Systems and methods for countering an unmanned air vehicle are disclosed. An example method includes detecting a target UAV via a first component of a target acquisition system. The example method further includes, in response to detecting the target UAV, directing, by executing one or more computer-readable instructions of a launch control system in communication with the target acquisition system, an interceptor UAV to launch. The example method further includes, subsequent to the launch, tracking the target UAV via a second component of the target acquisition system, the second component carried by the interceptor UAV. The example method further includes, when the target UAV is within a target range of the interceptor UAV, deploying a disabling element from the interceptor UAV toward the target UAV.

Systems and methods for countering an unmanned air vehicle are disclosed. An example method includes detecting a target UAV via a first component of a target acquisition system. The example method further includes, in response to detecting the target UAV, directing, by executing one or more computer-readable instructions of a launch control system in communication with the target acquisition system, an interceptor UAV to launch. The example method further includes, subsequent to the launch, tracking the target UAV via a second component of the target acquisition system, the second component carried by the interceptor UAV. The example method further includes, when the target UAV is within a target range of the interceptor UAV, deploying a disabling element from the interceptor UAV toward the target UAV.

A T-tail joint assembly is described that is used to mechanically couple a left and right horizontal stabilizer to a vertical stabilizer. In one embodiment, the T-tail joint assembly comprises a plurality of lower rib chord members, each having a first base member, a first fin projecting from a first surface of the first base member, notches in the first fin proximate to ends of the first base member, and attachment members projecting from a second surface of the first base member that opposes the first surface. The T-tail joint assembly further comprises a plurality of upper rib chord member, each having a second base member, a second fin projecting from a surface of the second base member, and notches in the second fin proximate to ends of the second base member. The T-tail joint assembly further comprises a plurality of spar fittings disposed between the upper rib chord members and the lower rib chord members, wherein the spar fittings engage the notches in the first fin of the lower rib chord members and the notches in the second fin of the upper rib chord members, and a plurality of spar chords coupled to and separating pairs of the upper rib chord members and the lower rib chord members, wherein the plurality of spar chords is proximate to ends of the first base member and the second base member.

A T-tail joint assembly is described that is used to mechanically couple a left and right horizontal stabilizer to a vertical stabilizer. In one embodiment, the T-tail joint assembly comprises a plurality of lower rib chord members, each having a first base member, a first fin projecting from a first surface of the first base member, notches in the first fin proximate to ends of the first base member, and attachment members projecting from a second surface of the first base member that opposes the first surface. The T-tail joint assembly further comprises a plurality of upper rib chord member, each having a second base member, a second fin projecting from a surface of the second base member, and notches in the second fin proximate to ends of the second base member. The T-tail joint assembly further comprises a plurality of spar fittings disposed between the upper rib chord members and the lower rib chord members, wherein the spar fittings engage the notches in the first fin of the lower rib chord members and the notches in the second fin of the upper rib chord members, and a plurality of spar chords coupled to and separating pairs of the upper rib chord members and the lower rib chord members, wherein the plurality of spar chords is proximate to ends of the first base member and the second base member.

A VTOL (vertical take-off and landing) box-wing aerial vehicle with multirotor to provide VTOL flight includes a detachable cabin, centered fuselage, a pair of first wings extending outward from the upper portion of the fuselage and a pair of second wings extending outwardly and from the lower portion of the fuselage. The first and second wings are spaced apart longitudinally and vertically. The pylon joints the first wing and second wing at the tip to form the box-wing. The pylon includes heading control rudder. Secured to the wing or pylon or both wing and pylon, an overhead boom extending longitudinally to support a plurality of lift rotors or tiltable rotors for VTOL flight. Finally, the overhead boom mounted tiltable rotors propel the vehicle forward to generate lift from the wings. Furthermore, the wings are equipped with elevators and ailerons for flight control.

An aircraft apparatus is disclosed that has a fuselage boom having proximal and distal ends, a wing coupled to a proximal end of the fuselage boom and at least one transparent stabilizer coupled to a distal end of the fuselage boom.

An aircraft apparatus is disclosed that has a fuselage boom having proximal and distal ends, a wing coupled to a proximal end of the fuselage boom and at least one transparent stabilizer coupled to a distal end of the fuselage boom.

A method and system for attaching a vertical stabilizer to an aircraft fuselage using a clevis system is disclosed. A composite skin is installed over the aircraft fuselage. The composite skin has apertures for receiving a plurality of clevises in a clevis system. The plurality of clevises is inserted through the apertures in the composite skin. Each of the plurality of clevises is secured to a frame member in the aircraft fuselage. The vertical stabilizer has a multi-spar box connected with a base rib assembly having a plurality of lugs. The base rib assembly of the vertical stabilizer is engaged with the clevis system. The plurality of lugs in the base rib assembly is secured to the plurality of clevises in the clevis system. Attachment of the vertical stabilizer to the aircraft fuselage, as well as subsequent inspection, may be performed from outside the aircraft.

A method and system for attaching a vertical stabilizer to an aircraft fuselage using a clevis system is disclosed. A composite skin is installed over the aircraft fuselage. The composite skin has apertures for receiving a plurality of clevises in a clevis system. The plurality of clevises is inserted through the apertures in the composite skin. Each of the plurality of clevises is secured to a frame member in the aircraft fuselage. The vertical stabilizer has a multi-spar box connected with a base rib assembly having a plurality of lugs. The base rib assembly of the vertical stabilizer is engaged with the clevis system. The plurality of lugs in the base rib assembly is secured to the plurality of clevises in the clevis system. Attachment of the vertical stabilizer to the aircraft fuselage, as well as subsequent inspection, may be performed from outside the aircraft.

Integration driving mechanism for fin control assembly applied for UAV, aerial observation equipment, comprises: the control assembly, the fin root assembly, the fin shaft. The control assembly is small size, high temperature operation, waterproof ability, vibration resistance, easily replacement and reparation that is still warrant the operation condition.