Abstract: An aircraft designed with three wings located on either side of the fuselage. The forward wing has a downward angle with a curved top and bottom surface. The upper wing is located towards the rear of the aircraft and above the forward wing. The lower wing is located below the upper wing and slightly forward. It is also located to the rear and below of the forward wing. The outer ends of all three wings come into contact at one point. The forward wing uses the Coanda effect to increase the airflow across the top surface of the bottom wing. The aircraft can be designed so that it is large enough to carry people and/or cargo, or to be small enough to be flown as a toy aircraft. The like design can use any type of aircraft engine commonly used today. One embodiment of the aircraft has two turbines, shaft-coupled to a power source, located on either side of the forward end of the fuselage.

Abstract: A firearm safety system for the prevention of undesired or unauthorized discharge of a firearm by a person other than an authorized person. The safety system is made up of a computer chip which is implanted into the authorized user's anatomy for verification of the user. The information from the computer chip is received by a sensor connected to a firearm and the information processed by a processor. If the information received from the computer chip matches that of an authorized user, the firearm can be discharged by the authorized user.

Abstract: A rack system (10) is disclosed for use on a vehicle (12) which carries weapons containers (48, 50) containing one or more missiles or rockets (52). A crane mounted on the system pivots each weapons container independently from a storage position to a vertical launch position. Locking devices lock the weapons containers in the storage position for transport and in the vertical, launch position.

Abstract: A cooled rotor aerofoil blade having a closed cycle cooling system containing sodium comprises an aerofoil cross-section portion and a root portion which are interconnected by a shank portion. The shank portion encloses two pairs of chambers one chamber of each pair being interconnected with the other chamber by a heat exchanger provided on the upstream face of the shank portion. The aerofoil cross-section portion encloses a plurality of length-wise extending passages which interconnect the two pairs of chambers within the shank portion with a further chamber provided within the tip of the aerofoil cross-section portion. A closed cycle cooling system is thus defined which contains sodium as the cooling medium.In operation, sodium contained within the passages of the aerofoil portion is vaporized, passes down the passage into the chambers and thence into the heat exchanger where it condenses.