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公开(公告)号：US5703593A
公开(公告)日：1997-12-30
申请号：US571001
申请日：1995-12-12
IPC分类号： G01S13/44 , G01S13/524 , G01S13/72 , G01S13/534
CPC分类号： G01S13/4472 , G01S13/5242 , G01S13/449 , G01S13/5244 , G01S13/726
摘要： An ADPCA subsystem includes a weight processor for weighting the delta channel signal according to the results of an adaptive algorithm to which the output of a DPCA vector combiner is input. An AMTI vector combiner is connected to the output of the DPCA vector combiner to form the filter output. The delta channel signal is time delayed and samples of the delta channel signal are collected by the processor together with a sum channel sample and a residue sample, in order to apply the proper weights to the undelayed and delayed delta channel samples. The output of the ADPCA weight processor therefore provides an optimum correction signal to the vector combiner.
摘要翻译： ADPCA子系统包括权重处理器，用于根据输入DPCA矢量组合器的输出的自适应算法的结果对增量信道信号进行加权。 AMTI矢量组合器连接到DPCA矢量组合器的输出端以形成滤波器输出。 Δ信道信号是时间延迟的，并且Δ信道信号的样本由处理器与和信道样本和残差采样一起收集，以便将适当的权重应用于未延迟和延迟的三角形信道样本。 因此，ADPCA加权处理器的输出为矢量组合器提供最佳校正信号。
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公开(公告)号：US07611093B2
公开(公告)日：2009-11-03
申请号：US11829497
申请日：2007-07-27
IPC分类号： B64D41/00
CPC分类号： F02C7/04 , B64D41/00 , B64D2033/0213 , B64D2041/002 , F02C6/06 , F02C7/042 , Y02T50/44 , Y02T50/671 , Y10T137/0536
摘要： Dual flow auxiliary power unit (APU) inlets and associated systems and methods are disclosed. An inlet in accordance with one embodiment of the invention includes an entrance aperture and a divider positioned in the inlet and located to separate a first portion of the inlet from a second portion of the inlet. The first portion can be configured to couple to an engine air intake of an APU, and the second portion can be configured to direct air away from the air intake. The divider can be positioned to direct air having a first total pressure level and a first distortion level to the first portion of the inlet, and direct air having a second total pressure level and second distortion level to the second portion of the inlet. The first total pressure level can be approximately the same as or higher than the second total pressure level, or the second distortion level can be approximately the same as or higher than the first distortion level, or both.
摘要翻译： 公开了双流辅助动力单元（APU）入口及相关系统和方法。 根据本发明的一个实施例的入口包括入口孔和分隔件，其定位在入口中并且定位成将入口的第一部分与入口的第二部分分开。 第一部分可以被配置成联接到APU的发动机进气口，并且第二部分可被配置成将空气引导离开进气口。 分隔器可以定位成将具有第一总压力水平和第一失真水平的空气引导到入口的第一部分，并且具有第二总压力水平和第二失真水平的直接空气到入口的第二部分。 第一总压力水平可以大致等于或高于第二总压力水平，或者第二失真水平可以大致等于或高于第一失真水平，或两者。
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3.发明申请AUTOMATIC CONTROL SYSTEMS FOR AIRCRAFT AUXILIARY POWER UNITS, AND ASSOCIATED METHODS 有权飞机辅助动力单位自动控制系统及相关方法公开(公告)号：US20110127372A1
公开(公告)日：2011-06-02
申请号：US13021422
申请日：2011-02-04
IPC分类号： B64D41/00
CPC分类号： B64D41/00 , B64D2041/002 , B64D2221/00
摘要： Systems and methods for operating aircraft power systems are disclosed. A power system in accordance with one embodiment of the invention includes an aircraft auxiliary power unit and a controller coupled to the aircraft auxiliary power unit, with the controller being configured to automatically stop the auxiliary power unit while the auxiliary power unit is functioning normally. The controller can also be configured to automatically start the auxiliary power unit in-flight when power supplied or expected to be supplied to a subsystem of the aircraft has a non-zero value at or below a threshold value. The controller may also be configured to start the auxiliary power unit when a load or expected load on the subsystem meets or exceeds a threshold value.
摘要翻译： 公开了用于操作飞机动力系统的系统和方法。 根据本发明的一个实施例的电力系统包括飞行器辅助动力单元和耦合到飞行器辅助动力单元的控制器，其中控制器被配置为在辅助动力单元正常运行时自动停止辅助动力单元。 控制器还可以被配置为在供电或期望提供给飞行器的子系统的电源具有等于或小于阈值的非零值时，在飞行中自动启动辅助电源单元。 控制器还可以被配置为在子系统上的负载或预期负载满足或超过阈值时启动辅助电源单元。
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公开(公告)号：US07513119B2
公开(公告)日：2009-04-07
申请号：US11051272
申请日：2005-02-03
申请人： Edward Zielinski , Alan T. Bernier , Kent W. Knechtel , Thomas A. Campbell , Jeffrey J. White , Mark D. Ralston
发明人： Edward Zielinski , Alan T. Bernier , Kent W. Knechtel , Thomas A. Campbell , Jeffrey J. White , Mark D. Ralston
CPC分类号： F02C7/262 , F02C7/268 , F02C7/275 , F02C7/277 , F05D2220/76 , F05D2220/764 , Y02T50/671
摘要： Methods and systems for starting aircraft turbofan engines are disclosed. A system in accordance with one embodiment includes an electrically-powered starter motor coupled to a turbofan engine to provide power to the turbofan engine during an engine start procedure. The system can further include an on-board, deployable, ram air driven turbine coupled to an electrical generator, which is in turn coupled to the starter motor to provide electrical power to the starter motor. In other embodiments, the ram air driven turbine can be replaced with a fuel cell or a battery. In still further embodiments, a single controller can control operation of both the engine starter and other motors of the aircraft.
摘要翻译： 公开了用于启动飞机涡扇发动机的方法和系统。 根据一个实施例的系统包括耦合到涡轮风扇发动机的电动起动马达，以在发动机起动过程期间向涡轮风扇发动机提供动力。 该系统还可以包括联接到发电机的机载可部署的冲压空气驱动的涡轮机，该发电机又连接到起动马达以向起动马达提供电力。 在其他实施例中，冲压空气驱动涡轮机可以用燃料电池或电池代替。 在另外的实施例中，单个控制器可以控制飞行器的发动机起动器和其它马达的操作。
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5.发明授权Automatic control systems for aircraft auxiliary power units, and associated methods 有权飞机辅助动力装置自动控制系统及相关方法公开(公告)号：US08061650B2
公开(公告)日：2011-11-22
申请号：US13021422
申请日：2011-02-04
CPC分类号： B64D41/00 , B64D2041/002 , B64D2221/00
摘要： Systems and methods for operating aircraft power systems are disclosed. A power system in accordance with one embodiment of the invention includes an aircraft auxiliary power unit and a controller coupled to the aircraft auxiliary power unit, with the controller being configured to automatically stop the auxiliary power unit while the auxiliary power unit is functioning normally. The controller can also be configured to automatically start the auxiliary power unit in-flight when power supplied or expected to be supplied to a subsystem of the aircraft has a non-zero value at or below a threshold value. The controller may also be configured to start the auxiliary power unit when a load or expected load on the subsystem meets or exceeds a threshold value.
摘要翻译： 公开了用于操作飞机动力系统的系统和方法。 根据本发明的一个实施例的电力系统包括飞行器辅助动力单元和耦合到飞行器辅助动力单元的控制器，其中控制器被配置为在辅助动力单元正常运行时自动停止辅助动力单元。 控制器还可以被配置为在供电或期望提供给飞行器的子系统的电源具有等于或小于阈值的非零值时，在飞行中自动启动辅助电源单元。 控制器还可以被配置为在子系统上的负载或预期负载满足或超过阈值时启动辅助电源单元。
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公开(公告)号：US20080179466A1
公开(公告)日：2008-07-31
申请号：US11829497
申请日：2007-07-27
CPC分类号： F02C7/04 , B64D41/00 , B64D2033/0213 , B64D2041/002 , F02C6/06 , F02C7/042 , Y02T50/44 , Y02T50/671 , Y10T137/0536
摘要： Dual flow auxiliary power unit (APU) inlets and associated systems and methods are disclosed. An inlet in accordance with one embodiment of the invention includes an entrance aperture and a divider positioned in the inlet and located to separate a first portion of the inlet from a second portion of the inlet. The first portion can be configured to couple to an engine air intake of an APU, and the second portion can be configured to direct air away from the air intake. The divider can be positioned to direct air having a first total pressure level and a first distortion level to the first portion of the inlet, and direct air having a second total pressure level and second distortion level to the second portion of the inlet. The first total pressure level can be approximately the same as or higher than the second total pressure level, or the second distortion level can be approximately the same as or higher than the first distortion level, or both.
摘要翻译： 公开了双流辅助动力单元（APU）入口及相关系统和方法。 根据本发明的一个实施例的入口包括入口孔和分隔件，其定位在入口中并且定位成将入口的第一部分与入口的第二部分分开。 第一部分可以被配置成联接到APU的发动机进气口，并且第二部分可被配置成将空气引导离开进气口。 分隔器可以定位成将具有第一总压力水平和第一失真水平的空气引导到入口的第一部分，并且具有第二总压力水平和第二失真水平的直接空气到入口的第二部分。 第一总压力水平可以大致等于或高于第二总压力水平，或者第二失真水平可以大致等于或高于第一失真水平，或两者。
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公开(公告)号：US07210653B2
公开(公告)日：2007-05-01
申请号：US10691440
申请日：2003-10-21
申请人： Warren A. Atkey , Alan T. Bernier , Michael D. Bowman , Thomas A. Campbell , Jonathan M. Cruse , Charles J. Fiterman , Charles S. Meis , Casey Y. K. Ng , Farhad Nozari , Edward Zielinski
发明人： Warren A. Atkey , Alan T. Bernier , Michael D. Bowman , Thomas A. Campbell , Jonathan M. Cruse , Charles J. Fiterman , Charles S. Meis , Casey Y. K. Ng , Farhad Nozari , Edward Zielinski
IPC分类号： B64D41/00
CPC分类号： B64D13/08 , B64D13/06 , B64D41/00 , B64D2013/0611 , B64D2013/064 , B64D2013/0644 , B64D2041/005 , B64D2221/00 , Y02T50/44 , Y02T50/53 , Y02T50/56 , Y02T90/36
摘要： Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet engine. The jet engine can be configured to provide propulsive thrust to the aircraft, and the electric generator can be configured to receive shaft power from the jet engine. The environmental control system can be configured to provide outside air to a passenger cabin of the aircraft in the absence of bleed air from the jet engine.
摘要翻译： 为飞机系统提供次级电源的方法和系统。 在一个实施例中，用于向环境控制系统提供动力的飞机系统架构包括可操作地联接到喷气发动机的发电机。 喷气发动机可以被配置成向飞行器提供推进推力，并且发电机可被配置成从喷气发动机接收轴功率。 环境控制系统可以被配置为在没有来自喷气发动机的排放空气的情况下向飞行器的客舱提供外部空气。
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8.发明授权Passive cooling device and method for cooling an auxiliary power unit on an airplane 失效被动冷却装置和用于冷却飞机上的辅助动力装置的方法
公开(公告)号：US5655359A
公开(公告)日：1997-08-12
申请号：US441467
申请日：1995-05-15
CPC分类号： B64D41/00 , B64D33/02 , B64D33/08 , F02C7/14 , B64D2033/0213 , B64D2041/002 , F05D2260/601 , Y02T50/675
摘要： A passive cooling system for aircraft auxiliary power units having an intake duct extending between an inlet opening and the compartment in which the auxiliary power unit is positioned. An inlet scoop is positioned in the intake duct for diverting a portion of the airflow in the intake duct through an outlet in a wall of the intake duct. A vacuum duct is positioned near an oil cooler for the auxiliary power unit, and an aspirator is operatively positioned between the vacuum duct and an exhaust passage of the auxiliary power unit. The aspirator creates a low-pressure region in the vacuum duct that draws the diverted air out of the outlet and through the oil cooler.
摘要翻译： 一种用于飞机辅助动力装置的被动冷却系统，其具有在入口开口和辅助动力单元所在的隔室之间延伸的进气管道。 入口勺定位在进气管道中，用于通过进气管道的壁中的出口将进气管道中的气流的一部分转向。 真空管道位于用于辅助动力单元的油冷却器附近，并且吸气器可操作地定位在真空管道和辅助动力单元的排气通道之间。 吸气器在真空管道中产生低压区域，其将转移的空气从出口抽出并通过油冷却器。
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公开(公告)号：US08798722B2
公开(公告)日：2014-08-05
申请号：US13203800
申请日：2010-03-01
IPC分类号： A61B5/00
CPC分类号： A61B18/203 , A61B5/0059 , A61B5/0066 , A61B5/0084 , A61B5/411 , A61B5/442 , A61B5/444 , A61B5/685 , A61B2018/00452 , A61N5/0616 , A61N2005/0631 , A61N2005/067 , G02B6/032 , G02B6/06 , G02B6/262
摘要： The present invention relates to the field of optical imaging and therapeutics. More particularly, embodiments of the present invention provide minimally-invasive Fiberoptic Microneedle Devices (FMDs) for light-based therapeutics, which physically penetrate tissue and deliver light directly into the target area below the skin surface (FIG. 1). A preferred embodiment of the invention is a fiberoptic microneedle device comprising: (a) one or more silica-based needles capable of guiding light and comprising a length of about 0.5-6 mm, a base having an outer diameter in the range of about 100-150 micron, and a tip having an outer diameter in the range of about 5-20 micron; (b) a support member to which the needles are secured; (c) a ferrule comprising one or more holes for each of the needles, wherein the ferrule is operably configured to provide mechanical support to each needle at all or some portion of the length of the needle. Embodiments of the invention enable depth-selective and deep photothermal therapeutics and can be adapted for use with any laser-based treatment or diagnostic in which light is used to detect or treat targets under or on the skin surface.
摘要翻译： 本发明涉及光学成像和治疗学领域。 更具体地说，本发明的实施例提供了用于基于光的治疗剂的微创光纤微针装置（FMD），其物理地穿透组织并将光直接传送到皮肤表面下方的目标区域（图1）。 本发明的优选实施例是一种光纤微针装置，包括：（a）一个或多个能够引导光并且包括约0.5-6mm的长度的基于二氧化硅的针，具有约100的外径的基部 -150微米，以及外径在约5-20微米范围内的尖端; （b）固定针的支撑构件; （c）套圈，其包括用于每个针的一个或多个孔，其中所述套圈可操作地构造成在所述针的所述长度的全部或某一部分处为每个针提供机械支撑。 本发明的实施方案可实现深度选择性和深度光热治疗剂，并且可适用于任何基于激光的治疗或诊断，其中光用于检测或治疗皮肤表面下或皮肤表面上的靶标。
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公开(公告)号：US07891605B2
公开(公告)日：2011-02-22
申请号：US12047833
申请日：2008-03-13
CPC分类号： B64D41/00 , B64D2041/002 , B64D2221/00
摘要： Systems and methods for operating aircraft power systems are disclosed. A power system in accordance with one embodiment of the invention includes an aircraft auxiliary power unit and a controller coupled to the aircraft auxiliary power unit, with the controller being configured to automatically stop the auxiliary power unit while the auxiliary power unit is functioning normally. The controller can also be configured to automatically start the auxiliary power unit in-flight when power supplied or expected to be supplied to a subsystem of the aircraft has a non-zero value at or below a threshold value. The controller may also be configured to start the auxiliary power unit when a load or expected load on the subsystem meets or exceeds a threshold value.
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