Abstract: A hijacking prevention system which employs a gas which can render everyone in the passenger compartment temporarily unconscious in the event a hijacking occurs. A single switch, hidden in the cockpit and easily accessible to the pilot while flying the plane, would activate the flow of the gas through the existing venting system, while simultaneously locking and/or sealing the cockpit door, and deploying air masks connected to a separate source of fresh air for the pilots. Each of the crew members, and a selected one of the passengers, e.g., an air Marshall or security agent, would be equipped with a transmitter alerting the pilots to the need of deploying the system.
Abstract: An airship (100) for conveyance through a fluid medium in a selected direction of travel. The airship includes a hull adapted to contain a lifting medium therein, wherein the hull (108) includes a first section having a width which varies along the selected direction of travel, the width increasing from a bow of the hull to a maximum width and decreasing from the maximum width to a tail section of the first section; and a second section coupled to the first section and having a width which varies along the selected direction of travel, the width increasing from a leading edge of the second section to a maximum width and decreasing from the maximum width to a stern of the hull.
Abstract: A VSTOL vehicle including a fuselage with two pairs of ducted rotors fully enclosed fore and aft of the fuselage respectively. The fuselage is aerodynamically shaped to generate lift in forward flight. All four ducts are configured such that their center axes are at angles tilted sufficiently forward from the vertical axis of the fuselage. Each ducted rotor is powered by one engine inside the duct behind the rotor. All four rotors and engine shafts rotates counterclockwise, generating substantial angular momentum for gyroscopic effect. Variable inlets of the ducted rotors and vector thrusting of the airflow out of the ducted rotors combine to provide efficient power and control during all phases of flight. The vehicle is configured to meet motor vehicle requirements to drive on streets.
Abstract: A miniature spacecraft is constructed using modular features so as to provide a wide range of possible sizes with a choice of physical attributes. Radially directed bays are arranged around a central cylindrical element which may be used for storing a propulsion tank or canister. Octagonal or other configurations provide rigidity and strength through the use of triangular planetary cylinders which form outwardly facing bays for storage.
Abstract: The invention provides an aircraft having a flight control system (20) comprising an aerodynamic lift generator, and a control system in use the lift provided by the lift generator. The lift control system in one embodiment uses a concentrated mass mounted within a longitudinal body of the aircraft, the concentrated mass comprising at least one existing aircraft function and/or system mounted on a support in a confined area. Bearings permit relative movement between the support for the concentrated mass and at least a portion of the lift generator. An actuator is provided for causing such relative movement whereby in use the center of aerodynamic lift and the center of gravity of the aircraft may be moved relative to one another for effecting flight control.
Abstract: The system of the present invention is a spacecraft architecture for precision motion control of a payload while isolating disturbances and vibrations to the payload. The motion of the payload module is controlled by reacting on the support module using non-contact actuators disposed between the two modules. The motion of the support module is controlled to follow the payload module using external actuators that react against the surroundings. This system achieves vibration isolation down to zero frequency and is not limited by sensor characteristics.
Abstract: A pressure frame, designed in particular for an aircraft, including a dome-shaped cover made of composite materials reinforced with fibers, preferably in one single piece, and cover reinforcing devices connected to the cover or produced integrally therewith. To reduce weight and cost while still fulfilling strain requirements, particularly of large aircraft, and to reduce the risk of destruction due to the cover being turned inside out towards the inside of the aircraft, the cover is of essentially uniform thickness and includes at least one cover reinforcing device which is mounted in the central area on the concave side of the cover. Advantageously, this cover reinforcing device in the central area is formed by a reinforcing structure oriented against the curvature of the cover, such as at truncated cone-shaped, mug-shaped or parabolic structure, with a cavity being arranged between the cover and the reinforcing structure.
May 9, 2000
Date of Patent:
April 30, 2002
Fischer Advanced Composite Components AG
Abstract: Apparatus and methods for performing multiple automated poultry processing operations upon a slaughtered animal or a part thereof via a single machine is described. The machine contains at least two rotary processors in a single frame. A covering surrounds the processors. A venting processor cuts out and removes the vent of a slaughtered animal and in the process removes unwanted fecal or other material from the exterior and the interior of the carcass. The processors integrated into the single machine are coupled by a conveyor line following a preferably generally S-shaped route that carries the carcasses amongst the processors, preferably positioning the carcasses at the optimum registration point for the operation performed by the particular processor.
November 10, 2000
Date of Patent:
March 19, 2002
Stork Gamco Incorporated
Max Volk, Raymond Strawn, Adrianus J. Van Den Nieuwelaar, Bradley K. Gazaway, Hendrikus Werner Peeters
Abstract: A landing gear door assembly for an aircraft, having a closed position to cover the door opening through which the landing gear moves between its stowed and operating position. The door assembly comprises two panel sections, each of which is rotated by a related positioning section so as to rotate about a center of rotation from the closed positions upwardly and outwardly into the aircraft structure to the open position. In one arrangement, each panel section is made up of an inside and outside panel which are hinge mounted with respect to one another. These move in a manner that the outer panel moves in a path deviating from a straight rotational path to provide better clearance with the aircraft structure. In another arrangement, each panel section is rigid and is rotated about a fixed axis of rotation.