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公开(公告)号：US06926235B2
公开(公告)日：2005-08-09
申请号：US10600400
申请日：2003-06-20
CPC分类号： B64C1/00 , B64C29/0058 , B64C39/024 , B64C2201/046 , B64C2201/086 , B64C2201/088 , B64C2201/104 , B64C2201/121 , B64C2201/165 , B64C2201/167 , B64C2201/187 , B64D7/00
摘要： 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.
摘要翻译： 模块化组件组可配置成形成多个具有飞行能力的平台。 多个端片各自具有连续地连接的弯曲外部部分，每个端部从尖端纵向扩展以终止于钝的附接面。 主体部件具有相对的端部以接收端部钝器附接面，以及具有相对壁的矩形中间部分。 多个任务专用面板各自可拆卸地连接到相对的壁之一。 至少一个具有端部件的主体部件在相对的端部连接，并且连接到相对的一个壁之一的任务专用面板中的至少一个为每个具有飞行能力的平台形成最小的部件组。
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公开(公告)号：US06926231B2
公开(公告)日：2005-08-09
申请号：US10829757
申请日：2004-04-22
CPC分类号： F02K7/075 , B64C1/1415 , B64C29/0058 , B64D5/00 , B64D27/023 , B64D27/20 , Y02T50/44 , Y02T50/672
摘要： A method is provided for reducing vulnerability to hostile detection of and aggression towards an aircraft. The method includes adapting an aircraft fuselage to form an armored payload bay, wherein the armored payload bay includes a pair of sidewalls and a bottom. The method additionally includes adapting wings of the aircraft to allow the aircraft to be transported within a larger aircraft. For example, the wings could have a fixed wing span that allows the aircraft to transported within a larger aircraft or the wings could be adapted to fold so that the aircraft can transported within a larger aircraft. The method further includes disposing at least one pulse ejector thrust augmentor (PETA) bank within each sidewall. Each PETA bank is oriented such that a thrust exhaust produced is directed down and away from a centerline of the payload bay. Still further, the method includes adapting the bottom of payload bay to allow ingress and egress of cargo.
摘要翻译： 提供了一种减少对飞机的敌对侦察和侵略的脆弱性的方法。 该方法包括使飞行器机身适应形成装甲有效载荷舱，其中装甲有效载荷舱包括一对侧壁和底部。 该方法还包括使飞行器的翼适应，以允许飞机在较大的飞机内运输。 例如，机翼可以具有固定的机翼跨度，其允许飞机在更大的飞行器内运输，或者翼可以适应折叠，使得飞机可以在更大的飞机内运输。 该方法还包括在每个侧壁内设置至少一个脉冲喷射推力增强器（PETA）组。 每个PETA组被定向成使得产生的推力排气向下并远离有效载荷舱的中心线。 此外，该方法包括调整有效载荷底部以允许货物的入口和出口。
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公开(公告)号：US06976654B2
公开(公告)日：2005-12-20
申请号：US10829743
申请日：2004-04-22
CPC分类号： F02K7/075 , B64C1/1415 , B64C29/0058 , B64D5/00 , B64D27/023 , B64D27/20 , Y02T50/44 , Y02T50/672
摘要： A flight capable mobile platform adapted for covert deployment is provided. The mobile platform is additionally adapted to have a reduced vulnerability to hostile detection and aggression. The mobile platform includes a fuselage having a pair of sidewalls and a bottom. The sidewalls and bottom form an armored payload bay. The mobile platform additionally includes a pair of wings connected to the fuselage. The wings have a fixed wingspan constructed such that the mobile platform can be transported by a larger second mobile platform. This allows for the mobile platform to be aerial deployed from the larger second mobile platform. Each of the sidewalls include at least one pulse ejector thrust augmentor (PETA) bank that is canted outward. Therefore, thrust exhaust produced by each PETA bank is directed down and away from a centerline of the payload bay. Furthermore, the bottom of the mobile platform is adapted to allow ingress and egress of cargo, e.g. military troops, from the payload bay.
摘要翻译： 提供了一种适合隐蔽部署的具有行动能力的移动平台。 移动平台还适应于对敌对检测和侵略的脆弱性降低。 移动平台包括具有一对侧壁和底部的机身。 侧壁和底部形成一个装甲有效载荷舱。 移动平台还包括连接到机身的一对翼。 机翼具有固定的翼展，其构造使得移动平台能够被较大的第二移动平台运输。 这允许移动平台从较大的第二移动平台进行空中部署。 每个侧壁包括向外倾斜的至少一个脉冲喷射器推力增强器（PETA）组。 因此，每个PETA银行产生的推力排气被引导向下并远离有效载荷舱的中心线。 此外，移动平台的底部适于允许货物的进出口。 军事部队，从有效载荷湾。
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公开(公告)号：US06824097B1
公开(公告)日：2004-11-30
申请号：US10649033
申请日：2003-08-27
IPC分类号： B64D2720
CPC分类号： F02K7/075 , B64C1/1415 , B64C29/0058 , B64D5/00 , B64D27/023 , B64D27/20 , Y02T50/44 , Y02T50/672
摘要： An aircraft adapted for covert deployment and having low vulnerability to hostile detection and aggression is provided. The aircraft includes a fuselage having a pair of sidewalls and a bottom. The sidewalls and bottom form an armored payload bay. The aircraft additionally includes a pair of wings connected to the fuselage. The wings have a fixed wingspan constrained such that the aircraft can be transported within a larger aircraft. This allows for the aircraft to be aerial deployed from the larger aircraft. Each of the sidewalls include at least one pulse ejector thrust augmentor (PETA) bank that is canted outward. Therefore, a thrust exhaust produced by each PETA bank is directed down and away from a centerline of the payload bay. Furthermore, the bottom of the aircraft is adapted to allow ingress and egress of cargo, e.g. military troops, from the payload bay.
摘要翻译： 提供了一种适用于秘密部署并且具有较低的敌对侦察和侵略脆弱性的飞机。 飞机包括具有一对侧壁和底部的机身。 侧壁和底部形成一个装甲有效载荷舱。 飞机还包括一对连接到机身的机翼。 机翼具有固定的翼展限制，使得飞机可以在更大的飞机内运输。 这允许飞机从较大的飞机部署空中。 每个侧壁包括向外倾斜的至少一个脉冲喷射器推力增强器（PETA）组。 因此，每个PETA银行产生的推力排气被引导向下并远离有效载荷舱的中心线。 此外，飞机的底部适于允许货物的进出口。 军事部队，从有效载荷湾。
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公开(公告)号：US08162262B2
公开(公告)日：2012-04-24
申请号：US11831806
申请日：2007-07-31
IPC分类号： B64D9/00
CPC分类号： B64C39/024 , B64D1/22 , B64D39/00
摘要： A reconfigurable aircraft and associated methods. In one embodiment the reconfigurable aircraft comprises a plurality of payload retainers. The payload retainers are configured to receive and retain payloads, including fuel, armaments and sensors. The aircraft is configured to cooperate in flight with an airborne supply vehicle to receive the payloads from the supply vehicle.
摘要翻译： 可重构飞机及相关方法。 在一个实施例中，可重构飞机包括多个有效载荷保持器。 有效载荷保持器被配置为接收和保留有效载荷，包括燃料，武器和传感器。 该飞机被配置为与空中供应车辆在飞行中配合以从供应车辆接收有效载荷。
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公开(公告)号：US20100025523A1
公开(公告)日：2010-02-04
申请号：US11831806
申请日：2007-07-31
CPC分类号： B64C39/024 , B64D1/22 , B64D39/00
摘要： A reconfigurable aircraft and associated methods. In one embodiment the reconfigurable aircraft comprises a plurality of payload retainers. The payload retainers are configured to receive and retain payloads, including fuel, armaments and sensors. The aircraft is configured to cooperate in flight with an airborne supply vehicle to receive the payloads from the supply vehicle.
摘要翻译： 可重构飞机及相关方法。 在一个实施例中，可重构飞机包括多个有效载荷保持器。 有效载荷保持器被配置为接收和保留有效载荷，包括燃料，武器和传感器。 该飞机被配置为与空中供应车辆在飞行中配合以从供应车辆接收有效载荷。
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公开(公告)号：US06793174B2
公开(公告)日：2004-09-21
申请号：US10245145
申请日：2002-09-16
IPC分类号： B64D2720
CPC分类号： B64C29/0058 , F02K7/02 , F02K7/075 , Y02T50/671
摘要： A vertical take-off and landing (VTOL) aircraft includes separate axial and vertical propulsion sources. The vertical propulsion source includes pulsejet engines located in separate augmentor bays having apertured walls to equalize pulsejet thrust. The pulsejet engine structure is integrated with aircraft structure such that aircraft structural loads are partially carried by each pulsejet engine. Each pulsejet engine produces an aircraft vertical thrust component throttled or exhaust restricted to control aircraft ascent or descent separate from the axial propulsion source. One or more inlet cowls isolate the pulsejet engine bays. One or more outlet cowls at the exhaust bays assist in controlling pulsejet engine thrust. By using separate axial and vertical thrust sources and pulsejet engines for vertical thrust, aircraft speed, payload and operating range are improved and loss of one or more lift engines is mitigated compared to VTOL aircraft using a single propulsion source type for axial and vertical thrust.
摘要翻译： 垂直起降飞机包括独立的轴向和垂直推进源。 垂直推进源包括位于具有多孔壁的单独增强器舱中的脉冲喷气发动机，以均衡脉冲喷射推力。 脉冲喷气发动机结构与飞机结构集成，使得飞机结构载荷由每个脉冲喷气发动机部分承载。 每个脉冲喷气发动机产生一个飞机垂直推力组件，节流或排气被限制，以控制与轴向推进源分离的飞机上升或下降。 一个或多个入口罩隔离脉冲喷气发动机舱。 在排气槽处的一个或多个出口罩有助于控制脉冲喷气发动机推力。 通过使用单独的轴向和垂直推力源和脉冲喷气发动机用于垂直推力，与使用单个推进源类型用于轴向和垂直推力的垂直起降飞机相比，改进了飞机速度，有效载荷和操作范围，减轻了一个或多个提升发动机的损失。
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公开(公告)号：US07051510B2
公开(公告)日：2006-05-30
申请号：US10831498
申请日：2004-04-23
申请人： Richard P. Ouellette
发明人： Richard P. Ouellette
IPC分类号： F02K7/075
CPC分类号： F02C5/00
摘要： A pulsejet system and method requires no pulsejet internal moving parts. Each pulsejet includes a combustion chamber having an upstream inlet port joined to an inlet diffuser, boundary layer air ports enveloping the combustion chamber, and a downstream exit port joined to a discharge nozzle. Each pulsejet discharges into an ejector to increase net thrust. Each ejector includes an augmentor cell having side walls and perforated end plates. The perforated end plate between each pair of pulsejets is shared to permit the discharge thrust to equalize across the pulsejet group. Air and fuel mix in the combustion chamber and are detonated by a reflected back-pressure wave. Detonation/deflagration reverse pressure waves compressing boundary layer air flow act as a pneumatic throat to temporarily choke off inlet fresh air at the upstream inlet port. The pneumatic throat replaces the conventional mechanical valve used for this purpose.
摘要翻译： 脉冲喷射系统和方法不需要脉冲喷射内部运动部件。 每个脉冲喷射器包括燃烧室，其具有连接到入口扩散器的上游入口端口，包围燃烧室的边界层空气端口和与排放喷嘴连接的下游出口。 每个脉冲喷射器排放到喷射器中以增加净推力。 每个喷射器包括具有侧壁和穿孔端板的增强单元。 在每对脉冲喷射组之间的穿孔端板被共享以允许排出推力跨过脉冲喷射组平衡。 空气和燃料在燃烧室中混合并被反射的背压波引爆。 爆震/爆燃反压波压缩边界层气流作为气动喉管暂时阻塞上游入口处的入口新鲜空气。 气动喉管代替了用于此目的的常规机械阀门。
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公开(公告)号：US5706649A
公开(公告)日：1998-01-13
申请号：US650583
申请日：1996-05-20
摘要： The present invention is a thrust reversing apparatus for diverting purely rearwardly directed air flowing through an engine nacelle to combined rearward-and-radially-outward flow, and then to a combination of various radially outward angles and forward flow, where in the latter states thrust reversal is effected. The apparatus includes parallel inner and outer air flow blocking members driven by actuators which are coupled to the blocking members for effecting synchronous movement. The inner member includes a first door having fixed vanes and a solid second door pivotably coupled to the first door. The inner member has a closed position in which the two doors are collinear, and various open positions in which the two doors are pivoted relative to one another. The outer member comprises an array of pivotable, parallel vanes, and has a closed position in which the vanes tightly overlap, and various open positions in which the vanes are pivoted out of contact with each other through various amounts of rotation.
摘要翻译： 本发明是一种推力反向装置，用于将流过发动机舱的纯粹向后指向的空气转向组合的后向和径向向外流动，然后转向各种径向向外的角度和向前流动的组合，其中在后者状态推力 反转。 该装置包括由致动器驱动的并联的内部和外部空气流动阻塞构件，其被联接到阻挡构件以实现同步运动。 内部构件包括具有固定叶片的第一门和可枢转地联接到第一门的实心第二门。 内部构件具有闭合位置，其中两个门共线，以及各个打开位置，其中两个门相对于彼此枢转。 外部构件包括可枢转的平行叶片的阵列，并且具有关闭位置，叶片紧密地重叠在该关闭位置，并且各个打开位置，叶片通过各种旋转量彼此不相互转动。
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公开(公告)号：US08441141B1
公开(公告)日：2013-05-14
申请号：US12721628
申请日：2010-03-11
IPC分类号： H02P9/04
CPC分类号： F03D5/02 , B63B21/502 , F03D9/17 , F03D9/25 , F03D9/28 , F03D13/25 , F05B2240/124 , F05B2240/13 , F05B2240/14 , F05B2240/93 , F05B2240/95 , F05B2260/403 , Y02E10/70 , Y02E10/727 , Y02E60/15
摘要： A wind power system including a first pulley, a second pulley spaced from the first pulley, a continuous loop structure engaged with the first and second pulleys, a plurality of airfoils fixedly connected to the continuous loop structure, wherein the airfoils extend outward from the continuous loop structure, and a fairing positioned to direct airflow to the airfoils.
摘要翻译： 一种风力发电系统，包括第一滑轮，与第一滑轮间隔开的第二滑轮，与第一和第二滑轮接合的连续环形结构，固定地连接到连续环结构的多个翼型件，其中翼型件从连续的 环形结构，以及将气流引向翼型的整流罩。
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