Abstract: A lock for a thrust reverser comprising a retainer member carried by a pivot pin, the pivot pin being angularly moveable between a first position in which the retainer member retains a part of the thrust reverser and a second position in which the said part of the thrust reverser is not retained by the retainer member. The lock further comprises a lock arrangement for retaining the pivot pin in its first position, the lock arrangement comprising a lock member axially moveable between a locked position, in which it cooperates with the pivot pin to prevent movement of the pivot pin from its first position to its second position, and a retracted position, an arrangement for restricting angular movement of the lock member, and a solenoid actuator arranged to control movement of the lock member.

Abstract: A deployable crew quarters incorporates folding panels and acoustic panels to provide a lightweight on-orbit crew quarter. The deployable crew quarters preferably includes a frame and a plurality of panels mounted to the frame. At least one of the panels is hinged to the frame to allow movement between a stowed position and a deployed position. More specifically, the panels include a front panel coupled to the frame and two side panels moveable coupled to the frame. The two side panels are moveable between a stowed position and a deployed position. Still further, a top panel is also preferably moveable coupled to the frame, wherein the top panel is moveable between a stowed position and a pop-up deployed position. The front panel includes a sliding door panel to allow crew access to the deployable crew quarters. The front panel also preferably extends outward from the frame, which provides space in which a ventilation mechanism can be mounted.

Abstract: An aircraft mechanical structural system which provides an improvement to the existing aircraft structure by reinforcing the fuselage frame aluminum skin (3) and fuselage frame (5), without replacement of any of the existing structural elements. The improvement is comprised of high performance, solid fabric (1) fuselage section jackets (13), fuselage frame metal external paneling (4), and a thermal and cryogenic resistant adhesive (23). The jackets (13) are installed between the aluminum skin (3) and fuselage frame metal external paneling (4). The external paneling (4) is installed between the jackets (13) and entire outside surface of the fuselage frame (5). The external paneling (4) provides a solid foundation for the jackets (13) by preventing sagging into openings in the fuselage frame (5). The adhesive (23) bonds the jackets (13) to the aluminum skin (3) and to the external paneling (4). The adhesive (23) prevents premature crimping, abrasion and tearing of the jackets (13), and rivet (22) failure.

Abstract: A configurable aerial vehicle aerosurface is disclosed, The configurable aerial vehicle aerosurface includes first and second airfoil surfaces in sliding engagement. A plurality of apertures pass transversely through the airfoil surfaces and are disposed in such a relationship so as to define a first position wherein the apertures are in substantial alignment and a second position wherein the apertures are in substantial non-alignment. In this way, the configurable aerial vehicle aerosurface of the present invention can be configured from a first, low drag transport position, to a second, aerodynamic position to provide missile lift and control.

Abstract: Fishing rods are molded with integral line guides or line guide stanchions for attaching conventional or only slightly modified line guides. The preferred line guides are made of metal or ceramic guide inserts in metal frames with one or two support feet. The molding process facilitates the automated manufacture of rods with line guides in proper alignment and positioning. The handle section of the blank can be molded to form an integral foregrip and/or reel seat.

Abstract: An aircraft has a fuselage designed essentially as an aerostatic lift body. Combined lift and propulsion devices are articulated on the fuselage, are provided with propellers and form propulsion units and which in each case can tilt between a lift position, in which the respective propeller rotation plane is essentially horizontal and a propulsion position, in which the respective propeller rotation plane is essentially vertical. Additionally the propeller rotation plane has all-round inclination relative to the output shaft of the associated drive device.

Abstract: The anti-vibration suspension device comprises at least three oblique bars, each articulated on the gearbox and on the structure by means of a rigid lever supporting an oscillating weight and in turn pivotally mounted by means of at least one pivot on this structure, and each lever is also joined to the gearbox by means of at least one torsion spring biassed about a torsion axis substantially perpendicular to the radial plane defined by the axes of the rotor and the corresponding oblique bar.

Abstract: A spacecraft architecture is defined that distinguishes components and sub-systems based on both functional and physical dependencies. On one side of the interface are kernel components that are both functionally and physically independent of the vehicle configuration and functionally and physically independent of the mission-specific system. On the other side of the interface are components that depend on either the spacecraft configuration or the mission-specific system. The kernel components can be included in a variety of spacecraft, independent of the spacecraft architecture and independent of the spacecraft mission. The kernel includes a communications system for communicating with an earth station, a command and data handling processor, and a power regulation and distribution system.

Abstract: An illuminated kite includes a number of light sources extending along its surfaces. These light sources may include a number of light circuits, each of which includes light bulbs extending in a spaced-apart relationship along an electrical wire including a pair of conductors, or one or more electroluminescent panels extending along a cover surface of the kite. The light circuits extend, within transparent sleeves formed in the kite cover, adjacent structural members of the kite. The electroluminescent panels are coated on the surface of the kite cover, or they are formed as elastomeric solids to be placed in pockets on the kite cover.

Abstract: The convertible aircraft with tilting rotors comprises two fixed wings with zero sweep on which an inter-connecting shaft is substantially rectilinear and parallel with the pivot axis but offset from this axis, substantially perpendicular to a longitudinal axis of symmetry of the aircraft, the center of gravity of which, in helicopter mode, is substantially in a vertical plane passing through the pivot axis and, in aeroplane mode, is substantially contained in or is in proximity to another vertical plane passing through the straight line of the aerodynamic centers of the wings.

Abstract: An apparatus and method for moving an airline passenger whereby a Tyvek® sling having handles attached thereto is buckled about an airline passenger and then the passenger is lifted and transferred, by two or more persons grasping the handles, from a wheelchair on the aircraft into an adjacent seat.

Abstract: A trigger lock for use on a firearm having a trigger and a trigger guard includes a plurality of spaced apart pins and means for holding and locking these pins in their spaced apart relationship. These pins cooperate to prevent trigger movement when one of them is placed and held behind the trigger, while another is placed and held against the inside of the trigger guard at a position behind the trigger.

Abstract: A cover-skin web structure for use in flow profiles, in particular aerofoils or their components, comprising a cover skin on the pressure side and a cover skin on the suction side, connected by webs essentially comprising fiber reinforced material. The webs are aligned in the direction of the span and essentially have one or several web cutouts which extend from the cover skin on the suction side to the cover skin on the pressure side. The webs are made of metal in the area of the web cutouts.

Abstract: A patient transport arrangement is provided in the passenger cabin of an aircraft and includes a patient stretcher, medical supplies and equipment, and a compartment that is variably and adaptably useable as a restroom compartment and as a medical care compartment. The compartment is arranged adjacent to the doorway clearance area in front of the cabin door of the aircraft. The adaptable compartment includes a foldable wall element so that the stretcher can extend at least partially into the compartment during take-off, landing and ground operations of the aircraft while leaving the doorway clearance area unobstructed, and so that the stretcher can be repositioned out of the compartment and into the doorway clearance area during cruise flight so as to allow the compartment to be used as a passenger restroom during the flight. This arrangement makes efficient use of space within the passenger cabin that would otherwise be unused during various phases of flight.

Abstract: A method and system is disclosed for using inertial sensors in an Inertial Navigation System (INS) to obtain analytic estimates of angle-of-attack (&agr;) and sideslip angle (&agr;). The inertial sensors consist of one or more accelerometers which produce the estimated signals for angle-of-attack (&agr;) and sideslip angle (&bgr;). Three methods are shown for obtaining &agr; and &bgr; estimates from INS information and are programmed into a nonlinear simulation of a relaxed stability aircraft requiring a high level of artificial stability augmentation in its flight control system. Simulation results from the nonlinear simulation for each of the three methods were compared with the results obtained when conventional probes were used to obtain direct measurements of &agr; and &bgr;.

Abstract: A structure for attaching the landing gear (16) to an aircraft fuselage incorporates a force take-up bar (32), housed coaxially in the barrel (24) of the landing gear. The force take-up bar (32) transmits lateral forces exerted by the landing gear (16) towards the outside of the aircraft when it is on the ground, to a ventral beam (22) connected to the fuselage. This characteristic permits the landing gear barrel (24) to be mounted in the non-reinforced lateral fitting (20), connected to the fuselage.

Abstract: Method, apparatus and sensors for directly interfacing a pilot (1) with the aerodynamic state of the surfaces of an aircraft, in particular allowing the direct sensorization of the conditions of the aerodynamic surfaces during the flight. The pilot (1) wears one or several “data suits” (2), for example on the arm, on the trunk, on the face or on the hands. The information on the boundary layer state is detected by a plurality of sensors (3) located on the different aerodynamic surfaces. A body interface (4) comprising a console (5), a multi-channel conditioning unit (6) and a processor (7) for the data acquisition are connected to the data suit (2). The data suit uses tactile sensations to transmit to the pilot, data responsive to critical airflow conditions at the sensors (3). In an aircraft with many aerodynamic surfaces the pilot can detect directly any arising critical condition.

Abstract: A rotating airfoil aircraft utilizing blown air from a centrifugal fan located at its center to produce lift by causing airflow to travel over the upper surface of the airfoil and outwardly and downwardly from the lower surface of the airfoil. The airflow over the upper surface produces lift by causing a reduced pressure in the blown air current and the downwardly directed air produces an upward lift. This lifting force is used in connection with other lift produced by various factors including the airfoil traveling laterally through ambient air and, particularly during takeoff and landing, by means of the downward exhaust of an engine such as a jet engine. The rapidly rotating airfoil aircraft provides an advantage of providing the leading edge an opportunity to cool during a major portion of each rotation, thereby reducing the effective degree of leading edge heating caused during lateral flight.

Abstract: A portable, hand-holdable controller for interfacing with various flight control, weapons control and other subsystems of an aircraft by a crew member who is not piloting the aircraft. In a preferred embodiment the portable controller includes a keyboard, a mode selector switch and a cursor control. The mode selector switch allows the controller to be interfaced with a plurality of independent multi-function display (MFD) or multi-purpose display (MPD) systems. The cursor control enables the non-pilot crew member to control the cursor on the display being interfaced with. The keyboard allows the non-pilot crew member to enter alphanumeric data or commands to the display being interfaced to. Interfacing is accomplished by coupling the controller via a suitable cable to a convenient point on a control panel of the aircraft. The controller is lightweight and compact and able to be held with one or both hands by the non-pilot crew member or alternatively strapped to a thigh of the crew member.

Abstract: An aircraft landing gear (16) located in front of a fuel tank is equipped with a protection device (22) designed to at least partially automatically disconnect the landing gear (16) from the structure that supports it. For example, the protection device (22) comprises a part (40) hinged on the landing gear, and mechanisms (42) connecting this part to pins (38) through which the landing gear (16) is installed on the aircraft. In the case of a bad landing, the landing gear pivots backwards and the part (40) collides with a reinforcement wall placed on the tank. The part (40) then pivots about its axis and releases the pins (38) from their housing. Perforation of the tank is thus prevented.