Abstract: An aircraft canopy fracturing system includes a canopy having fore and aft portions and a region that is severable from the canopy to provide an opening therethrough for the egress of aircraft occupants. The severable region has a shape that inhibits passage of the severable region through the opening created in the canopy once the severable region is freed from the canopy and is displaced aftward relative to the canopy. The canopy fracturing system also may include one or more mechanisms that will impart an aftward impulse to the severable region of the canopy once it has been severed and freed from the remainder of the canopy.

Abstract: An ejected pilot's seat deploys a drogue chute shortly upon ejection so as to slow the pilot's seat. A strain gauge is connected in line with a drogue chute to sense the load thereon. The load corresponds to speeds at which the ejected seat travels. As the ejected seat slows, the first possible safe speed for main parachute deployment is detected and a sequence controller causes rotation of a rotary solenoid shaft. The shaft displaces a mechanical stop for a parachute deployment timer. The main parachute is deployed shortly upon actuation of the parachute deployment timer. The result is main parachute deployment as soon as the ejected seat has reached a safe deployment speed, as opposed to after a longer fixed interval of time. This maximizes the altitude of descent for an ejected pilot, thereby increasing his safety factor for descent.

Abstract: An aircraft canopy breaking device, having means for penetrating the canopy lazing material upon application of an applied force from the rising ejection seat to the penetrating means. The device further comprises prepositioning means for prepositioning the penetrating means at a fixed distance from the canopy glazing material, shielding the penetrating means from inadvertently contacting the canopy glazing material, other material or personnel, and compressing whereby upon application of a force the penetrating means contacts the canopy glazing material causing crack propagation in the canopy glazing material.

Abstract: An improved aircraft cockpit canopy for allowing thru-the-canopy ejection of an ejection seat is disclosed. The canopy includes windshield and side sections of transparency panels tough enough to withstand high energy bird strikes and a portion of an overhead section of the canopy made of a frangible transparency panel that will break into small fragments if struck by an ejecting ejection seat. The frangible transparency panel is made thinner than the tougher transparency panel. The frangible transparency panel is held in place by either an elastomeric sealing gasket or by a metal bracket with an elastomeric sealing layer. Both the elastomeric sealing gasket and the metal bracket can be made to bend or break to release the frangible transparency panel when struck by an ejecting ejection seat. The elastomeric sealing gasket and the metal bracket can also absorb the dynamic oscillations of a bird strike elsewhere on the canopy.

Abstract: An aircraft canopy ejection system includes a releasable coupling 22 in the load path between an opening/closing jack 19 and the canopy. The coupling 22 is released immediately before emergency jettison of the canopy.

Abstract: An assembly for hinging a canopy to a fuselage includes a hinge with a floating hinge axis which accommodates differential thermal expansion of the canopy and the fuselage.

Abstract: A powered canopy breaker attached to an ejection seat, that fractures a canopy when the seat is ejected. The breaker has a piston that is operatively connected to an explosive cartridge. When the seat is ejected, the piston engages the canopy, pushing the piston a predetermined distance until the cartridge is detonated. The detonated cartridge ignites a detonating cord that fractures the canopy.

Abstract: A powered canopy breaker attached to an ejection seat, that fractures a canopy when the seat is ejected. The breaker has a piston that is operatively connected to an explosive cartridge. When the seat is ejected, the piston engages the canopy, pushing the piston a predetermined distance until the cartridge is detonated. The detonated cartridge thrusts the piston back, fracturing the canopy.

Abstract: An ejector seat device for aircraft includes a support structure which is adapted to be mounted in an aircraft and which can be ejected in an emergency, a seat connected to the support structure, a harness system which is capable of keeping a person in the seat and which comprises a recall device to immobilize the person in a suitable position at the moment of ejection, at least one pyrotechnical catapult capable of ejecting the support structure and the seat, together with a person sitting on the seat, out of the aircraft, a device for at least weakening the aircraft canopy by shock wave, a control handle, and an initiator connector to the handle for transforming a pull on the handle into a pyrotechnical signal. The pyrotechnical signal from the handle is transmitted in the form of a shock wave to the harness recall device and to the catapult.

Abstract: An emergency remover device for ejecting an aircraft canopy preliminary to in-flight ejection of personnel from the aircraft, which device is a ballistic gas actuated telescoping multi-cylinder assembly that is normally keyed in retracted relation and comprises an inner cylinder, an intermediate cylinder, and an outer cylinder, with the assembly arranged for upright incorporation in the usual aircraft canopy actuating extensible and retractable strut, in which assembly the outer cylinder is fixed against movement relative to the aircraft on emergency actuation of the device, and the inner and intermediate cylinders act under ballistic gas pressure released within the device to effect the imposition on the canopy of the needed unbalanced force in a more or less uniform manner to effect the application to the canopy of maximized release momentum prior to the remover device to effect the application to the canopy of maximized release momentum prior to the remover device reaching its extending length, and to prov

Abstract: A parachute system for an airman ejected from an aircraft in an ejection seat includes at least one drouge parachute housed within a rigid hollow container. In conventional manner, the drogue parachute is connected by lines with releasable attachments on the seat, one of the lines being further connected with the main parachute so that the latter will be deployed after release of said attachments. The container is formed as a projectile mounted in a gun mounted on the ejection seat. The container has, at its end facing away from the direction in which it is fired, a closure connected with the lines and with the drogue parachute. When the container and closure are fired from the gun, and the closure is arrested abruptly by the lines, the container continues in its trajectory whilst the drogue parachute is drawn from the container and deployed by the lines.

Abstract: An aircraft cockpit canopy has a separable portion which is capable of being separated from a remaining portion of the canopy at a clearly defined break line by means of detonating cord, to facilitate ejection of a crew member along a predetermined path through the canopy, the separable portion being of such a size that hinges are provided to constrain it to swing in a predetermined path to clear the ejection path, the hinges being attached to the canopy and bridging the break line so that prior to separation, they remain unused but subsequently they are effective to pivotally constrain the separated portion. Conveniently, the separable portion may be in two or three large parts.

Abstract: An arrangement of devices for removing wall parts of a cockpit canopy in emergencies, with fuses being mounted in such a manner to the canopy glass for the purpose of the rapid removal of glass parts from the ejection path of a person to be rescued. Glass halves are formed by severing specific glass sections while maintaining a bending line along a specific bending path in the area of the longitudinal glass edges.

Abstract: When the pilot seated at the front of a high-performance two-seater aircraft equipped with a forwardly-plunging transparent canopy transparency, wants to bail out on his ejection seat, he triggers a two-period pyrotechnical sequence; first, he cuts out a well-bounded fragment or dome located towards the rear of the canopy and right above his head on the seat ejection axis; and only then, upon a second period, he renders frangible the forwardly-plunging front portion of the canopy located above his knees which, at this instant, reach its level and smash it to pieces.

Abstract: Device for maintaining a detonating cord against a transparent aircraft canopy member which is of the type comprising a closed sheath within which is placed the cord. The device also has an outer envelope, whereof a first part, surrounded by the closed sheath, is maintained against the transparent member and whereof a second part is fixed to a structural component of the aircraft cockpit.

Abstract: Panel breaking apparatus for breaking a panel such as a military aircraft cockpit canopy ahead of an ejector seat and wherein at least one conductor formed of aluminum sheathed in palladium is embedded in the panel. The conductor is part of an electrical circuit which comprises initiation switch means, a power reservoir and a source of high electrical energy and is operative upon closure of the switch to explode and break the panel.

Abstract: The window is constituted by two parallel walls and a central space, a detonating fuse being inserted between the walls and mounted in such a manner as to produce anisotropic detonating action. As a result of detonation, breakage and ejection of the outer wall and embrittlement of the inner wall take place simultaneously along the cutting outline.

Abstract: This invention relates to apparatus for explosively severing non-metallic material such as aircraft canopy transparencies, egress panels and other structural members. To provide a more effective use of a given amount of explosive, a detonating cord is encapsulated within the material to be severed. This encapsulation protects the cord and maximizes the severance effect of the detonation. The cord may be encapsulated at positions wherein augmented shock waves are used to accomplish fracture along a line away from the detonating cord while leaving the explosion products restricted in the remaining cord cavity.

Abstract: A Panel Breaking Apparatus comprising at least one fusible conductor having at least one region of increased fusibility and embedded in intimate contact with the panel material and connected to a source of electrical power operable to produce a high-energy pulse of current sufficient to fuse the conductor and thus to break the panel.