Abstract: A pyrotechnic initiator having an internal sleeve that facilitates the loading and durable retention of a pyrotechnic charge in place on the header surface within the initiator. The sleeve beneficially retains the charge either in conjunction with the upper interior surface of the charge can, or through the use of a monolithic charge and a narrowed top end of the sleeve.

Abstract: The present invention relates to priming device for the explosive charge of a sub-munition scattered by a carrier, of the type incorporating a firing pin onto which a deployable drag ribbon has been attached, a primer able to be driven by a motor organ and a detonating primer to ignite the explosive charge. This device also comprises self-destruction means for the sub-munition operating after a predetermined delay, such means being activated by the extraction of a self-destruction lock. It is characterized in that the self-destruction lock is integral with the drag ribbon and is therefore extracted by the ribbon during its deployment.

Abstract: An ammunition article includes a molded plastic cartridge casing body having a first end and a second end, and a projectile attached to the first end of the cartridge casing body. The cartridge casing body is molded around at least a portion of the projectile. A molded plastic base for an ammunition article, a molded plastic blank cartridge, and a molded plastic cartridge casing body having a pronged web are also disclosed.

Abstract: Apparatus and methods for performing satellite proximity operations such as inspection, recovery and life extension of a target satellite through operation of a “Satellite Inspection Recovery and Extension” (“SIRE”) spacecraft which can be operated in the following modes (teleoperated, automatic, and autonomous). The SIRE concept further consists of those methods and techniques used to perform certain (on-orbit) operations including, but not limited to, the inspection, servicing, recovery, and lifetime extension of satellites, spacecraft, space systems, space platforms, and other vehicles and objects in space, collectively defined as “target satellites”. The three basic types of SIRE proximity missions are defined as “Lifetime Extension”, “Recovery”, and “Utility”. A remote cockpit system is provided to permit human control of the SIRE spacecraft during proximity operations.

Abstract: A trigger assembly is adapted to replace the trigger and trigger safety assembly supplied in pistols for enhancing safety features. The invention is formed by a sideways insertable locking pin, a newly designed trigger safety member and a helicoidal spring. The user may lock the pistol trigger assembly by pushing the locking pin to one safe position, and unlock it with an opposite movement.

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 safety device for a breechblock of a firearm suitable for limiting accidental sliding of a breechblock (14) following knocks to the firearm, comprises a locking lever (15) of the breechblock (14), pivoted to the structure of the firearm in an axis (11) and an elastic return element (18) of the lever (15), suitable for keeping it is rest position in conditions of normal use of the firearm, the locking lever (15) being equipped with an engagement element (19) for intervention in a seat (20) of the breechblock (14) and with a center of gravity (G) which is offset with respect to the axis of rotation (11) of the lever (15), suitable for causing its inertial rotation in a middle plane of line (21).

Abstract: A proximity fuze for use in a tube launched projectile carrying a payload, comprising an oscillator for generating a radio frequency signal which has a varying frequency, a single antenna for transmitting the radio frequency signal and for receiving an echo of the radio frequency signal, a first signal processor for generating a range signal corresponding to the time delay between the transmission of the radio frequency signal and the receipt of the echo signal, second signal processor for comparing the range signal with a reference signal and depending on the result of the comparison generating an activation signal for activating the payload, wherein a directional coupler is used for coupling the radio frequency signal from the oscillator to the antenna and to the signal processor and for coupling the echo signal from the antenna to the signal processor, and wherein the second signal processor comprises a threshold detector, a peak detector and a comparator, the threshold detector being for allowing the comp

Abstract: Articulation device for an aircraft door panel and an aircraft door integrating such a device. An aircraft door panel is articulated on the jamb by a device (20) that defines an approximately elliptical opening and closing trajectory, in which the major axis is approximately perpendicular to the panel. The device (20) comprises in particular a main arm (30), a secondary arm (32) articulated at the end of the main arm and a control lever (34) connecting the secondary arm (32) to the jamb, by articulation axes (A4, A5) close to the articulation axes of the main arm (30) on the jamb and the secondary arm (32) on the main arm. This arrangement makes it possible to fit a more voluminous emergency exit chute into the door panel.

Abstract: A gas generator comprises a tubular housing of a pressure-resistant material and a propellant strand which is incorporated in the housing and provided with an envelope. At least one channel is provided between the envelope and the propellant strand so as to extend in an axial direction. The propellant strand has a substantially circular cross-section and the envelope has a polygonal cross-section.

Abstract: A vertical lift aircraft comprises a cabin mounted to an enclosed rotary wing which provides vertical lift for the aircraft. The rotary wing includes an annular housing and a main rotor blade rotatable within a space circumscribed by the housing. The main rotor blade is rotatable about a rotation axis that is tilted forwardly from a vertical axis of the aircraft. A horizontal directional control for the aircraft includes a plurality of control slides disposed at spaced locations along the housing and being movable inwardly and outwardly in a radial direction between a neutral position in which the control slides are retracted from the downdraft area and an operational position in which the control slides are extended into the downdraft area. Selective deployment of one or more control slides in the operational position effects horizontal directional turning of the aircraft in the direction of the one or more deployed control slides.

Abstract: An ornithopter has a power assembly which provides flapping of the wings by a reciprocating shaft and bell cranks. The wings are mounted on a hub which rotates in response to the flapping of the wings. The sinusoidal movement of the wings provides lift for flight.

Abstract: Systems in which anti-icing fluids may be automatically mixed with water, and by which de-icing fluids may be heated and mixed with water, to provide variable temperatures and ratios of de-icing fluid-to-water to local aircraft de-icing fluid application devices in an instantaneous manner. Also contemplated herein are systems that additionally are configured for applying decontamination fluid and/or corrosion control fluid to military aircraft or other vehicles.

Abstract: A fuzing system for non-spinning or substantially non-spinning weapons is implemented by means of wide angle optics providing at least forward-hemisphere coverage, an array of infrared detectors and a microprocessor for image and data processing, aim-point selection, directional-warhead aiming and skewed-cone fuzing. The skewed-cone fuzing has a generatrix which is the vector sum of missile velocity, warhead velocity and the negative of target velocity.

Abstract: This invention concerns a supplementary safety device in the form of a false cartridge to be inserted into the chamber of a light firearm barrel, including a radially expandable portion controlled by a lock operated by a specific key for locking/unlocking it in the barrel in which it is housed, so it may be removed only voluntarily.

Abstract: The present invention features devices for mounting accessories to a weapon and more particularly mounting devices that allow one or more accessories to be secured to the weapon, such as a firearm and crossbow, at the same time using the same mounting device. In more particular embodiments, one of a scent generating device, a weapon hanger, a recording device and/or an illumination device, such as a flashlight is secured to the device and thus to the weapon. The present invention also features methods related thereto including methods for masking the scent of a hunter and hunting.

Abstract: A method comprises: launching observation means configured to observe upper air environment immediately before launching an airship to acquire ambient air data on the actual conditions of the upper ambient air including altitude, pressure, wind direction, wind speed and temperature; determining an ascension profile for the airship by simulation using the ambient air data on the actual conditions of the ambient air; determining an initial quantity of Helium gas conforming to the actual conditions of the ambient air; and adjusting the quantity of Helium gas in the Helium room to the initial quantity of Helium gas to set an initial buoyancy. The method sets hull parameters for the hull of the airship to provide an ascension profile conforming to the actual conditions of the ambient air.

Abstract: A non-lethal projectile or a projectile for delivery of a substance (optional) has a tubular body casing (1) which surrounds a compartment (2) for containment of the substance. The compartment (2) coaxially supports a hollow tube (5) projecting forward within an ogival nose cap (8). An inflatable membrane (7) is located within the nose cap (8). On target impact the nose is displaced and permits a small amount of substance from compartment (2) to bleed through opening (6) allowing piston (4) to move forward uncovering ports (16). This action allows pressure gas to pass through the ports (16) and ducts to inflate the membrane (7). The piston is also free to move forward to discharge the substance through needle (5). The bag (7) thus expands rapidly and prevents excess penetration whilst spreading the impact energy over a wide area. The construction avoids the need for a charge to be contained within the projectile itself.

Abstract: The aircraft with multi-level cabins functioning as a cargo cabin or passenger cabin comprises a first cabin provided with a cargo hatchway which is opened and closed by a cargo door on a fuselage, the cargo door facing towards the cargo cabin; a second cabin which lacks the cargo hatchway, the second cabin being positioned directly above or under the first cabin; and an elevator to convey a cargo item, moved into the first cabin through the cargo hatchway, to the second cabin, and to convey back the conveyed cargo item from the second cabin to the first cabin, thereby the cargo item is moved between the exterior of the aircraft and the second cabin.

Abstract: A seating unit in a combat vehicle that is protected against mines is provided. The vehicle has a hull that is disposed on the chassis and that has at least one hatch in its roof plate that can be closed off by a hatch cover. The seating unit, which is disposed in the hull in the region below the hatch, is provided with a base on which is disposed a seat and that is suspended on the front or side wall and/or the roof plate of the hull via a tubular construction in such a way that the base is not at less than a prescribed spacing relative to the base of the hull. The tubular construction can comprise two guide tubes that extend parallel to one another and upwardly at an angle. The upper ends of the tubes are connected with the front wall, and the lower ends are suspended on the roof plate via connecting tubes. The base is displaceably disposed on the guide tubes via holding devices.