| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | LIGHT MULTI-PURPOSE AIRCRAFT | US12450712 | 2007-07-11 | US20100327112A1 | 2010-12-30 | Oleg Fedorovich Demchenko; Nikolai Nikolaevich Dolzhenkov; Konstantin Fedorovich Popovich; Vladimir Petrovich Shkolin; Vitaly Jurievich Naryshkin; Valery Grigorievich Kodola; Georgy Aleksandrovich Fedotov |
| A light multi-purpose aircraft comprises a fuselage 1; a wing 2; a fin assembly 3; a landing gear 4; main and auxiliary power plants 5; a crew protection system; an integrated complex for controlling a general-purpose aircraft equipment which is engaged through a multiplexer channel with a set of on-board digital computers, electronic control systems of port and starboard engines, a recording and monitoring system, a guidance and landing equipment, a complex control system and is engaged through code communication lines with a fuel control and monitoring system, a voice message equipment, a complex electron display system, characterized in that the crew protection system is made in the form of a multilayer screen of auxiliary and main equipment configured in order of increasing its significance farther and farther away from the shell and load-bearing elements of the fuselage 1; the greatest component density is ensured with due regard for the most likely zones and aspect angles of injury: ˜30° with respect to the surface of approaching the destruction means at the front—from below and on the side—from below of the fuselage forepart, and the integrated complex for controlling a general-purpose aircraft equipment is provided with a crew warning system 12 regarding the fall outside limiting values of destruction aspect angles, the system 12 being connected to the complex electron display system and the voice message equipment. | ||||||
| 122 | Weapon Interface System and Delivery Platform Employing the Same | US11925471 | 2007-10-26 | US20100326264A1 | 2010-12-30 | Steven D. Roemerman; John P. Volpi; Joseph Edward Tepera |
| A weapon interface system, and methods of operating the same. The weapon interface system is coupled to an electrical interconnection system of a delivery platform and a weapon system coupled to a rack system. The weapon interface system includes a translation interface configured to provide an interface between the electrical interconnection system and an inductive power and data circuit. The weapon interface system also includes a weapon coupler, coupled to the translation interface, configured to provide an inductive coupling to the weapon system to provide mission information thereto. | ||||||
| 123 | Chaff Pod Dispenser | US12267245 | 2008-11-07 | US20100326262A1 | 2010-12-30 | Benjamin J. Galanti; David J. Broadhead; Michael A. Huff |
| According to one embodiment, a chaff pod includes at least two dispensers disposed within a chaff pod housing. Each of the dispensers has a surface defining an opening through which a number of countermeasures may be dispensed. The dispensers are configured to be coupled to the aircraft. The first dispenser directs countermeasures in a first direction, and the second dispenser directs countermeasures in a second direction. The difference between the first direction and the second direction form a relative angle. | ||||||
| 124 | Ducted fan VTOL vehicles | US11411243 | 2006-04-26 | US07857253B2 | 2010-12-28 | Raphael Yoeli |
| A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, a pilot's compartment formed in the fuselage between the lift-producing propellers and substantially aligned with one side of the fuselage, a payload bay formed in the fuselage between the lift-producing propellers and opposite the pilot's compartment, and two pusher fans located at the rear of the vehicle. Many variations are described enabling the vehicle to be used not only as a VTOL vehicle, but also as a multi-function utility vehicle for performing many diverse functions including hovercraft and ATV functions. Also described is an Unmanned version of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles. | ||||||
| 125 | Ballistic fire protection system | US11759798 | 2007-06-07 | US07841421B2 | 2010-11-30 | Richard L. Kulesha |
| A fire protection device has a panel having a plurality of channels formed there through. A plurality of containers is used for holding a fire suppression material. Each container is placed in one of the plurality of channels. An attachment device is used for removably coupling the fire protection device to a structure to be protected. | ||||||
| 126 | DECOY PROTECTION SYSTEM FOR AIRCRAFT AND METHOD OF PROTECTION | US11946210 | 2007-11-28 | US20100288877A1 | 2010-11-18 | Joseph L. Strabala |
| The current invention is inclusive of a decoy protection system and method of protecting jet aircraft from shoulder fired missiles comprising while such aircraft is in a flight envelope where it is susceptible to being hit by a such a missile, by employing a decoy means towed by aircraft at a distance away from the aircraft whereby the decoy means is located sufficiently remote away from any part of said aircraft that a missile strike on the decoy mean will not normally damage the aircraft, supplying said decoy means with jet fuel from said aircraft and burning said jet fuel in the decoy means to create a high intensity IR signature in the decoy means sufficient to divert shoulder fired missiles from said aircraft to said decoy means.Burning jet fuel in such a decoy means, such as a pulse jet engine configuration for the decoy, creates IR and UV signatures at the decoy means that are nearly identical to those of the jet engines of a aircraft protected by the system and method; further it creates an exhaust plume from the decoy means that is very similar in spectra to the exhaust plumes of the aircraft's engines to fool discriminators used in some of such missiles. | ||||||
| 127 | Ducted fan VTOL vehicles | US11794906 | 2006-01-10 | US07806362B2 | 2010-10-05 | Raphael Yoeli |
| A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, and a body formed in the fuselage between the lift-producing propellers. Many variations are described enabling deflection and affection of flow streams and reduction of drag and momentum drag which improve speed and forward flight of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles. | ||||||
| 128 | Apparatus and method for air-to-air arming of aerial vehicles | US10568242 | 2004-02-18 | US07793888B2 | 2010-09-14 | Nir Padan |
| A transfer of ordnance units from a first aerial vehicle to a second aerial vehicle performed while both vehicles are airborne. The first aircraft is used as an ordnance storage, ordnance delivery and ordnance supplier platform. The second aircraft has the functionality and capability of delivering the received ordnance to designated targets. The first aircraft includes an ordnance storage apparatus, an ordnance transfer assembly, a computer-based highly accurate ordnance transfer control apparatus, and an ordnance transfer apparatus operating crew. The ordnance transfer assembly establishes temporarily a transfer link between the aircraft and utilizes an ordnance conveyor mechanism for the delivery of the ordnance units. The second aircraft includes a multi-use multi-purpose pylon that receives the transferred ordnance in the proper manner. The aircrafts can be uninhabited. | ||||||
| 129 | AIRCRAFT WITH MULTI-PURPOSE INTEGRATED ELECTRONIC COMPLEX | US12452561 | 2007-07-11 | US20100133388A1 | 2010-06-03 | Oleg Fedorovich Demchenko; Nikolai Nikolaevich Dolzhenkov; Konstantin Fedorovich Popovich; Vladimir Petrovich Shkolin; Arkady Iosifovich Gurtovoi; Valery Grigorievich Kodola; Vyacheslav Georgievich Kalugin; Kirill Veniaminovich Obrosov |
| An aircraft (1) at enhanced maneuvering properties comprising a fuselage, a wing, a fin assembly, a landing gear, a power plant, a multi-purpose integrated electronic complex (3), incorporating an information exchange system, a set of on-board digital computers (19) for controlling flight and training and combat operations, an external storage and an information input system, a radio inertial navigation and landing system, a complex aircraft control system, an armament control system, a complex system for electronic display, control and sighting, an emergency warning board, a general-purpose aircraft equipment control system, an on-board objective monitoring system, a speech information control system, an electric power supply system, external and internal lighting facilities, a complex emergency escape system, an electronic power plant control system, characterized in that an optoelectronic vision-sight system (5) comprises an automatic caging system (31) that fixes orientation of visual fields of a laser radar system (24), a narrow-field thermal vision system (25), a wide-field thermal vision system (26), a TV system (27) when a sight line transits to the upper hemisphere and decages thereof during transition to the lower hemisphere; the optoelectronic vision-sight system (5), receive-radiating units of an on-board radar (4) and a periscopic system (30) for bringing visual fields of the optoelectronic system to the upper hemisphere being mounted in a common fastening device. | ||||||
| 130 | LIGHT MULTIPURPOSE AIRCRAFT | US12448511 | 2006-12-25 | US20100012767A1 | 2010-01-21 | Oleg Fedorovich Demchenko; Nikolai Nikolaevich Dolzhenkov; Konstantin Fedorovich Popovich; Vladimir Petrovich Shkolin; Arkady Iosifovich Gurtovoi; Vladimir Grigorievich Kuznetsov; Vyacheslav Nikolaevich Nikitin; Vyacheslav Mikhailovich Ilin; Viktor Lavrentievich Bozhanov; Valery Grigorievich Kodola |
| A light multi-purpose aircraft comprises a fuselage (1); a wing (2); a fin assembly (3); a landing gear (4); a main power plant (5); an auxiliary power plant (7); pylons (10); outboard suspension objects (9) arranged on the undersurface and at the ends of the wing (2); at least one outboard suspension object (9) being arranged on the undersurface of the wing (2) and at least one outboard suspension object (9) being arranged at each end of the wing (2); a gun mount (8) or a guidance and tracking mount arranged in the lower part of the fuselage (1); a controlling integrated complex of airborne electronic equipment (17) with an electric power supply system (16) and an armament control complex (19) incorporating an on-board electronic guidance and tracking system (20); a defense system (21); a multi-purpose control panel (22); a group interaction system (23); an armament control system (24) which are related to each other and to the controlling integrated complex of airborne electronic equipment (17) through a multiplexer information exchange channel; the armament control system (24) comprising a matching and logic unit (25); an emergency unloading unit (26); at least one data distribution and conversion unit (27); executive units (28); units for switching outboard suspension objects (29); a unit for switching a gun mount or guidance and tracking mount (30); components of the armament control system (24) being linked by a local channel of information exchange, the number of the executive units (28) and the units for switching outboard suspension objects (29) being consistent with the number of outboard suspension objects (9). | ||||||
| 131 | Stealth attack fighter bomber | US11732250 | 2007-04-03 | US07581699B1 | 2009-09-01 | Samuel Barran Tafoya |
| A fighter bomber aircraft having a rhomboid airframe with a dihedral bottom surface and a top surface designed as an airfoil. The rhomboid cross-sectional configuration gives it increased lift, stealth characteristics, and enhanced load-bearing capacity. It also has two central tubes stacked on top of one another and extending front-to-rear, with the upper tube extending part way through the airframe and preferably housing a pilot, guns forward from and in line with the pilot, a gear/equipment compartment behind the pilot, and fuel tanks positioned behind the gear/equipment compartment. The lower tube extends substantially throughout the airframe and preferably houses the air-intake for the engine, radar, nose gear, bombs, and rear engine. The aircraft has no conventional wing structure and its dihedral bottom surface allows it to make wheels-up emergency landings on water and hard runway surfaces. In addition, rockets can be optionally mounted on the top of the lift area. | ||||||
| 132 | TURRET ASSEMBLIES FOR SMALL AERIAL PLATFORMS, INCLUDING UNMANNED AIRCRAFT, AND ASSOCIATED METHODS | US11932545 | 2007-10-31 | US20090216394A1 | 2009-08-27 | Stephen B. Heppe; Andreas H. von Flotow; Aram Soghikian |
| Turret assemblies for small aerial platforms, including unmanned aircraft, and associated methods are disclosed herein. In one embodiment, an aircraft system can include a turret assembly having a payload with a line of sight to a target and a gimbal system carrying the payload. The gimbal system can include (a) a first support coupled to a first actuator to rotate about a first axis, and (b) a second support carried by the first support and coupled to a second actuator to rotate about a second axis generally transverse to the first axis. The payload can be carried by the second support. A housing at least partially surrounds the payload and the gimbal system. The turret assembly can also include a controller configured to direct movement of at least one of the first actuator and the second actuator such that the line of sight is pointed away from a point of impact before the turret assembly contacts the ground or another external structure during landing or capture operations. | ||||||
| 133 | Energy absorbing impact band and method | US11790144 | 2007-04-24 | US20080265095A1 | 2008-10-30 | Timothy J. Lee; Jason L. Firko; Jonathan W. Gabrys |
| An energy absorbing apparatus and system for leading edge structures includes an impact member, such as a “bird-band”, of a plastically deformable material of a predetermined configuration positioned with the structure in an area of the leading edge of the structure to absorb energy of an impact of a projectile with the leading edge of the structure, and to redistribute the energy of the impact to the structure, and can break up the projectile, and can increase the impact area. The structure can have one or more sheet members, such as a single sheet, or an inner face sheet and an outer face sheet with a core positioned between the inner face sheet and the outer face sheet. One or more impact members of the plastically deformable material can be positioned with one or more of the single sheet, the inner face sheet, the outer face sheet or the core. | ||||||
| 134 | Method and apparatus for reducing the infrared and radar signature of a vehicle | US10514753 | 2003-05-23 | US07396577B2 | 2008-07-08 | Bryan A. Riley; Robert A. Shepherd |
| The present invention provides a lightweight structure for simultaneously providing a reduced infrared and radar signature, while adding little or no weight to a vehicle. As such, the present invention allows for substantial improvements over prior systems. An example of the type of vehicle able to make use of the present invention is a military helicopter, but there is nothing within the spirit and scope of the present invention limiting it to any particular vehicle. The teachings of the present invention are useful with any vehicle for which a reduction in infrared emissions and microwave reflections is desired. | ||||||
| 135 | Systems and methods for evading heat seeking missles | US11199266 | 2005-08-09 | US07367531B2 | 2008-05-06 | Leonard M. Greene |
| A method and system in an airborne aircraft to evade a heat seeking missile includes the steps of detecting the launch or “lock on” of a heat seeking missile and reducing the radiation from the aircraft's engine by reducing the engine speed to idle. The method may also include the steps of shutting down and restarting an engine and taking countermeasures to distract the missile or distorting its tracking system. In addition, a method and system for automatically shutting down an engine and/or injecting cooling water into the engine's exhaust port are disclosed. | ||||||
| 136 | Onboard modular optronic system | US10582632 | 2004-12-09 | US20070152099A1 | 2007-07-05 | Dominique Moreau |
| The present invention relates to a modular optronics system onboard a carrier, such as a combat aircraft, a helicopter or a drone. The system as claimed in the invention comprises at least one optronics element having a target line that can be addressed in a given space, and comprising a mechanical structure designed to be the interface with the carrier and a target line orientation and stabilization mechanism. According to the invention, the mechanical structure comprises a module forming a section with three interfaces, including said interface with the carrier and two lateral interfaces that can receive a lateral module. The optronics elements and the target line orientation and stabilization mechanism are directly incorporated in the module forming a section. | ||||||
| 137 | Hanger assembly for aircraft | US10797681 | 2004-03-05 | US07100873B2 | 2006-09-05 | James Benjamin Moates |
| A hanger assembly for suspending an external store from an aircraft includes left and right side panels in hinged connection to a center panel, where the panels, in combination, form a band for substantially circumferentially surrounding the external store. The center panel includes an interface for engagement with an attachment pod on an aircraft, and the side panels are fastened in tension to each other diametrically opposite the interface. The length, thickness and material strength of the band are selected to minimize the bending moment, which is induced in the hanger assembly based on loading experienced during operational use, at a region of the band at which an interface is established with the aircraft. | ||||||
| 138 | METHOD FOR AERIAL REARMAMENT OF AIRCRAFT | US11052173 | 2005-01-31 | US20060145025A1 | 2006-07-06 | John Beyerle; Gary Illingworth |
| The invention provides a method for the aerial transfer of munitions from a rearming aircraft to the weapons pylon of the recipient combat aircraft. The invention also provides for the selection of munitions from a database of munitions and aircraft types in response to an Air Tasking Order. The invention allows a variety of combat aircraft to be adapted_to aerial rearmament. The invention also allows the release of precision guided munitions directly from a rearming aircraft so that orbiting combat aircraft can guide these munitions to the target by remote control. | ||||||
| 139 | Penetration- and fire-resistant fabric materials and structures | US11090645 | 2005-03-25 | US20060145009A1 | 2006-07-06 | Donald Shockey; David Erlich; Jeffrey Simons |
| A ballistic and/or fire barrier for protecting objects in an interior of a vehicle due to projectile penetration and/or fire includes one or more layers of high strength fabric positioned towards an outer shell of the vehicle. The high strength fabric is substantially fixedly or fixedly positioned with respect to the outer shell of the vehicle. In another embodiment, the ballistic and/or fire barrier protects objects in a structure from damage due to projectile penetration. The ballistic and/or fire barrier includes at least one layer of high strength fabric positioned towards an outer housing of the structure. The high strength fabric is substantially fixedly positioned with respect to the structure towards either the inner or outer surface of the outer housing. In another embodiment of the present invention, a ballistic barrier protects a wearer of the ballistic barrier from damage due to projectile penetration. The ballistic barrier comprises first and second portions positioned generally parallel each other. The first portion includes one or more layers of high strength fabric while the second portion is generally impact-resistant. Preferably, the layer of high strength fabric comprise a plurality of plies. One of the plies can comprise woven fibers. Another of the plies can be a felt. Also preferably, the layer of high strength fabric in the ballistic barrier embodiments comprises a polymer material such as one or more of aramid material, polyethylene material, and polybenzoxazole material. | ||||||
| 140 | Small weapons shield for helicopters | US11048130 | 2005-02-02 | US07059567B1 | 2006-06-13 | Dino Scorziello |
| A small weapons shield for helicopters consisting of a protective shield (10), which consists of a light-weight, ballistic-resistant composite material, extension rods (20) made of steel, and support wires (30) made of steel cable. The support wires (30) are connected to the protective shield (10) through holes protected by eyelets (40) that protect the shield from fraying. The shield is supported away from the helicopter (1) to prevent transferring large impact forces directly to the helicopter (1). | ||||||
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