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1. 发明申请

US20030094540A1 Last chance aircraft back-up hydraulic system 失效
标题翻译：最后机会飞机后备液压系统
公开(公告)号：US20030094540A1
公开(公告)日：2003-05-22
申请号：US09990639
申请日：2001-11-21
申请人： The Boeing Company
发明人： Paul E. Shappell , Richard H. Janiesch
IPC分类号： B64B001/36 , B64C015/00
CPC分类号： B64C13/42 , F15B20/005 , F15B21/06
摘要： A last chance aircraft back-up hydraulic system in which fuel from the fuel tanks of the aircraft is injected into the return line of a leaking hydraulic system by use of a pump activated by a guarded switch by the aircraft's pilot. The fuel serves as hydraulic fluid to operate the pumps of the system as it is injected upstream from the fluid being lost to extend the operating time of the system and prevent failure so the aircraft can be landed at a site.
摘要翻译：最后一次飞机后备液压系统，其中来自飞机的燃料箱的燃料通过使用由飞行器的驾驶员由防护开关激活的泵被注入到泄漏的液压系统的返回管线中。燃料用作液压流体，以在系统的泵被注入上游从被损失的流体喷射以延长系统的运行时间并且防止故障从而使飞机降落在现场时操作系统的泵。

2. 发明申请

US20040089764A1 Passive jet spoiler for yaw control of an aircraft 有权
标题翻译：用于飞机偏航控制的被动喷气扰流板
公开(公告)号：US20040089764A1
公开(公告)日：2004-05-13
申请号：US10229971
申请日：2002-08-28
发明人： Paul D. McClure
IPC分类号： B64B001/36 , B64C015/00
CPC分类号： B64C15/14
摘要： A wing for an aircraft has a passive jet spoiler for providing yaw control by increasing drag on the wing. The spoiler comprises an inlet located near the leading edge of a lower surface of the wing and at least one outlet formed on the lower surface or on an upper surface of the wing. An internal passage connects the inlet and each outlet for allowing air to pass from the inlet to the outlet. The air exits the outlets generally normal to the respective surface of the wing, causing a laminar flow to separate from the surfaces downstream of each outlet. The separated flow increases the drag on the wing, producing a yawing moment on the aircraft. Selective placement of the outlets on the upper and lower surfaces limits undesirable roll and pitch moments. Valves are provided for selectively controlling the amount of air passing through the spoiler.
摘要翻译：用于飞机的机翼具有被动喷气扰流板，用于通过增加机翼上的阻力来提供偏航控制。扰流器包括位于翼的下表面的前缘附近的入口和形成在翼的下表面或上表面上的至少一个出口。内部通道连接入口和每个出口，以允许空气从入口通向出口。空气通常垂直于机翼的相应表面离开出口，导致层流与每个出口下游的表面分离。分离的流量增加了机翼上的阻力，在飞机上产生了偏航力矩。出口在上表面和下表面上的选择性放置限制了不希望的滚动和俯仰力矩。提供阀，用于选择性地控制通过扰流器的空气量。

3. 发明申请

US20020074453A1 Creating imbalanced thrust in a center line mounted multi-engine jet aircraft configuration and a method of using imbalanced thrust 有权
标题翻译：在中心线安装的多引擎喷气式飞机配置中创建不平衡推力和使用不平衡推力的方法
公开(公告)号：US20020074453A1
公开(公告)日：2002-06-20
申请号：US09912078
申请日：2001-07-24
发明人： Richard J. Bacon
IPC分类号： B64B001/36 , B64C015/00
CPC分类号： B64D27/20 , B64C15/00
摘要： A centerline mounted overbalanced multiple main jet engine configuration. The multiple jet engines are centerline mounted rather than parallel offset. While each jet engine is a nullmainnull engine, capable of safely operating the aircraft in the event of a failure of the other engines, the engines are overbalanced in the sense that at least one of the main engines has substantially greater thrust than the other main engines. All of the main engines operate at critical periods of flight, but only one or the other of the main engines operates at other periods. The configuration of this invention combines the efficiency and performance of a single engined aircraft with enhanced safety advantages.
摘要翻译：中心线安装超平衡多主喷气发动机配置。多台喷气发动机是中心线安装的，而不是平行偏移。虽然每个喷气发动机是“主要”发动机，能够在其他发动机发生故障的情况下安全地操作飞行器，但是发动机是过平衡的，因为主发动机中的至少一个具有比其他发动机大得多的推力主机所有主要发动机都在关键的飞行时段运行，但只有一个或另一个主发动机在其他时期运行。本发明的结构将单个发动机的效率和性能与增强的安全性优点相结合。

4. 发明申请

US20040245381A1 Hot gas valve with fibrous monolith ceramic 审中-公开
标题翻译：热气阀与纤维整体陶瓷
公开(公告)号：US20040245381A1
公开(公告)日：2004-12-09
申请号：US10440327
申请日：2003-05-16
发明人： Jason A. Gratton , Don L. Mittendorf
IPC分类号： B64B001/36
CPC分类号： F02K9/805 , F05D2270/18 , F16K25/005 , F16K31/1245 , F16K31/426
摘要： A valve is disclosed for use in hot gas applications such as in rocket or missile engine systems or the like. The valve is designed to withstand the extreme temperatures encountered in the gas exhaust from rocket propellants. The valve seat of the valve is constructed of fibrous monolith ceramic. This material does not degrade significantly when rocket exhaust, such as resulting when ammonium perchlorate propellant is burned, is ported through the valve. The valve generally includes a valve body, a valve seat, through which gases may pass, and a poppet which opens and closes the valve by pressing against and moving away from the valve seat.
摘要翻译：公开了用于热气应用中的阀门，例如在火箭或导弹发动机系统等中。该阀被设计成可承受火箭推进剂排气中遇到的极端温度。阀的阀座由纤维整体陶瓷构成。当火焰排放（如高氯酸铵推进剂燃烧时产生的）被引入阀门时，该物质不会显着降解。阀通常包括阀体，阀座，气体可以通过该阀座，以及通过压靠和离开阀座而打开和关闭阀的提升阀。

5. 发明申请

US20040084566A1 Multi-nozzle grid missile propulsion system 审中-公开
标题翻译：多喷嘴格栅导弹推进系统
公开(公告)号：US20040084566A1
公开(公告)日：2004-05-06
申请号：US10288943
申请日：2002-11-06
发明人： Daniel Chasman
IPC分类号： B64B001/36
CPC分类号： F02K9/97
摘要： A jet propulsion outlet device is disclosed that has a grid plate having a plurality of densely clustered nozzlettes, the nozzlettes of the grid plate being configured to operably couple to a pressurized gas source to efficiently expand the pressurized gas.
摘要翻译：公开了一种具有多个密集聚集的喷嘴的格栅板的喷射推进出口装置，格栅板的喷嘴构造成可操作地耦合到加压气体源以有效地扩张加压气体。

6. 发明申请

US20030201363A1 Aircraft internal wing and design 有权
标题翻译：飞机内翼和设计
公开(公告)号：US20030201363A1
公开(公告)日：2003-10-30
申请号：US10046957
申请日：2002-01-14
发明人： Robert Jonathan Carr
IPC分类号： B64B001/36 , B64D027/00 , B64C015/00
CPC分类号： B64C3/46 , B64C39/066 , B64C39/068 , Y02T50/14
摘要： An aircraft designed with three wings located on either side of the fuselage. The forward wing has a downward angle with a curved top and bottom surface. The upper wing is located towards the rear of the aircraft and above the forward wing. The lower wing is located below the upper wing and slightly forward. It is also located to the rear and below of the forward wing. The outer ends of all three wings come into contact at one point. The forward wing uses the Coanda effect to increase the airflow across the top surface of the bottom wing. The aircraft can be designed so that it is large enough to carry people and/or cargo, or to be small enough to be flown as a toy aircraft. The like design can use any type of aircraft engine commonly used today. One embodiment of the aircraft has two turbines, shaft-coupled to a power source, located on either side of the forward end of the fuselage. Each engine has part of its thrust diverted through and directed by a plenum disposed internal of the coanda toward both sides of the fuselage so that an equal amount of thrust flows through the duct and over the wings on either side of the fuselage. This ensures equal lift on the coanda and both wings on either side of the fuselage in the event that one engine malfunctions.
摘要翻译：设计有三个机翼的飞机位于机身两侧。前翼具有向下的角度，具有弯曲的顶部和底部表面。上翼位于飞机的后方，位于前翼的上方。下翼位于上翼下方，稍微向前。它也位于前翼的后方和下方。所有三个翼的外端在一点接触。前翼使用柯恩达效应来增加穿过底翼顶表面的气流。该飞机可以设计成足够大以携带人和/或货物，或者足够小以作为玩具飞机飞行。类似的设计可以使用今天普遍使用的任何类型的飞机引擎。飞机的一个实施例具有两个位于机身前端两侧的与电源轴耦合的涡轮机。每个发动机的一部分推力通过设置在机身内部的整流室并通过机身的两侧而被引导，以使等量的推力流过机身的导管和机身的两侧。如果一个发动机发生故障，这样可以确保机身两侧的平均升力和机身两侧的两翼。

7. 发明申请

US20020190159A1 Variable cycle propulsion system with compressed air tapping for a supersonic airplane 有权
标题翻译：可变循环推进系统，用于超音速飞机的压缩空气攻丝
公开(公告)号：US20020190159A1
公开(公告)日：2002-12-19
申请号：US10167419
申请日：2002-06-13
申请人： SNECMA MOTEURS
发明人： Michel Franchet , Yann Laugier , Jean Loisy
IPC分类号： B64B001/36 , B64C015/00
CPC分类号： F02K3/025 , F02K3/075 , F02K3/12 , Y02T50/671
摘要： A variable cycle propulsion system for a supersonic airplane, the system comprising at least one engine having at least one compressor and capable of generating thrust for supersonic flight speeds, and at least one auxiliary propulsion assembly separate from said engine, and capable of generating additional thrust for takeoff, landing, and subsonic cruising speeds, at least one pipe connecting the engine to the auxiliary propulsion assembly to convey thereto compressed air produced by the compressor so as to enable the auxiliary propulsion assembly to generate additional thrust for takeoff, landing, and subsonic cruising flight, there being at least one valve enabling the pipe to be closed off for supersonic cruising flight.
摘要翻译：一种用于超音速飞机的可变循环推进系统，该系统包括至少一个具有至少一个压缩机并能够产生用于超音速飞行速度的推力的发动机，以及与所述发动机分离的至少一个辅助推进组件，并且能够产生额外的推力用于起飞，着陆和亚音速巡航速度，至少一个管道将发动机连接到辅助推进组件以将由压缩机产生的压缩空气输送到辅助推进组件，以使辅助推进组件产生用于起飞，着陆和亚音速的附加推力巡航飞行，至少有一个阀门使管道能够被关闭用于超音速巡航飞行。

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