| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 241 | Accessory for vehicle | US11812301 | 2007-06-18 | US20080099622A1 | 2008-05-01 | Meir Yoffe |
| External store systems and assemblies for a carrier vehicle are provided. In some embodiments, the system includes a plurality of external store elements, each external store element comprising a plurality of surfaces defining an exterior thereof, the surfaces comprising at least one face, and a mounting arrangement configured for enabling reversible mounting of the elements to form at least one external store assembly having at least one of electrical continuity and aerodynamic conformality between adjacent external store elements, and for reversibly attaching the external store elements to a carrier vehicle. | ||||||
| 242 | Missile defense system and methods for evading heat seeking missiles | US11199268 | 2005-08-09 | US20070034072A1 | 2007-02-15 | Leonard Greene |
| A method for aiding a helicopter pilot to avoid a heat seeking missile includes the step of detecting a threat from a missile. The method also includes the step of reducing heat emanating from the helicopter's engine and rapidly reducing altitude. Then, when the threat has passed flight is resumed. A system for accomplishing the above is also described which simultaneously reduces engine temperature, deflects the exhaust gases, injects water into the exhaust gases, reduces altitude and launches a countermeasure. | ||||||
| 243 | Unmanned air vehicle, integrated weapon platform, avionics system and control method | US11160645 | 2005-07-01 | US20070023582A1 | 2007-02-01 | Daniel Steele; Joseph Chovan |
| A small, reusable interceptor unmanned air vehicle (UAV), an avionics control system for the UAV, a design method for the UAV and a method for controlling the UAV, for interdiction of small scale air, water and ground threats. The UAV includes a high performance airframe with integrated weapon and avionics platforms. Design of the UAV first involves the selection of a suitable weapon, then the design of the interceptor airframe to achieve weapon aiming via airframe maneuvering. The UAV utilizes an avionics control system that is vehicle-centric and, as such, provides for a high degree of autonomous control of the UAV. A situational awareness processor has access to a suite of disparate sensors that provide data for intelligently (autonomously) carrying out various mission scenarios. A flight control processor operationally integrated with the situational awareness processor includes a pilot controller and an autopilot controller for flying and maneuvering the UAV. | ||||||
| 244 | Apparatus and method for air-to-air arming of aerial vehicles | US10568242 | 2004-02-18 | US20060202088A1 | 2006-09-14 | Nir Padan |
| A transfer of ordnance units (20) from a first aerial vehicle (10) to a second aerial vehicle (14) performed while both vehicles are airborne. The first aircraft (10) is used as an ordnance storage, ordnance delivery and ordnance supplier platform. The second aircraft (14) has the functionality and capability of delivering the received ordnance (20) to designated targets. The first aircraft (10) includes an ordnance storage apparatus, an ordnance transfer assembly (22), a computer-based highly accurate ordnance transfer control apparatus, and an ordnance transfer apparatus operating crew. The ordnance transfer assembly (22) establishes temporarily a transfer link between the aircraft and utilizes an ordnance conveyor mechanism for the delivery of the ordnance units (20). The second aircraft (14) includes a multi-use multi-purpose pylon (16) that receives the transferred ordnance (20) in the proper manner. The aircrafts can be uninhabited. | ||||||
| 245 | Recoverable pod for self-protection of aircraft and method of protecting an aircraft using a recoverable pod | US10739866 | 2003-12-18 | US07053812B2 | 2006-05-30 | Daniel W. Trainor |
| In a countermeasure system for an aircraft, a countermeasure module includes a chamber. Countermeasure equipment is housed in the chamber of the countermeasure module. An attachment mechanism allows for releasable attachment of the countermeasure module to an aircraft. A flight mechanism is provided on the countermeasure module for returning the countermeasure module to a location, such that when an aircraft to which the countermeasure module is attached reaches a desired airborne position, the attachment mechanism releases the countermeasure module from the aircraft, and the flight mechanism on the released countermeasure module returns the countermeasure module to the location. | ||||||
| 246 | Apparatus and method for restraining and releasing a control surface | US10369370 | 2003-02-18 | US07040210B2 | 2006-05-09 | Gregory M. Richards |
| An apparatus includes a restraint for restraining a first control surface in a stowed configuration and a severing mechanism for parting the restraint to allow the first control surface to move into an operational configuration. A vehicle includes a body, a first control surface rotatably mounted to the body, and a restraint attached to the first control surface for restraining the first control surface in a stowed configuration. The vehicle further includes a severing mechanism for parting the restraint to allow the first control surface to move into an operational configuration. A method includes attaching a restraint to the control surface to restrain the control surface in a stowed configuration and cutting the restraint to allow the control surface to move to an operational configuration. | ||||||
| 247 | Penetration-and fire resistant fabric materials and structures | US09544357 | 2000-04-06 | US06951162B1 | 2005-10-04 | Donald A. Shockey; David C. Erlich; Jeffrey W. 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. | ||||||
| 248 | Method and apparatus for reducing the infrared and radar signature of a vehicle | US10514753 | 2003-05-23 | US20050208321A1 | 2005-09-22 | Bryan Riley; Robert 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. | ||||||
| 249 | Runway-independent omni-role modularity enhancement (ROME) vehicle | US10600400 | 2003-06-20 | US06926235B2 | 2005-08-09 | Richard P. Ouellette; Aaron J. Kutzmann |
| A modular component set is configurable to form a plurality of flight capable platforms. A plurality of end pieces each has contiguously connected curved outer portions each longitudinally expanding from a tip to terminate at a blunt attachment face. Body members have opposed ends to receive the end piece blunt attachment face, and a rectangular shaped mid-portion having opposed walls. A plurality of task specific panels are each releasably connectable to one of the opposed walls. At least one of the body members with the end pieces joined at the opposed ends, and at least one of the task specific panels connected to one of the opposed walls form a minimum component set for each of the flight capable platforms. | ||||||
| 250 | Method of manufacturing window having at least one of radio wave stealth property and electromagnetic wave shield property, and window material having at least one of radio wave stealth property and electromagnetic wave shield property | US10946114 | 2004-09-22 | US20050170083A1 | 2005-08-04 | Kazuyuki Oguri |
| There is provided a method of manufacturing a window having at least one of a radio wave stealth property and an electromagnetic wave shield property comprising: a step for forming a thin-film composed of a conductive material on the surface of a transparent window member having a curved surface, and a step for forming the thin-film into a mesh shape. As a result, it is, possible to manufacture, at lower cost, a window having a radio wave stealth property that scatters radio waves in various directions so as not to be detected by radar, while transparency to visible light is improved, as well as a window having an electromagnetic wave shield property that effectively prevents harmful electromagnetic waves, except for visible radiation, from invasion into an aircraft. | ||||||
| 251 | RECOVERABLE POD FOR SELF-PROTECTION OF AIRCRAFT AND METHOD OF PROTECTING AN AIRCRAFT USING A RECOVERABLE POD | US10739866 | 2003-12-18 | US20050134496A1 | 2005-06-23 | Daniel Trainor |
| In a countermeasure system for an aircraft, a countermeasure module includes a chamber. Countermeasure equipment is housed in the chamber of the countermeasure module. An attachment mechanism allows for releasable attachment of the countermeasure module to an aircraft. A flight mechanism is provided on the countermeasure module for returning the countermeasure module to a location, such that when an aircraft to which the countermeasure module is attached reaches a desired airborne position, the attachment mechanism releases the countermeasure module from the aircraft, and the flight mechanism on the released countermeasure module returns the countermeasure module to the location. | ||||||
| 252 | Aircraft with forward opening inlay spoilers for yaw control | US10353660 | 2003-01-29 | US06892982B2 | 2005-05-17 | Walter Dennis Clark |
| An aircraft comprises first and second wings positioned on opposite sides of a longitudinal axis, a first forward opening control surface attached to an upper surface of the first wing, and a second forward opening control surface attached to an upper surface of the second wing, wherein each of the first and second hinges is canted with respect to a direction perpendicular to a longitudinal axis of the aircraft. A method of providing yaw control of an aircraft is also provided. The method comprises the steps of providing a first forward opening, canted spoiler in a top surface of a first wing of the aircraft, providing a second forward opening, canted spoiler in a top surface of a second wing of the aircraft, and operating the first and second spoilers differentially to create a yaw moment. The creation of yaw moments without any down force has application in sweptback wings where the tips are behind the center of gravity of the aircraft. The advantage is in reducing radar cross section over traditional (forward hinged, rearward opening) spoilers where there must be a spoiler on the bottom side to counter the down force created by the top spoiler. | ||||||
| 253 | Conformal airliner defense (CAD) system | US10624784 | 2003-07-22 | US20050029394A1 | 2005-02-10 | James Ackleson; Michael Guy; Robert Hale; Jeffrey Plebanski |
| A conformal air defense (CAD) system is provided which is adapted to be attached externally to an aircraft as an appendage. The CAD system includes a conformal mounting adapter having an aircraft-to-adapter interface and upper adapter side. A mounting structure is provided which has an adapter interface and a mounting side, wherein the adapter interface is attached to the upper adapter side. A missile countermeasures system is mounted on the mounting side of the mounting structure. And a cover substantially encloses the countermeasures system, wherein the cover is removably fastened to the mounting side of the mounting structure. | ||||||
| 254 | Hanger assembly for aircraft | US10797681 | 2004-03-05 | US20040262456A1 | 2004-12-30 | 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. | ||||||
| 255 | Aircraft sensor pod assembly | US10373459 | 2003-02-25 | US06745981B1 | 2004-06-08 | Stanley Irvin Rainer; Vito Richard Simone; Paul Arthur Fraser |
| The invention is a sensor pod for mounting on the top surface of the fuselage of an aircraft. The pod it supported by right and left front supports and right and left rear supports that attach to the fuselage on either side of the longitudinal axis of the aircraft. A fifth structural support, aligned with the longitudinal axis of the aircraft, has a first end attached to the fuselage of the aircraft a second end attached to the sensor pod the aircraft. | ||||||
| 256 | Modular integrated self-contained cargo deployment/retrieval system | US10156899 | 2002-05-28 | US06708926B2 | 2004-03-23 | Frank H. Bonisch |
| The present invention relates to self contained, modular integrated deployment and retrieval system for use with an aircraft such as a helicopter. The deployment and retrieval system comprises a support frame, a winch connected to the support frame, a tow cable wound around the winch, which tow cable is connected to the external load, and a support structure connected to the support frame. The support structure is axially movable relative to the support frame for moving the external load so as to control the center of gravity of the aircraft and so as to deploy and retrieve the external load. | ||||||
| 257 | Apparatus for improving the installation moments of external loads on aircraft | US09851414 | 2001-05-09 | US06669140B2 | 2003-12-30 | Ronald Deslandes; Stefan Donauer; Alois Pantele |
| Apparatus for reducing the installation moments of an external load installed at at least one fastening station of an aircraft includes a ramp arranged in front of the shoulder station relative to the direction of flight. The height of the ramp increases toward the fastening station, and the end of the ramp that is located in proximity of the shoulder station forms a break-off edge that is disposed at a predetermined distance from the outer side of the external load that is directed toward the break-off edge, in order to influence pitch moments and yawing moments of the external load. | ||||||
| 258 | Penetration resistant fabric structures and materials | US09325596 | 1999-06-02 | US06612217B1 | 2003-09-02 | Donald A. Shockey; David C. Erlich; Jeffrey W. Simons |
| A ballistic barrier for protecting an aircraft from damage due to projectile penetration, the aircraft having a fuselage including an outer skin, an inner panel and a structure. The ballistic barrier includes at least one layer of high strength fabric disposed between the outer skin and the inner panel of the aircraft which is substantially fixedly positioned with respect to the fuselage of the aircraft. Preferably, the at least one layer of high strength fabric comprises a plurality of plies. One of the plies can be a felt. Another of the plies can comprise woven fibers. Also preferably, the at least one layer of high strength fabric comprises a polymer material such as one or more of aramid material, polyethylene material, and polybenzoxazole material. The layer of high strength fabric can be attached to at least one of the frames of the structure of the fuselage, to a layer of insulation positioned between the outer skin and inner panel of the fuselage of the aircraft, or be enclosed within an outer covering of a layer of insulation positioned between the outer skin and inner panel of the fuselage of the aircraft. | ||||||
| 259 | Ballistic shield for dual engine single output shaft propulsion system | US09816598 | 2001-03-22 | US06484970B2 | 2002-11-26 | Hersheng Lin; Shen-yeh Chen |
| A ballistic shield containment system for preventing fragments expelled from an engine assembly from penetrating the casing of an adjacently disposed engine is provided. In a turboprop engine assembly having two power sections connected through a combining gearbox to a single propeller shaft, it is imperative that failure of the rotor disks in one engine not cause failure of the remaining engine. A substantially rectangular shaped panel member is supported at approximately the mid-point between the power sections by a support truss system extending from the panel to a space frame. The space frame is supported by a separate truss system connected to fixed bulkhead. The panel includes reinforcing ribs to prevent fragment penetration and excessive deformation. Each of the truss members is attached at either end to a spherical bearing capable of transmitting force loads while preventing transmission of moment loads. | ||||||
| 260 | Ballistic shield for dual engine single output shaft propulsion system | US09816598 | 2001-03-22 | US20020134887A1 | 2002-09-26 | Hersheng Lin; Shen-Yeh Chen |
| A ballistic shield containment system for preventing fragments expelled from an engine assembly from penetrating the casing of an adjacently disposed engine is provided. In a turboprop engine assembly having two power sections connected through a combining gearbox to a single propeller shaft, it is imperative that failure of the rotor disks in one engine not cause failure of the remaining engine. A substantially rectangular shaped panel member is supported at approximately the mid-point between the power sections by a support truss system extending from the panel to a space frame. The space frame is supported by a separate truss system connected to fixed bulkhead. The panel includes reinforcing ribs to prevent fragment penetration and excessive deformation. Each of the truss members is attached at either end to a spherical bearing capable of transmitting force loads while preventing transmission of moment loads. | ||||||
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