公开(公告)号：US07861968B2

公开(公告)日：2011-01-04

申请号：US11553170

申请日：2006-10-26

申请人： Pradip G. Parikh ,  Robert H. Willie

发明人： Pradip G. Parikh ,  Robert H. Willie

IPC分类号： B64D11/00

CPC分类号： B64D13/00 ,  B64D33/08 ,  B64D2013/0622 ,  B64D2033/0226 ,  B64D2241/00 ,  Y02T50/56 ,  Y10T137/0536

摘要： An inlet apparatus and method for use with a cabin air compressor on a high speed, airborne mobile platform, such as a commercial or military aircraft. The apparatus includes a Pitot inlet of a desired shape that is supported outside an exterior surface of a fuselage of the aircraft by a diverter structure. The diverter structure diverts a low energy portion of a boundary layer so that the low energy portion does not enter the Pitot inlet. The Pitot inlet receives the higher energy portion of the boundary layer and channels a ram airflow to an inlet of a cabin air compressor. The apparatus provides a recovery factor (RF) of at least about 0.8 at a cabin air compressor (CAC) inlet face, which keeps the electric power required to drive the CAC within available power limits, while minimizing the drag of the inlet apparatus.

摘要翻译： 一种用于在高速，机载移动平台（如商用或军用飞机）上的机舱空气压缩机的入口装置和方法。 该装置包括一个所需形状的皮托特入口，该导入口通过分流器结构支撑在飞行器的机身的外表面外部。 分流器结构转移边界层的低能量部分，使得低能量部分不进入皮托特入口。 皮托特入口接收边界层的较高能量部分，并将冲压气流引导到机舱空气压缩机的入口。 该设备在机舱空气压缩机（CAC）入口面处提供至少约0.8的恢复因子（RF），其保持将CAC驱动到可用功率限制内所需的电力，同时最小化入口设备的阻力。

公开(公告)号：US07618006B2

公开(公告)日：2009-11-17

申请号：US11599245

申请日：2006-11-13

申请人： Pradip G. Parikh ,  E. Dale Hastings

发明人： Pradip G. Parikh ,  E. Dale Hastings

IPC分类号： B64D33/02

CPC分类号： B64D13/00 ,  B64D33/02 ,  Y02T50/44 ,  Y10T137/0536

摘要： Ram air inlets for use with aircraft environmental control systems and other aircraft and non-aircraft systems are described herein. In one embodiment, a ram air inlet configured in accordance with the present invention includes an inlet lip spaced apart from an inlet housing. An inlet door is moveably attached to the inlet housing, and includes a first surface portion, a second surface portion, and a transition region extending between the first and second surface portions. The first surface portion is moveably positioned at least approximately forward of the inlet lip. The second surface portion is fixed at an angle relative to the first surface portion, and is moveably positioned at least approximately aft of the inlet lip. The transition region is positioned at least approximately adjacent to the inlet lip to form an inlet opening therebetween. Movement of the inlet door in a first direction reduces the size of the inlet opening to thereby decrease the flow of ram air through the inlet. Conversely, movement of the inlet door in a second direction enlarges the inlet opening to increase the flow of ram air through the inlet.

摘要翻译： 本文描述了用于飞机环境控制系统和其他飞机和非飞机系统的Ram空气入口。 在一个实施例中，根据本发明配置的冲压空气入口包括与入口壳体间隔开的入口唇缘。 入口门可移动地附接到入口壳体，并且包括第一表面部分，第二表面部分和在第一和第二表面部分之间延伸的过渡区域。 第一表面部分可移动地至少位于入口唇缘的前方。 第二表面部分相对于第一表面部分以一定角度固定，并且可移动地定位在入口唇缘的至少近似后方。 过渡区至少与入口唇缘相邻，以形成入口之间的入口。 入口门在第一方向上的运动减小了入口的尺寸，从而减小了通过入口的冲压空气的流动。 相反，入口门在第二方向上的移动增加了入口开口，以增加冲压空气通过入口的流动。

公开(公告)号：US20090212165A1

公开(公告)日：2009-08-27

申请号：US11763569

申请日：2007-06-15

申请人： Pradip G. Parikh

发明人： Pradip G. Parikh

IPC分类号： B64C21/06 ,  F16K31/04

CPC分类号： B64C21/06 ,  B64C2230/20 ,  B64C2230/22 ,  Y02T50/166 ,  Y10T137/1842

摘要： Passive removal of suction air for producing a laminar flow, and associated systems and methods are disclosed. One such method includes forming a laminar flow region over an external surface of an aircraft by drawing air through the external surface and into a plenum. The method can further include passively directing the air from the plenum overboard the aircraft. For example, the air can be passively directed to a region external to the aircraft having a static pressure lower than a static pressure in the plenum, as a result of the motion of the aircraft. Flows from different sections of the external surface can be combined in a common plenum, and the corresponding massflow rates can be controlled by the local porosity of the external surface.

摘要翻译： 公开了用于产生层流的吸入空气的被动去除以及相关的系统和方法。 一种这样的方法包括通过将空气抽吸通过外表面并进入增压室而在飞行器的外表面上形成层流区域。 该方法还可以进一步包括被动地引导来自空中的空气在飞机上。 例如，作为飞行器的运动的结果，空气可以被动地定向到具有低于静压力的静压力的飞行器外部的区域。 来自外表面的不同部分的流动可以组合在共同的气室中，相应的质量流量可以通过外表面的局部孔隙度来控制。

公开(公告)号：US07866609B2

公开(公告)日：2011-01-11

申请号：US11763569

申请日：2007-06-15

申请人： Pradip G. Parikh

发明人： Pradip G. Parikh

IPC分类号： B64C21/06

CPC分类号： B64C21/06 ,  B64C2230/20 ,  B64C2230/22 ,  Y02T50/166 ,  Y10T137/1842

摘要： Passive removal of suction air for producing a laminar flow, and associated systems and methods are disclosed. One such method includes forming a laminar flow region over an external surface of an aircraft by drawing air through the external surface and into a plenum. The method can further include passively directing the air from the plenum overboard the aircraft. For example, the air can be passively directed to a region external to the aircraft having a static pressure lower than a static pressure in the plenum, as a result of the motion of the aircraft. Flows from different sections of the external surface can be combined in a common plenum, and the corresponding massflow rates can be controlled by the local porosity of the external surface.

摘要翻译： 公开了用于产生层流的吸入空气的被动去除以及相关的系统和方法。 一种这样的方法包括通过将空气抽吸通过外表面并进入增压室而在飞行器的外表面上形成层流区域。 该方法还可以进一步包括被动地引导来自空中的空气在飞机上。 例如，作为飞行器的运动的结果，空气可以被动地定向到具有低于静压力的静压力的飞行器外部的区域。 来自外表面的不同部分的流动可以组合在共同的气室中，相应的质量流量可以通过外表面的局部孔隙度来控制。

公开(公告)号：US07849702B2

公开(公告)日：2010-12-14

申请号：US11765748

申请日：2007-06-20

申请人： Pradip G. Parikh

发明人： Pradip G. Parikh

IPC分类号： B60H1/32 ,  F25D9/00 ,  B64D33/02

CPC分类号： B64D13/00 ,  B64D2241/00 ,  Y02T50/44 ,  Y02T50/54 ,  Y02T50/56

摘要： Aircraft environmental control systems having a single ram air inlet providing air to both cabin air compressors and associated heat exchangers are disclosed herein. In one embodiment, and environmental control system for use with an aircraft includes a ram air inlet, an air conditioning pack, and an associated heat exchanger. In this embodiment, the ram air inlet provides a first portion of air to the air conditioning pack, and a second portion of air to the associated heat exchanger. The first portion of air flows from the air conditioning pack and through the heat exchanger before flowing into an aircraft cabin. The second portion of air from the ram air inlet cools the first portion of air in the heat exchanger before exiting the aircraft through a ram air outlet. The inlet and outlet can be modulated on an optimized schedule to minimize the net drag of the ram system.

摘要翻译： 本文公开了具有向舱室空气压缩机和相关热交换器提供空气的单个冲压空气入口的飞行器环境控制系统。 在一个实施例中，与飞行器一起使用的环境控制系统包括冲压空气入口，空调组件和相关联的热交换器。 在该实施例中，冲压空气入口将空气的第一部分提供给空调组件，并将空气的第二部分提供给相关联的热交换器。 第一部分的空气在流入飞机机舱之前从空气调节组件流过热交换器。 来自冲压空气入口的空气的第二部分在离开飞行器之前通过冲压空气出口冷却热交换器中的第一部分空气。 入口和出口可以按照优化的时间表进行调节，以最小化压头系统的净阻力。

公开(公告)号：US07624944B2

公开(公告)日：2009-12-01

申请号：US11553181

申请日：2006-10-26

申请人： Pradip G Parikh ,  Warren A Atkey

发明人： Pradip G Parikh ,  Warren A Atkey

IPC分类号： B64D33/02

CPC分类号： B64D13/02 ,  B64C21/00 ,  B64D13/06 ,  B64D2013/0618 ,  B64D2013/0622 ,  B64D2033/0226 ,  B64D2241/00 ,  Y02T50/166 ,  Y02T50/56 ,  Y10T137/0536

摘要： A tandem inlet apparatus for use with a high speed mobile platform, for example a commercial or military aircraft. The tandem inlet apparatus includes a Pitot inlet for feeding air to a cabin air compressor (CAC) of an air conditioning pack carried on the mobile platform. A flush heat exchanger inlet is disposed forwardly of the Pitot inlet and longitudinally aligned with the Pitot inlet, for supplying cooling air to a heat exchanger of the air conditioning pack. By locating the heat exchanger inlet forwardly and longitudinally in line with the Pitot inlet, the heat exchanger inlet is able to effectively swallow a large portion of the boundary layer, which results in a thinner boundary layer at the inlet face of the Pitot inlet. This enables a smaller throat area Pitot inlet to be used, as well as a shorter diverter height to be employed with the Pitot inlet, while still realizing an improved recovery factor (RF) performance with the Pitot inlet. The reduced height Pitot inlet also enables drag to be reduced.

摘要翻译： 一种与高速移动平台（例如商用或军用飞机）一起使用的串联入口装置。 串联入口设备包括皮托特入口，用于将空气供给到在移动平台上承载的空调包的客舱空气压缩机（CAC）。 冲洗式热交换器入口设置在皮托特入口的前方并与皮托特入口纵向对准，以将冷却空气供应到空调包装的热交换器。 通过将热交换器入口向前和纵向设置为与皮托特入口一致，热交换器入口能够有效地吞下边界层的大部分，这导致在皮托特入口的入口面处更薄的边界层。 这使得能够使用较小的喉部区域Pitot入口，以及与皮托特入口一起使用的更短的分流器高度，同时仍然使用皮托特入口实现改进的恢复因子（RF）性能。 减小的皮托托入口也可以减少拖曳。

公开(公告)号：US5772156A

公开(公告)日：1998-06-30

申请号：US566584

申请日：1995-11-30

申请人： Pradip G. Parikh ,  Frank D. Neumann

发明人： Pradip G. Parikh ,  Frank D. Neumann

IPC分类号： B64C21/02 ,  B64C21/06

CPC分类号： B64C21/025 ,  B64C2230/04 ,  B64C2230/22 ,  Y02T50/166

摘要： An improvement to boundary layer control system, including a transpiration panel (58) for transpiring suction air in a distributed manner, is provided. The transpiration panel (58) replaces the discharge nozzle of prior art flow control systems. The transpiration panel (58) is generally a rigid panel having a plurality of small holes (62) extending from an inner panel surface (56) to a smooth outer panel surface (54). The transpiration panel (58) is positioned flush with an external aircraft surface in a region where laminar flow control is not being attempted. Exemplary subsonic and supersonic boundary layer control systems including the transpiration panel (58) are provided. A preferred location of the transpiration panel (58) for the subsonic application is the underside of a wing (80), near the leading edge. A preferred location of the transpiration panel (58) for the supersonic application including on the upper surface of a wing (114) near the fuselage (118), in a turbulent wedge region.

摘要翻译： 提供了边界层控制系统的改进，包括用于以分布式方式蒸发吸入空气的蒸腾面板（58）。 蒸腾面板（58）代替现有技术的流量控制系统的排放喷嘴。 蒸腾面板（58）通常是具有从内面板表面（56）延伸到光滑的外面板表面（54）的多个小孔（62）的刚性面板。 蒸腾面板（58）在没有尝试层流控制的区域内与外部飞机表面齐平。 提供了包括蒸腾面板（58）的示例性亚音速和超音速边界层控制系统。 用于亚音速应用的蒸腾面板（58）的优选位置是在前缘附近的翼（80）的下侧。 用于超音速应用的蒸腾面板（58）的优选位置包括在机身（118）附近的机翼（114）的上表面上，处于紊流楔形区域。

公开(公告)号：US20080099631A1

公开(公告)日：2008-05-01

申请号：US11553181

申请日：2006-10-26

申请人： Pradip G. Parikh ,  Warren A. Atkey

发明人： Pradip G. Parikh ,  Warren A. Atkey

IPC分类号： B64D33/00

CPC分类号： B64D13/02 ,  B64C21/00 ,  B64D13/06 ,  B64D2013/0618 ,  B64D2013/0622 ,  B64D2033/0226 ,  B64D2241/00 ,  Y02T50/166 ,  Y02T50/56 ,  Y10T137/0536

摘要： A tandem inlet apparatus for use with a high speed mobile platform, for example a commercial or military aircraft. The tandem inlet apparatus includes a Pitot inlet for feeding air to a cabin air compressor (CAC) of an air conditioning pack carried on the mobile platform. A flush heat exchanger inlet is disposed forwardly of the Pitot inlet and longitudinally aligned with the Pitot inlet, for supplying cooling air to a heat exchanger of the air conditioning pack. By locating the heat exchanger inlet forwardly and longitudinally in line with the Pitot inlet, the heat exchanger inlet is able to effectively swallow a large portion of the boundary layer, which results in a thinner boundary layer at the inlet face of the Pitot inlet. This enables a smaller throat area Pitot inlet to be used, as well as a shorter diverter height to be employed with the Pitot inlet, while still realizing an improved recovery factor (RF) performance with the Pitot inlet. The reduced height Pitot inlet also enables drag to be reduced.

摘要翻译： 一种与高速移动平台（例如商用或军用飞机）一起使用的串联入口装置。 串联入口设备包括皮托特入口，用于将空气供给到在移动平台上承载的空调包的客舱空气压缩机（CAC）。 冲洗式热交换器入口设置在皮托特入口的前方并与皮托特入口纵向对准，以将冷却空气供应到空调包装的热交换器。 通过将热交换器入口向前和纵向设置为与皮托特入口一致，热交换器入口能够有效地吞下边界层的大部分，这导致在皮托特入口的入口面处更薄的边界层。 这使得能够使用较小的喉部区域Pitot入口，以及与皮托特入口一起使用的更短的分流器高度，同时仍然使用皮托特入口实现改进的恢复因子（RF）性能。 减小的皮托托入口也可以减少拖曳。

公开(公告)号：US20080099630A1

公开(公告)日：2008-05-01

申请号：US11553170

申请日：2006-10-26

申请人： Pradip G. Parikh ,  Robert H. Willie

发明人： Pradip G. Parikh ,  Robert H. Willie

IPC分类号： B64D33/00

CPC分类号： B64D13/00 ,  B64D33/08 ,  B64D2013/0622 ,  B64D2033/0226 ,  B64D2241/00 ,  Y02T50/56 ,  Y10T137/0536

摘要： An inlet apparatus and method for use with a cabin air compressor on a high speed, airborne mobile platform, such as a commercial or military aircraft. The apparatus includes a Pitot inlet of a desired shape that is supported outside an exterior surface of a fuselage of the aircraft by a diverter structure. The diverter structure diverts a low energy portion of a boundary layer so that the low energy portion does not enter the Pitot inlet. The Pitot inlet receives the higher energy portion of the boundary layer and channels a ram airflow to an inlet of a cabin air compressor. The apparatus provides a recovery factor (RF) of at least about 0.8 at a cabin air compressor (CAC) inlet face, which keeps the electric power required to drive the CAC within available power limits, while minimizing the drag of the inlet apparatus.

摘要翻译： 一种用于在高速，机载移动平台（如商用或军用飞机）上的机舱空气压缩机的入口装置和方法。 该装置包括一个所需形状的皮托特入口，该导入口通过分流器结构支撑在飞行器的机身的外表面外部。 分流器结构转移边界层的低能量部分，使得低能量部分不进入皮托特入口。 皮托特入口接收边界层的较高能量部分，并将冲压气流引导到机舱空气压缩机的入口。 该设备在机舱空气压缩机（CAC）入口面处提供至少约0.8的恢复因子（RF），其保持将CAC驱动到可用功率限制内所需的电力，同时最小化入口设备的阻力。

公开(公告)号：US20080314060A1

公开(公告)日：2008-12-25

申请号：US11765748

申请日：2007-06-20

申请人： Pradip G. Parikh

发明人： Pradip G. Parikh

IPC分类号： B60H1/32

CPC分类号： B64D13/00 ,  B64D2241/00 ,  Y02T50/44 ,  Y02T50/54 ,  Y02T50/56

摘要： Aircraft environmental control systems having a single ram air inlet providing air to both cabin air compressors and associated heat exchangers are disclosed herein. In one embodiment, and environmental control system for use with an aircraft includes a ram air inlet, an air conditioning pack, and an associated heat exchanger. In this embodiment, the ram air inlet provides a first portion of air to the air conditioning pack, and a second portion of air to the associated heat exchanger. The first portion of air flows from the air conditioning pack and through the heat exchanger before flowing into an aircraft cabin. The second portion of air from the ram air inlet cools the first portion of air in the heat exchanger before exiting the aircraft through a ram air outlet. The inlet and outlet can be modulated on an optimized schedule to minimize the net drag of the ram system.

摘要翻译： 本文公开了具有向舱室空气压缩机和相关热交换器提供空气的单个冲压空气入口的飞行器环境控制系统。 在一个实施例中，与飞行器一起使用的环境控制系统包括冲压空气入口，空调组件和相关联的热交换器。 在该实施例中，冲压空气入口将空气的第一部分提供给空调组件，并将空气的第二部分提供给相关联的热交换器。 第一部分的空气在流入飞机机舱之前从空气调节组件流过热交换器。 来自冲压空气入口的空气的第二部分在离开飞行器之前通过冲压空气出口冷却热交换器中的第一部分空气。 入口和出口可以按照优化的时间表进行调节，以最小化压头系统的净阻力。