A transfer of ordnance units (20) from a first aerial vehicle (10) to a second aerial vehicle (14) performed while both vehicles are airborne. The first aircraft (10) is used as an ordnance storage, ordnance delivery and ordnance supplier platform. The second aircraft (14) has the functionality and capability of delivering the received ordnance (20) to designated targets. The first aircraft (10) includes an ordnance storage apparatus, an ordnance transfer assembly (22), a computer-based highly accurate ordnance transfer control apparatus, and an ordnance transfer apparatus operating crew. The ordnance transfer assembly (22) establishes temporarily a transfer link between the aircraft and utilizes an ordnance conveyor mechanism for the delivery of the ordnance units (20). The second aircraft (14) includes a multi-use multi-purpose pylon (16) that receives the transferred ordnance (20) in the proper manner. The aircrafts can be uninhabited.

Apparatus and method for air-to-air arming of aerial vehicles

The wind operated generator has a housing having a shaft opening for receiving an outer turbine tube shaft extending longitudinally through the shaft opening. An inner turbine has an inner tube shaft extending longitudinally through the outer tube shaft. Roller means are provided for supporting the outer and inner tube shafts within the housing. Roller ring means are interposed between the inner and outer tube shafts and the housing for limiting axial movements between the outer and inner tube shafts with respect to the housing. Magnetic means are carried on outer and inner tube shafts with corresponding juxtaposed electromagnetic pick-up means to provide an electrical output, the inner turbine means having scroll-type vanes directing a coplanar flow of air to actuate the outer turbine having open-ended box-type vanes.

Wind operated generator

Unmanned Aerial Vehicle and Method of Operation A method of unmanned aerial vehicle (UAV) flight includes providing horizontal thrust in-line with the direction of forward flight of the UAV (110) using at least one electric motor (120), providing primary vertical lift for the UAV (110) during the forward flight using a fixed and non-rotating wing (125), repositioning the at least one electric motor (120') to provide vertical thrust during transition of the UAV (110) to vertical flight(A) for descent (E), landing the UAV (110) on a surface (270) using a vertical approach after the motor repositioning, and deploying an anchor (150) to secure the UAV (110) to a surface (270).

Unmanned aerial vehicle and method of operation

The present invention relates to an unmanned aerial vehicle system having a multi-rotor type rotary wing. The unmanned aerial vehicle system having a multi-rotor type rotary wing includes a first unmanned aerial vehicle, at least one second unmanned aerial vehicle, and a bridge that connects the first unmanned aerial vehicle and the at least one second unmanned aerial vehicle to be separable from each other, wherein the at least one second unmanned aerial vehicle is moveable by the first unmanned aerial vehicle in a state where the at least one second unmanned aerial vehicle is coupled to the first unmanned aerial vehicle by the bridge without being driven, and the at least one second unmanned aerial vehicle is separable from the first unmanned aerial vehicle which is in flight.

Unmanned aerial vehicle system having multi-rotor type rotary wing

An active platform (1) for the landing of an aircraft on an access facility (B) including a support basement (2), suitable to be fixed on a reference surface (P) belonging to the aforesaid access facility (B), and a landing footboard (3), superiorly connected with the support basement (2) and suitable to receive the aircraft. In this case, the landing platform (1) comprises compensation and levelling means (4), operatively connected with moving means (5) so as to constantly keep the landing footboard (3) on a substantially horizontal plane when atmospheric agents, fluid masses and/or adjacent structures interfere with the access facility (B).

Active platform for the landing of an aircraft on an access facility

An aerial aircraft carrier is disclosed having a first and a second shuttlecraft that have a cantilever fluselage extending between the first and second shuttlecraft. The cantilever fuselage is disposed at both ends within a fuselage housing that depends from the under-carriage of the first (lead) and second (aft) shuttlecraft, the cantilever fuselage forming a longitudinal member therebetween. A means for elevating a plurality of aerodynamically stable platforms, (wing assemblies), is affixed to the cantilever fuselage. The wing assemblies each have a wing span member attached thereto, with control surfaces, for stabilizing an aircraft (a payload) that is secured in a mount assembly. An aircraft landing in the mount assembly is secured by an application of negative air pressure against a landing gear pod of the aircraft, and as the aircraft is adhered to a pair of mount elements, by evacuation of air, forming a suction seal peripheral to the environmental surfaces of the landing pod, the wing span members aerodynamically stabilize the weight of the aircraft on the wing assembly platforms. The pilot of the retrieved aircraft then feathers the rotors to his/her aircraft, the weight thereof being primarily supported by the aerodynamic lift of the wing span members. The aircraft is then retrieved in flight, aerodynamically stabilized and can be serviced while in flight. A reverse sequence allows the secured aircraft to be launched from the carrier apparatus.

Robert H. Vollmerhausen

Papers

Aerial aircraft carrier