| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | Emergency opening cylinder of a passenger door for an airplane, a door system and a method of modifying a door system | US10319808 | 2002-12-16 | US20030132347A1 | 2003-07-17 | Stefan Blum; Thomas Nickl; Wolfgang Spellmeier |
| An emergency opening cylinder of a passenger door of an airplane is provided. An existing emergency opening cylinder is adapted at the lowest expenditures and with an insignificant increase in weight with respect to its operating characteristic to the load situation of an emergency opening of the door against the force of gravity. A ventilation bore of the emergency opening cylinder leads into a collecting chamber which has an outlet valve controllable by a control. | ||||||
| 82 | Collapsible panel and method for controlled collapsing thereof | US09854483 | 2001-05-15 | US20020017414A1 | 2002-02-14 | Luciana Collinucci |
| A collapsible panel forming a separation structure between a generally closed inner environment and an outer environment, for instance consisting of a motorvehicle stratified window, incorporating within its mass at least one explosive charge to which an igniter/detonator device is operatively associated to produce detonation of the explosive charge so as to shiver the panel in a controlled way substantially within the plane thereof. | ||||||
| 83 | Plane saddle for a safety airplane | US374085 | 1995-01-18 | US5568903A | 1996-10-29 | Jesus S. Pena; Julia M. Williams; Joe L. Williams |
| A safety airplane comprising a carrier portion and a saddle portion. An assembly is for retaining the saddle portion on the carrier portion. A structure is for releasing the saddle portion from the carrier portion, when there is a problem during flight. Paraphernalia is for gently lowering the saddle portion to the ground. | ||||||
| 84 | Canopy breaking device | US35780 | 1993-03-17 | US5301904A | 1994-04-12 | Frederick C. Guill |
| An aircraft canopy breaking device, having means for penetrating the canopylazing 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. | ||||||
| 85 | Aircraft windshield system with frangible panel for aircrew emergency escape | US43705 | 1993-04-07 | US5289996A | 1994-03-01 | Ralph J. Speelman, III |
| 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. The improved aircraft canopy can also be made by direct forming, where the area of the canopy through which an ejection seat will exit is made more frangible by modifying the material properties of the transparency at that location, by making the transparency thinner over that area, by scoring the transparency over that area or by a combination of those and other methods. | ||||||
| 86 | Aircraft with releasable wings | US186151 | 1988-04-26 | US5009374A | 1991-04-23 | Carl Manfredi; Antonina Manfredi; Dario P. Manfredi; Savia Giarraffa |
| This invention relates to aircraft and specifically to devices for disconnecting the winds in a rapid manner. The frame of the wings is atached to the frame of the fuselage with exploding bolts. The skin of the wings is secured to the skin of the fuselage with rivets that also explode or a burnable tape is placed under the skin to sever the skin. A control arrangement is provided that simultaneously ignites the exploding bolts and the rivets or the tape to disconnect the wings from the fuselage. | ||||||
| 87 | Pyrotechnic system for providing an emergency exit in an aircraft | US372894 | 1989-06-28 | US4978089A | 1990-12-18 | Bruno Alquier; Olivier Belou; Paul Devienne; Thierry Martin |
| A system for providing an emergency exit in a wall of an aircraft includes a pyrotechnic device disposed against the wall, and capable of cutting a desired opening in the wall, an igniter for the pyrotechnic device, a controller for the igniter, and a manometric safety device which receives the pressures inside and outside the aircraft and inhibits the action of the igniter when the difference between the pressures inside and outside the aircraft is greater than a predetermined value. | ||||||
| 88 | Comprehensive airplane safety system | US29227 | 1987-03-23 | US4726550A | 1988-02-23 | Bao C. Chen; Shih C. Chen |
| An airplane with an enlarged safety door in the lower middle part of the fuselage which can be opened during mid-flight emergencies so as to let emergency exit stairs be hydraulically lowered down therefrom. The stairs have a hydraulically operated slideway on the lower end thereof. Chair assemblies which are slidable on rails and which are normally retained by a flip-up board. The chair assemblies can be moved either manually or by means of a motor driven draw cord. A user propelled water safety device comprising an inflatable chest support, two handlebars two inflatable paddlewheels and two floatation devices. A bouyant, collapsible carry-all which can be used to carry survival and safety items upon exit of the plane and which has holes in the bottom thereof for easy draining. An air-flow system comprising an air exhaust shield, a plurality of fans, air vents distributed at even intervals along the ceiling of the plane. An air supply system comprising pipes that run between the walls of the airplane to a plurality of outlets on the end sections of the pipe. | ||||||
| 89 | Airplane safety body passenger compartment | US860903 | 1986-05-08 | US4699336A | 1987-10-13 | Peter Diamond |
| An airplane safely body passenger compartment is provided which contains a mechanism for ejecting the passenger compartment from an elongated receptacle in the fuselage when an airplane is in danger of crashing so that parachutes will gently float the passenger compartment to the earth. | ||||||
| 90 | Arrangement of devices to sever and remove canopy wall sections from aircraft cockpits | US462790 | 1983-02-01 | US4570880A | 1986-02-18 | Hartmut Gehse |
| 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. | ||||||
| 91 | Panel breaking apparatus | US406372 | 1982-08-09 | US4405104A | 1983-09-20 | David H. Charman; Clara Turner; Henry W. Turner |
| 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. | ||||||
| 92 | Plate-glass fitted with an explosion-cutting device | US107605 | 1979-12-27 | US4333381A | 1982-06-08 | Paul H. Boeglin; Claude R. Chigot |
| 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. | ||||||
| 93 | Panel breaking systems | US945106 | 1978-09-25 | US4275858A | 1981-06-30 | Colin B. Bolton; Harry D. Rylands; Clara Turner; Henry W. Turner |
| 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. | ||||||
| 94 | Method and means for flash suppression | US51996074 | 1974-11-01 | US3919939A | 1975-11-18 | MURRAY JAMES L; SIRES LAWRENCE M |
| A method and apparatus is provided for suppressing light flashes from a linear-shaped charge, for example, on a cargo dispenser. Undesirable light flashes may be suppressed by either manufacturing the linear shaped charge container from silver or placing a container of chemical suppressant along the external skin of the cargo section at the cutting line of the linear shaped charge or both.
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| 95 | Aircraft emergency egress system | US44832474 | 1974-03-05 | US3885761A | 1975-05-27 | PENDERGAST DANIEL O; ENGEL WILLIAM T; DORROUGH VERNON R |
| A system for enabling rapid escape from an aircraft under emergency conditions comprising an explosive closure cutting assembly, an explosive initiator assembly in immediate proximity to said explosive closure cutting assembly, a manually actuated firing handle and a remote control mechanical actuating linkage having one end operatively connected to the explosive initiator assembly and the other end connected to the manually actuated firing handle.
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| 96 | Aircraft canopy ejection | US48349974 | 1974-06-27 | US3880387A | 1975-04-29 | MARTIN JR EDWARD F |
| An aircraft canopy-breakout arrangement including a rigid member hinged to the canopy and positioned adjacent to and in the interior of the canopy at a location above the ejection seat. Fragmentation, destruction and removal of a selected portion of the canopy directly in the region of the rigid member is brought about by the ejection seat coming into sudden contact with the rigid member and pushing it up through the canopy as a result of a propulsive force. This ensures that the selected area cleared by the rigid member and the ejection seat will not have fragments remaining in the path of the pilot after the ejection has broken through the remaining major portion of canopy that must be removed to produce the opening through which the crew-member in his ejection seat may pass without danger of injury from remaining fragments of canopy.
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| 97 | Aircrew escape systems | US3782284D | 1972-02-18 | US3782284A | 1974-01-01 | GIBB R; GALTON G; SHEPHERD D; SMITH D; WICKENDEN G |
| A detonating cord is provided, for causing fracture and break-up of an aircraft cockpit canopy for the purpose of emergency escape, consisting of an explosive core contained in a lead casing and surrounded by a plastic sheath, the cord being of substantially semi-circular or D-shaped cross-section. The semicircular surface, but not the flat face, of the casing has several layers of lead tape applied to it within the plastic sheath which lead tape acts as blast-containing and reflecting material to direct the blast effect of the detonation preferentially through the flat-face.
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| 98 | Aircraft canopy separation system | US3721407D | 1970-02-12 | US3721407A | 1973-03-20 | CLARKE J |
| An aircraft canopy separation system including a frangible member that can comprise tempered glass or a glass ceramic that is connected to the aircraft canopy at a location that will permit the opening or removal of the canopy after the frangible member has disintegrated as a result of being struck by a sharp instrument. The frangible member comprises a rod that is located within a hinge that is attached to the canopy. A sharp-pointed instrument is also provided for striking the frangible member that may be located on an aircraft ejection seat at a point where it will strike the frangible member as the ejection seat is being ejected from the cockpit of the aircraft.
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| 99 | Severance of polycarbonate material canopy transparency | US3670998D | 1970-07-10 | US3670998A | 1972-06-20 | CHARLEVILLE JOSEPH L; TIENNE MART E DE; LAMMERT CHARLES W |
| Method for permitting the emergency bail-out from an aircraft having a frangible polycarbonate material canopy transparency by a person in an ejection seat. A flexible linear shaped charge is used to sever the polycarbonate canopy transparency in lieu of jettisoning the canopy. The charge, after ignition and explosion, severs the canopy transparency around the forward arch, back along the canopy side frame, and up the canopy to the rear of the seat to a point which leaves an unsevered section, of preselected length, of the canopy transparency. This unsevered section serves as a hinge and as a retaining means, and as the seat is ejected from the aircraft the severed section of the canopy transparency moves backwardly away from the seat, thereby precluding any contact between the canopy transparency and the person in the ejection seat.
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| 100 | Safety mechanism for aircraft canopies | US56038366 | 1966-06-21 | US3382612A | 1968-05-14 | LEONARD SCHROEDTER |
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