Devices, systems, and methods are provided in which a wing of a tiltrotor aircraft is rotated during operational flight, for example from a position perpendicular to the aircraft's fuselage through an angle of 30 or more in the direction of flight. This effectively narrows the maximum width of the aircraft, and facilitates maneuvering through closely spaced obstacles.

A pivoting wing system, capable of vertical take-off and landing, having a hub connected to one or more wings provided on a spanwise axis. The wings are further provided with one or more thrust producing devices mounted to the top and bottom of the wings. The thrust producing devices are configured pivot the wings about the spanwise axis. The wings generate lift for forward flight situations, and the configuration allows for controlled vertical and horizontal flight. The wings may also be configured as rotary elements and enable the system to take flight like a helicopter.

An improved aircraft system is provided. The improved aircraft system comprises an adjustable vortices device that may be attached to an aircraft to create various vortices effects, which increase take-off weight and improve low-speed handling of the aircraft. The adjustable vortices device comprises a linear actuator, a pivot mechanism, and a vortex generator. The pivot mechanism is operably connected to the linear actuator in a way such that the translational energy of the linear actuator causes the pivot mechanism to rotate about a central axis. The vortex generator is moveably attached to a surface of the aircraft and coupled to the pivot mechanism in a way such that rotating the pivot mechanism causes the vortex generator to rotate about a central axis, which alters the angle the vortex generators move through the air.

An improved aircraft system is provided. The improved aircraft system comprises an adjustable vortices device that may be attached to an aircraft to create various vortices effects, which increase take-off weight and improve low-speed handling of the aircraft. The adjustable vortices device comprises a linear actuator, a pivot mechanism, and a vortex generator. The pivot mechanism is operably connected to the linear actuator in a way such that the translational energy of the linear actuator causes the pivot mechanism to rotate about a central axis. The vortex generator is moveably attached to a surface of the aircraft and coupled to the pivot mechanism in a way such that rotating the pivot mechanism causes the vortex generator to rotate about a central axis, which alters the angle the vortex generators move through the air.

An unmanned aerial vehicle (UAV) having wings stowed against a fuselage of the UAV in a first arrangement is disclosed. Methods and systems for deploying the wings into a second arrangement are disclosed. For example, after a launch of the UAV, the UAV monitors for at least one pre-set condition. The at least one pre-condition being a pre-condition associated with deploying wings of the UAV into the second arrangement. Upon detecting the at least one pre-set condition, the wings of the UAV are deployed into a second arrangement. Deploying the wings comprises activating, in response to detecting the at least one pre-set condition associated with the UAV, a gearbox configured to transition the wings from the first arrangement to the second arrangement. Roll control may be maintained throughout launch and deployment.

An unmanned aerial vehicle (UAV) having wings stowed against a fuselage of the UAV in a first arrangement is disclosed. Methods and systems for deploying the wings into a second arrangement are disclosed. For example, after a launch of the UAV, the UAV monitors for at least one pre-set condition. The at least one pre-condition being a pre-condition associated with deploying wings of the UAV into the second arrangement. Upon detecting the at least one pre-set condition, the wings of the UAV are deployed into a second arrangement. Deploying the wings comprises activating, in response to detecting the at least one pre-set condition associated with the UAV, a gearbox configured to transition the wings from the first arrangement to the second arrangement. Roll control may be maintained throughout launch and deployment.

An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

An airborne space anti-missile system provides an offensive anti-missile system that provides a supersonic jet flying in space at 10 times the speed of ultra-high speed jet to deliver air-to-surface missiles towards launch site of an attacking missile. The launching missile is targeted prior to launching or during flight. The supersonic jet comprises: a nuclear plasma jet engine operational in thermosphere, and a stamping jet fusion vector engine or anti-material vector engine for flying in lower atmospheres, no vertical tail and rudder, a pointed wing structure; a fuselage having a length of 60 meters and height of 15 meters, a variable swept wing configuration having a 100 range of wing positions, including a forward position where the wing is disposed forwardly, and wingspan is 200 meters from the fuselage, and a full rearward swept position where wingspan is 60 meters from the fuselage; and electromagnetic space for stealth operations.

An airborne space anti-missile system provides an offensive anti-missile system that provides a supersonic jet flying in space at 10 times the speed of ultra-high speed jet to deliver air-to-surface missiles towards launch site of an attacking missile. The launching missile is targeted prior to launching or during flight. The supersonic jet comprises: a nuclear plasma jet engine operational in thermosphere, and a stamping jet fusion vector engine or anti-material vector engine for flying in lower atmospheres, no vertical tail and rudder, a pointed wing structure; a fuselage having a length of 60 meters and height of 15 meters, a variable swept wing configuration having a 100 range of wing positions, including a forward position where the wing is disposed forwardly, and wingspan is 200 meters from the fuselage, and a full rearward swept position where wingspan is 60 meters from the fuselage; and electromagnetic space for stealth operations.