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1. 发明授权

US5779150A Aircraft engine ejector nozzle 失效
标题翻译：飞机发动机喷射器喷嘴
公开(公告)号：US5779150A
公开(公告)日：1998-07-14
申请号：US723589
申请日：1996-10-01
申请人： Gary L. Lidstone , David L. Sandquist , Larry T. Clark , Imre A. Szupkay
发明人： Gary L. Lidstone , David L. Sandquist , Larry T. Clark , Imre A. Szupkay
IPC分类号： F02K1/12 , F02K1/38 , B64D33/04
CPC分类号： F02K1/383 , F02K1/1223 , Y02T50/671
摘要： An aircraft ejector nozzle includes a plug assembly (26) located between upper and lower cowlings (18, 20) and upright sidewalls (22). The plug assembly (26) includes separable upper and lower diverters (28, 30). Each diverter includes multiple subsections pivotably attached end-to-end. In one embodiment, first, second, and third subsections (90, 92, 94) are provided. Stationary ejectors (40, 42) located in the cowlings (18, 20) input ambient airflow (44) into an exhaust stream (32). Preferably the ejectors (40, 42) include mixing components (46). Upper and lower aft flaps (48, 50) further tailor the exhaust path shape. An actuation assembly (52) moves the diverters (28, 30) and aft flaps (48, 50) between their various positions. One actuation assembly embodiment includes a number of rotatable disks (118, 120, 132, 134, 142) for guiding the upper and lower diverters (28, 30) and the aft flaps (48, 50). In a first plug assembly configuration the diverter forward ends (84) are positioned together and the diverter aft ends (86) are positioned together. The first configuration forces exhaust (32) around the diverters (28, 30). In a second plug assembly configuration the diverter forward ends (84) are positioned apart and the diverter aft ends (86) are positioned apart. The second configuration forces exhaust (32) between the diverters (28, 30) while simultaneously covering the ejectors (40, 42). Acoustic linings (100) are provided at various locations within the nozzle and are exposed to the exhaust flow only during noise suppression configurations, thus minimizing liner wear and contamination.
摘要翻译：飞行器喷射器喷嘴包括位于上部和下部整流罩（18,20）和直立侧壁（22）之间的插塞组件（26）。插头组件（26）包括可分离的上部和下部分流器（28,30）。每个分流器包括多个子节点可枢转地连接到端对端。在一个实施例中，提供了第一，第二和第三子部分（90,92,94）。位于整流罩（18,20）中的固定喷射器（40,42）将环境气流（44）输入排气流（32）。优选地，喷射器（40,42）包括混合部件（46）。上下翼片（48,50）进一步调整排气路径形状。致动组件（52）在其各个位置之间移动转向器（28,30）和后挡板（48,50）。一个致动组件实施例包括用于引导上部和下部转向器（28,30）和后部翼片（48,50）的多个可旋转盘（118,120,132,134,142）。在第一插头组件配置中，分流器前端（84）被定位在一起，并且分流器后端（86）被定位在一起。第一构造迫使排气（32）围绕转向器（28,30）。在第二插头组件构造中，分流器前端（84）定位成分开，并且分流器后端（86）被定位成分开。第二结构迫使分流器（28,30）之间的排气（32）同时覆盖喷射器（40,42）。声学衬垫（100）设置在喷嘴内的各个位置处，并且仅在噪声抑制构造期间暴露于排气流，从而最小化衬垫磨损和污染。

2. 发明授权

US5941065A Stowable mixer ejection nozzle 失效
标题翻译：可调式搅拌机喷嘴
公开(公告)号：US5941065A
公开(公告)日：1999-08-24
申请号：US743104
申请日：1996-11-04
申请人： Gary L. Lidstone , Larry T. Clark , Imre A. Szupkay , David L. Sandquist
发明人： Gary L. Lidstone , Larry T. Clark , Imre A. Szupkay , David L. Sandquist
IPC分类号： F02K1/08 , F02K1/36 , F02K1/38 , F02K1/46
CPC分类号： F02K1/36 , F02K1/085 , F02K1/383
摘要： An ejector nozzle (10) including an first cowling (12), a second cowling (14), and opposed upright sidewalls (16) that together form an internal nozzle exhaust path is provided. A reconfigurable plug assembly (18) having separable first and second diverters (20), (22) is located in the exhaust path to direct engine exhaust (24) in either dual paths formed around diverter outer surfaces (76), or dual paths formed between the diverter inner surfaces (74) and centerbody exterior surfaces. When the diverters direct exhaust airflow between themselves, first and second ejectors (26), (28) formed in the first and second cowlings (12), (14), respectively, are available to entrain ambient air (30) into the exhaust stream (24). The preferred ejectors include translatable aft flaps (32), (34). Mixing devices, such as a lobed mixer (90) are incorporated into the diverters (20), (22) to improve engine noise suppression. When the diverters (20), (22) direct exhaust airflow around themselves, the ejectors are closed and the mixing devices are positioned such that they are not significantly exposed to the engine exhaust 24. An actuation assembly moves the diverters (20), (22) and ejectors between various positions.
摘要翻译：提供了包括一起形成内部喷嘴排气路径的第一整流罩（12），第二整流罩（14）和相对的直立侧壁（16）的喷射器喷嘴（10）。具有可分离的第一和第二分支器（20），（22）的可重新配置的插头组件（18）位于排气路径中，以将引擎排气（24）引导到形成在分流器外表面（76）周围的双路径中，或者形成双重路径在分流器内表面（74）和中心体外表面之间。当分流器在它们之间引导排气气流时，分别形成在第一和第二整流罩（12），（14）中的第一和第二喷射器（26），（28）可用于将环境空气（30）夹带到排气流（24）。优选的喷射器包括可翻转的后翼片（32），（34）。混合装置，例如叶片混合器（90）被并入转向器（20），（22）中以改善发动机噪声抑制。当分流器（20），（22）引导自身周围排出气流时，喷射器关闭，并且混合装置被定位成使得它们不会明显地暴露于发动机排气24.致动组件移动分流器（20）， 22）和各种位置之间的喷射器。

3. 发明授权

US4968879A Method and apparatus for measuring aircraft flight parameters 失效
标题翻译：用于测量飞机飞行参数的方法和装置
公开(公告)号：US4968879A
公开(公告)日：1990-11-06
申请号：US226076
申请日：1988-07-29
申请人： Larry T. Clark
发明人： Larry T. Clark
IPC分类号： B64D43/00 , G01P5/10 , G01P13/02
CPC分类号： B64D43/00 , G01P13/025 , G01P5/10
摘要： Various aircraft flight parameters are determined based on the thermal radiation emitted from a plurality of members while the aircraft is flying. A fiberoptic cable is positioned adjacent the member emitting the thermal radiation. A thermal radiation sensor receives, through the fiberoptic cable, the radiation emitted by the member and generates an electrical signal corresponding to the radiation emitted. For an aircraft traveling at high speeds, the heat flux generated across the skin surface by air friction is proportional to the velocity and angle of attack at a given air density. An on-board computer calculates various aircraft flight parameters, such as velocity, angle of attack of various aircraft surfaces, and the like, based on the signals received from the radiation sensors. Aircraft flight parameters are more rapidly and accurately determined than possible in the prior art.
摘要翻译：基于在飞行器飞行时从多个构件发射的热辐射来确定各种飞行器飞行参数。光纤电缆位于发射热辐射的部件附近。热辐射传感器通过光纤电缆接收由构件发射的辐射并产生对应于所发射的辐射的电信号。对于高速行驶的飞机，通过空气摩擦在皮肤表面产生的热通量与给定空气密度下的速度和迎角成比例。基于从辐射传感器接收的信号，车载计算机计算各种飞行器飞行参数，例如各种飞机表面的速度，迎角等。飞行器飞行参数比现有技术中可能更快速和准确地确定。

4. 发明授权

US4688934A Rotating polarizer angle sensing system 失效
标题翻译：旋转偏光片角度感应系统
公开(公告)号：US4688934A
公开(公告)日：1987-08-25
申请号：US863654
申请日：1986-05-15
申请人： Larry T. Clark
发明人： Larry T. Clark
IPC分类号： G01B11/16
CPC分类号： G01B11/168
摘要： A system for measuring aeroelastic deformation of an aircraft wing in flight or in a wind tunnel utilizing light from a linearly polarized light source (101). The light is transmitted through modulating elements (104, 105) to provide a carrier beam, and a small portion of the beam is reflected through a linear polarizer (107) into a photo-detector (108) for utilization as a reference electrical signal (208). The remainder of the beam is reflected back from a retro-reflector target (700) located on the wing into another photo-detector (114) to provide the target electrical signal (209). The two amplified electrical signals are compared in a phase detector (FIG. 3) for providing an angle measurement output signal E.sub.0.
摘要翻译：一种用于利用来自线偏振光源（101）的光测量飞行中或在风洞中的飞机机翼的气动弹性变形的系统。光通过调制元件（104,105）传输以提供载波束，并且光束的一小部分通过线性偏振器（107）反射成光检测器（108）以用作参考电信号（ 208）。光束的剩余部分从位于机翼上的后向反射器靶（700）反射回到另一光电检测器（114）中以提供目标电信号（209）。两个放大的电信号在相位检测器（图3）中进行比较，以提供角度测量输出信号E0。

5. 发明授权

US06662548B1 Jet blade ejector nozzle 有权
标题翻译：喷枪喷嘴
公开(公告)号：US06662548B1
公开(公告)日：2003-12-16
申请号：US09671870
申请日：2000-09-27
申请人： Larry T. Clark
发明人： Larry T. Clark
IPC分类号： F02K302
CPC分类号： F02K1/386 , F02K1/40 , Y02T50/671
摘要： A jet engine assembly having a jet engine and an unsteady flow ejector. The unsteady flow ejector segregates the exhaust flow from the jet engine into a plurality of rotating high velocity, low density jets and a plurality of rotating low pressure voids. The low pressure voids are employed to entrain at least a portion of a secondary flow of air which is mixed with the jets to produce a mixed flow having a relatively higher flow rate and a relatively lower velocity than the exhaust flow. A method for attenuating the noise that is produced by the exhaust flow of a jet engine is also provided.
摘要翻译：具有喷气发动机和不稳定流动喷射器的喷气发动机组件。不稳定流动喷射器将来自喷气发动机的排气流分离成多个旋转的高速，低密度射流和多个旋转的低压空隙。使用低压空隙来夹带与喷流混合的二次空气流的一部分以产生具有比排气流更高流速和相对较低速度的混合流。还提供了一种用于衰减由喷气发动机的排气流产生的噪声的方法。

6. 发明授权

US5884843A Engine noise suppression ejector nozzle 失效
标题翻译：发动机噪音抑制喷射器喷嘴
公开(公告)号：US5884843A
公开(公告)日：1999-03-23
申请号：US743105
申请日：1996-11-04
申请人： Gary L. Lidstone , Larry T. Clark , Imre A. Szupkay , David L. Sandquist
发明人： Gary L. Lidstone , Larry T. Clark , Imre A. Szupkay , David L. Sandquist
IPC分类号： F02K1/34 , F02K1/36
CPC分类号： F02K1/36 , F02K1/34 , Y02T50/672
摘要： A moderately high bypass ratio turbofan engine nozzle (36) is provided including an outer structure (46) and one or more ejectors (38). The ejectors (38) include inner and outer doors (82), (80) for closing off an ejector passage (76) extending through the outer structure (46). The ejectors (38) are sized to entrain exterior air (40) at aspiration ratios of generally less than 60%. The exterior air (40) is mixed with engine exhaust (42), resulting in a lower combined airflow velocity which in turn reduces jet exhaust noise. Mixing components formed as turning vanes (108) are located in the ejector passage (76) for encouraging further mixing of the airflows (40), (42). In preferred embodiments, the nozzle (36) further includes a translatable centerbody (52), an aft flap assembly (112), and a control system (122) for controlling the movements of the nozzle components. A method of suppressing aircraft moderately high bypass ratio turbofan engine exhaust noise including entraining exterior air to engine exhaust at an aspiration ratio of less than about 60%.
摘要翻译：提供了一种适度高的旁路比涡轮风扇发动机喷嘴（36），其包括外部结构（46）和一个或多个喷射器（38）。喷射器（38）包括用于封闭延伸穿过外部结构（46）的喷射器通道（76）的内门和外门（82），（80）。喷射器（38）的尺寸设定成以通常小于60％的吸气比夹带外部空气（40）。外部空气（40）与发动机排气（42）混合，导致较低的组合气流速度，这又降低喷射排气噪声。形成为转动叶片（108）的混合部件位于喷射器通道（76）中，用于鼓励气流（40），（42）的进一步混合。在优选实施例中，喷嘴（36）还包括可平移的中心体（52），后翼片组件（112）和用于控制喷嘴部件运动的控制系统（122）。一种抑制飞机适度高旁通比的涡轮风扇发动机排气噪声的方法，包括以小于约60％的吸气比将外部空气引入发动机排气。

7. 发明授权

US5149018A Cooling system for a hypersonic aircraft 失效
标题翻译：超音速飞机的冷却系统
公开(公告)号：US5149018A
公开(公告)日：1992-09-22
申请号：US525888
申请日：1990-05-17
申请人： Larry T. Clark
发明人： Larry T. Clark
IPC分类号： B64C1/38
CPC分类号： B64C1/38 , Y10S165/908 , Y10S60/912
摘要： A cooling system for a hypersonic aircraft is disclosed which enables hypersonic flight using non-cryogenic fuels. The cooling system positions a primary heat exchanger at an external location on the aircraft which remains relatively cool during hypersonic flight. A working fluid is passed through the primary heat exchanger to the hot parts of a supersonic combustion ram jet engine.
摘要翻译：公开了一种用于超音速飞行器的冷却系统，其使用非低温燃料实现超音速飞行。冷却系统将主热交换器定位在飞机上的外部位置，在超音速飞行期间保持相对凉爽。工作流体通过主热交换器到超音速燃烧柱塞喷气发动机的热部分。

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