with respect to the engine bay for operation of said engines. In some embodiments, the one or more engines can pivot to direct thrust in multiple directions. In some embodiments, the unmanned vehicle includes flight control surfaces to further improve the flight characteristics of the vehicle.

An unmanned vehicle having a launch configuration and one or more operational configurations. In the launch configuration, one or more engines resides within an engine bay. The unmanned vehicle is generally shaped like a projectile and can be launch from any tube-shaped deployment system using an initial propulsor. The engine bay can be opened, and the engines can be moved into a generally external position with respect to the engine bay for operation of said engines. In some embodiments, the one or more engines can pivot to direct thrust in multiple directions. In some embodiments, the unmanned vehicle includes flight control surfaces to further improve the flight characteristics of the vehicle.

A method and device for protecting an adjacent rupturable component including positioning a sheet of puncture resistant, flexible material including one or more openings at or about the structure opening wherein the one or more openings accommodate the rupturable component; permanently or semi-permanently attaching the sheet to the structure at a first portion of an area of the sheet; and positioning the rupturable component through the one or more openings, such that one or more portions of the rupturable component near the one or more openings are protected by the sheet if the structure becomes frayed; wherein the sheet prevents damage to the rupturable component if the structure frays or fractures at or about the structure opening.

The aircraft (10) comprises a fuselage (11) and a rhombohedral wing structure (12) comprising front wings (13, 14) mounted on a front wing-root support (17) and rear wings (15, 16) mounted on a rear wing-root support (18). At least two wings (13, 14) support an engine (24, 26) provided with a propeller (25, 27). The rear end of the fuselage supports an engine (21) provided with a propeller (22). The aircraft comprises means (28 to 35) for tilting said engines, the rotary shaft of each of the propellers being tilted between an orientation parallel to the main axis of the fuselage and an orientation perpendicular to the main axis of the fuselage and to an axis extending through the ends of the front wings.

The aircraft (10) comprises a fuselage (11) and a rhombohedral wing structure (12) comprising front wings (13, 14) mounted on a front wing-root support (17) and rear wings (15, 16) mounted on a rear wing-root support (18). At least two wings (13, 14) support an engine (24, 26) provided with a propeller (25, 27). The rear end of the fuselage supports an engine (21) provided with a propeller (22). The aircraft comprises means (28 to 35) for tilting said engines, the rotary shaft of each of the propellers being tilted between an orientation parallel to the main axis of the fuselage and an orientation perpendicular to the main axis of the fuselage and to an axis extending through the ends of the front wings.

An apparatus including a thrust vectoring system including a centrifugal fan and a nozzle configured to output an exhaust from the centrifugal fan, wherein the thrust vectoring system is configured to controllably orient at least one of, the centrifugal fan or the nozzle, to vector a thrust generated by the exhaust.