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11.发明公开UNIVERSAL ELECTRICAL INTERFACE BETWEEN AN AIRCRAFT AND AN ASSOCIATED STORE PROVIDING AN ON-SCREEN COMMANDS MENU 失效提供屏幕上命令菜单的飞机和相关商店之间的通用电气接口
公开(公告)号：EP1012820A1
公开(公告)日：2000-06-28
申请号：EP97913677.7
申请日：1997-10-10
IPC分类号： G09G5/00
CPC分类号： F41G7/007 , B64D7/08 , G09G5/08 , G09G2340/12
摘要： Apparatus and method providing an electrical interface (20) between an aircraft (10) and an associated store (20, 16) for controlling data transmissions therebetween. The aircraft (10) has a visual display (38) of video signals received from the associated store (20, 16). The electrical interface (20) includes circuitry for generating a menu (48) of the commands available to an operator of the aircraft (10) and for generating a cursor (44) associated with the menu (48). The electrical interface (20) overlays the menu (48) and cursor (44) on the display (38) to provide a user friendly electrical interface (20).
摘要翻译： 在飞机（10）和相关存储器（20,16）之间提供电接口（20）的设备和方法，用于控制其间的数据传输。 飞机（10）具有从相关存储器（20,16）接收的视频信号的视觉显示（38）。 电气接口（20）包括用于生成可用于飞行器（10）的操作者的命令的菜单（48）并用于生成与菜单（48）相关联的光标（44）的电路。 电接口（20）将菜单（48）和光标（44）叠加在显示器（38）上以提供用户友好的电接口（20）。
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12.发明公开HIGH EFFICIENCY, HIGH POWER DIRECT DIODE LASER SYSTEMS AND METHODS THEREFOR 失效直销高功率激光二极管以高效率和认证的听力程序制度
公开(公告)号：EP1008212A1
公开(公告)日：2000-06-14
申请号：EP97945210.9
申请日：1997-09-16
CPC分类号： G02B6/4249 , H01S5/4012 , H01S5/4025 , H01S5/4087
摘要： A direct diode laser system (400) includes N laser head assemblies (LHAs) (400A, 400B, etc.) generating N output beams and generating N received output beams, and a torch head (500) recollimating and focusing the N received output beams onto a single spot. Preferably, each of the laser head assemblies (400A, 400B, etc.) of the direct diode laser system (400) includes M modules generating M laser beams, wherein each of the M laser beams has a corresponding single wavelength of light, M-1 dichroic filters (420), wherein each of the M-1 dichroic filter (420) transmits a corresponding one of the M laser beams and reflects all other wavelenghts, and a fiber coupling device (460, 462, 464, 466) collecting the M laser beams to produce a respective one of the N output beams. In an exemplary case, the M-1 dichroic filters (420) function as band pass filters. A method of generating a high fluence, high power laser beam is also described.
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公开(公告)号：EP0885411B1
公开(公告)日：2000-01-05
申请号：EP97914819.4
申请日：1997-03-04
CPC分类号： B64C13/12 , G05D1/0077
摘要： A robust mechanical reversion system which provides the ability to fly and land in the absence of any fly-by-wire controls and which is transparent to the pilot during normal operation. The described invention provides a mechanism which includes redundant linear variable differential transmitters (LVDT) (7, 39) which generates a transmitted signal (8, 40) in proportion to the displacement of the control apparatus (3, 4, 78, 79) in the cockpit. The signal is fed to the flight control computer which determines the magnitude of the change represented by the signal and in turn, commands both the control surface servo actuators as well as an electrical mechanical servo actuator (EMA) (24, 47) located in close proximity to the flight compartment and coupled to the mechanical system to move in proportion to the change. An Electromagnetic Actuator drives the disconnected mechanical system in synchronization with the position of the cockpit controls in the fly-by-wire mode for a given control surface each time the servo actuator(s) for the control surface are electrically commanded by the flight computer (1). This causes the mechanical system to remain in phase with the position of the control elements as if connected thereto. In the event of a failure of the fly-by-wire system the mechanical systemis automatically coupled into the control system through locking actuators which release a coupling mechanism including a interlocking pin, locking cams, clutch or other engagement device and clamps or locks the pilots input to the mechanical control loop thus providing direct mechanical control to the surface actuators (2, 77) with very little transient effects.
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公开(公告)号：EP0938392A1
公开(公告)日：1999-09-01
申请号：EP97946244.0
申请日：1997-10-08
发明人： YASUI, Ken, K.
IPC分类号： B21D26
CPC分类号： B21D26/055 , Y10S72/709
摘要： Sheet materials are superplastically formed and optionally diffusion bonded into structures, by directly electrically resistance heating the sheets and forming them with a controlled gas-mass flow while the dies (362) in which they are formed may remain relatively cool. The dies include electrodes and thermocouples placed therein, and gas interface ports that connect to the sheets to be formed to allow rapid formation of structures. Some of the gas interface ports may become sealably attached to the part during the formation process so that the structures may be removed from the dies hot, thus allowing a high die throughput.
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公开(公告)号：EP0928269A1
公开(公告)日：1999-07-14
申请号：EP97941673.0
申请日：1997-09-18
IPC分类号： B64G1
摘要： A nose assembly (26) and method for controlling the rotation and stabilizing the orientation of a vehicle (10) during landing maneuvers. The vehicle (10) includes a nose assembly (26). The vehicle flap assembly (30) includes an actuator (32) and a flap (38a) from and between a fully retracted position and a fully extended position in response to a guidance signal received from a flight control computer. In a preferred embodiment, the flap assembly (30) includes a plurality of flaps (38a-38c) each coupled to the nose assembly frame (26) and an actuator that selectively positions the plurality of flaps (38a-38c) in response to a signal. The method for rotating a vehicle (10) in nose-forward flight, rotating the vehicle (10) in a first direction, and selectively actuating one of a first and second flaps (38a-38c) from a retracted position toward an extended position to generate a damping moment tending to position the vehicle (10) in a base-forward orientation.
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公开(公告)号：EP0745010A1
公开(公告)日：1996-12-04
申请号：EP95910992.0
申请日：1995-02-09
发明人： BABEL, Henry, Wolfgang , FUSON, Phillip, Lawrence , CHICKLES, Colin, Dean , JONES, Cherie, Ann , ANDERSON, Raymond, Hartwell
CPC分类号： F16L13/146 , B21D39/04 , Y10T29/49885 , Y10T29/49934
摘要： A relatively impervious mechanical seal is formed between the outer surface of a tube (1, 3) and the inside surface of a mechanical fitting (7) of a high pressure fluid or hydraulic system by applying a very thin soft metal layer (19) onto the outer surface of the hard metal tube (1, 3) and/or inner surface of the hard metal fitting (7). The thickness of such thin metal layer (19) is independent of the size of the tube (1, 3) and/or fittings (7). Many metals and alloys of those metals exhibit the requisite softness, including silver, gold, tin, platinum, indium, rhodium, and cadmium. Suitably, the coating is about 0.0025 millimeters (0.10 mils) in thickness. After compression, the tube (1, 3) and fitting (7) combination exhibits very low leak rates on the order of 10 cubic centimeters per second or less as measured using the Helium leak test.
摘要翻译： 在管（1,3）的外表面和高压流体或液压系统的机械配件（7）的内表面之间通过将非常薄的软金属层（19）施加到 硬金属管（1,3）的外表面和/或硬金属配件（7）的内表面。 这种薄金属层（19）的厚度与管（1,3）和/或配件（7）的尺寸无关。 许多金属和这些金属的合金表现出必要的柔软性，包括银，金，锡，铂，铟，铑和镉。 该涂层厚度约为0.0025毫米（0.10密耳）。 在压缩之后，如使用氦气泄漏测试所测量的那样，管（1,3）和配件（7）组合显示非常低的泄漏率，每秒10立方厘米或更少。
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公开(公告)号：EP0569561A1
公开(公告)日：1993-11-18
申请号：EP92920175.0
申请日：1992-09-01
发明人： YASUI, Ken, K.
IPC分类号： B21D26
CPC分类号： B21D26/055 , Y10S72/709
摘要： Une matrice de formage (13) comportant une cavité matricielle (19) contient une ébauche de formage (17) composée d'un alliage métallique aux propriétés de superplasticité. La pression de formage dans un espace sous pression (18) contigu à l'ébauche de formage (17) est régulée par un régulateur de pression (23). Le volume de la cavité matricielle (19) est déterminé, lorsque la masse de gaz est initialement contenue dans la cavité (19) au début du cycle de formage. Le temps de formage total est déterminé de manière empirique. La vitesse moyenne d'écoulement de la masse de gaz qui s'échappera de la cavité (19) est calculée en divisant la masse de gaz totale initialement contenue dans la cavité (19) par le temps de formage total. Un compteur (33) d'écoulement du gaz communique fluidiquement avec la cavité (19) et mesure la vitesse d'écoulement du gaz (35) déplacé par l'ébauche de formage (17) et sorti de la cavité (19). Le compteur (33) d'écoulement du gaz est continuellement surveillé lors du cycle de formage ou lorsqu'un signal de vitesse d'écoulement du gaz est renvoyé au régulateur de pression (23). La pression de déformation est régulée par le régulateur de pression (23) de manière à ce que la vitesse d'écoulement du gaz échappé de la cavité (19) s'approche par approximation à la vitesse d'écoulement moyenne déterminée du gaz.
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公开(公告)号：EP0569516A1
公开(公告)日：1993-11-18
申请号：EP92905833.0
申请日：1992-01-27
摘要： Rails de chargement parallèles et fixes (24 26), placés sur le plancher de la plateforme de chargement d'un avion et espacés suffisamment pour y déposer une palette en douceur. Une pluralité de fentes colinéaires sont disposées sur la longueur du plancher de la plateforme de chargement, immédiatement en dedans du bord de chaque rail. Lesdites fentes sont espacées régulièrement et orientées dans le sens de la longueur par rapport au plancher de la plateforme de chargement. Un taquet (38) s'étend au-dessus du plancher de la plateforme de chargement à partir de chaque fente et est conçu pour s'introduire dans une encoche (36) située dans le chargement. Quand il est introduit dans l'encoche, le taquet est conçu pour se déplacer le long de sa fente respective et, de ce fait, déplacer la palette dans le sens de la longueur du plancher de la plateforme de chargement. Ladite palette passe alors successivement de taquet à taquet. Un autre aspect de l'invention a trait à l'utilisation des rails de chargement mobiles sur la rampe de chargement. Ces rails peuvent coulisser dans le sens de la largeur sur la rampe, à l'intérieur de fentes de montage, ce qui permet de modifier l'écartement entre les rails. On facilite, de ce fait, le positionnement du chargement sur la rampe et son alignement avec les rails fixes du plancher de la plateforme de chargement.
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19.发明公开Apparatus for determining the position of a source of electromagnetic radiation relative to a remote object 失效装置，用于检测电磁辐射的关系的源的位置到远处的物体。
公开(公告)号：EP0037725A1
公开(公告)日：1981-10-14
申请号：EP81301463.6
申请日：1981-04-03
摘要： Apparatus for determining the position of a source (30) of electromagnetic radiation relative to a remote object (20) is disclosed. A multicomponent radiating means (40) of unknown orientation is provided having components centered about the origin of the source. A plurality of electrical signals are applied to the components of the multicomponent source to generate a plurality of electromagnetic fields. The electromagnetic fields are distinguishable from one another. A multicomponent receiving means (21) is disposed on the remote object. The multicomponent receiving means is provided with at least three orthogonal components (22, 23, 24) for detecting and measuring components of the electromagnetic fields transmitted from the source. The source and receiving means are adapted for operation at a separation distance sufficient to ensure that the far-field components of the electromagnetic fields are substantially greater in magnitude than the near-field components of the fields. Analyzing means (50) is associated with the receiver for converting the components of the electromagnetic fields into source position relative to the remote object without priori knowledge of the orientation of the sensor or the relative orientation of its components. The analyzing means operates open-loop with respect to the source and determines source position with at least one ambiguous combination of orientation or position.
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公开(公告)号：EP1066479B1
公开(公告)日：2007-12-05
申请号：EP98918751.3
申请日：1998-04-27
发明人： TAN, Jie
CPC分类号： F16H1/14 , B23F15/06 , F16H2055/173 , Y10T74/19623 , Y10T74/19665 , Y10T74/19958
摘要： The present invention is directed to a unique gear set (10) including a conical involute pinion (14) and a mating face gear (12). The mating face gear has an axis (GA) whose location and orientation is usually configured as intersecting with or slightly offset from the pinion axis (PA). The pinion teeth (16) are formed as involute helicoids generated from a base cylinder. The mating face gear teeth are defined by the shape of the mating conical pinion teeth surface at the time when the two mating gears are specifically positioned so as to perform synchronous rotations about their respective axes of rotation. This arrangement allows the gears to mesh and transmit high torque at high speeds through an angle as required in helicopter transmissions and the like.
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