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1.发明授权公开(公告)号：US07607318B2
公开(公告)日：2009-10-27
申请号：US11440486
申请日：2006-05-25
IPC分类号： F25D9/00
CPC分类号： B64D13/06 , B64D2013/0611 , B64D2013/0688 , Y02T50/44 , Y02T50/56
摘要： An integrated environmental control system for an aircraft compartment and aircraft power system comprises first and second air compressors, an auxiliary power unit, and first and second environmental control systems. The first and second compressors receive and compress airflow from the aircraft exterior. The auxiliary power unit comprises a first shaft rotatably mounting a power turbine, a third air compressor to compress airflow from the aircraft exterior, and a first cooling turbine to cool the airflow. Each environmental control system comprises a first heat exchanger, a recycling heat exchanger, and a second shaft rotatably mounting a fourth compressor and a second cooling turbine for compressing and cooling the airflow. The first heat exchanger receives airflow from the first, second, and third air compressors and forwards airflow to the aircraft compartment. The recycling heat exchanger receives airflow from the aircraft compartment and recirculates airflow back to the aircraft compartment.
摘要翻译： 用于飞机舱和飞机动力系统的集成环境控制系统包括第一和第二空气压缩机，辅助动力单元以及第一和第二环境控制系统。 第一和第二压缩机接收和压缩飞机外部的气流。 辅助动力单元包括可旋转地安装动力涡轮的第一轴，用于压缩来自飞行器外部的气流的第三空气压缩机和用于冷却气流的第一冷却涡轮机。 每个环境控制系统包括第一热交换器，再循环热交换器和可旋转地安装第四压缩机的第二轴和用于压缩和冷却气流的第二冷却涡轮机。 第一热交换器接收来自第一，第二和第三空气压缩机的气流并且将气流转向飞行器舱。 回收热交换器接收来自飞机舱的气流并将气流再循环回飞机舱。
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公开(公告)号：US20060042252A1
公开(公告)日：2006-03-02
申请号：US11182550
申请日：2005-07-15
申请人： Jean-Luc Derouineau
发明人： Jean-Luc Derouineau
IPC分类号： F02C7/268
CPC分类号： F02C9/26 , F05D2220/76 , F05D2270/05
摘要： An engine power extraction control system controls the main propulsion engines and the electrical machines that are coupled thereto to supply an appropriate amount of aircraft thrust and electrical energy to the aircraft. The engines and electrical machines are also controlled so that the propulsion thrust that is generated is split between the various turbines in the main propulsion engines to maintain an adequate surge margin and to minimize residual thrust generation.
摘要翻译： 发动机功率提取控制系统控制主推进发动机和联接到其上的电机，以向飞行器提供适当量的飞机推力和电能。 发动机和电机也受到控制，使得所产生的推进推力在主推进发动机中的各种涡轮机之间分开，以保持足够的喘振裕度，并使剩余推力产生最小化。
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公开(公告)号：US20120078450A1
公开(公告)日：2012-03-29
申请号：US12891581
申请日：2010-09-27
IPC分类号： G05D1/06
CPC分类号： G01C23/005 , G05D1/0005 , G05D1/0607
摘要： Methods and systems are provided for executing a single continuous altitude change by an aircraft to cruise altitude using an electronic flight bag via a flight management system. The method comprises the determination of an altitude change in a flight plan during the cruise phase of the flight plan. Based on the altitude change and a mathematical model of the aircraft an optimum vertical trajectory profile or the aircraft is determined from which an angle of attack (AOA) and a thrust is derived to achieve the optimum vertical trajectory. From the AOA and the thrust, the required aircraft control variables are determined that may be applied to the engines and the control surface actuators of the aircraft.
摘要翻译： 提供了一种方法和系统，用于通过飞行管理系统使用电子飞行包，由飞机执行单次连续高度变化以巡航高度。 该方法包括在飞行计划的巡航阶段确定飞行计划中的高度变化。 基于高度变化和飞行器的数学模型，确定最佳垂直轨迹轮廓或确定从哪个角度（AOA）和推力得到最佳垂直轨迹的飞机。 从AOA和推力来看，确定可能应用于飞机的发动机和控制表面致动器的所需飞机控制变量。
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4.发明申请AIRCRAFT ELECTRICAL POWER SYSTEM ARCHITECTURE USING AUXILIARY POWER UNIT DURING APPROACH AND TAXI 失效航空电力系统架构在方法和税收期间使用辅助电源单元公开(公告)号：US20110133545A1
公开(公告)日：2011-06-09
申请号：US12630755
申请日：2009-12-03
申请人： Wayne PEARSON , Jean-Luc DEROUINEAU
发明人： Wayne PEARSON , Jean-Luc DEROUINEAU
CPC分类号： H02J9/08 , F01D15/10 , F02C7/32 , F05D2220/50 , Y02T50/54 , Y10T307/636 , Y10T307/724
摘要： An electrical power system architecture uses an auxiliary power unit as an electrical power source during taxi (ground idle) and approach idle (if required). Using the APU as a power source enables a low pressure spool driven electrical generator to be off-line when its speed is too low for it to operate effectively.
摘要翻译： 电力系统架构在出租车（地面空闲）期间使用辅助电源单元作为电源，并且进入空闲（如果需要）。 使用APU作为动力源，当低速阀芯驱动的发电机的速度太低而无法有效运行时，可以将其脱机。
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公开(公告)号：US07970497B2
公开(公告)日：2011-06-28
申请号：US11681686
申请日：2007-03-02
IPC分类号： G01C23/00
CPC分类号： B64D13/06 , B64D2013/0618 , B64D2013/0644 , Y02T50/54 , Y02T50/56
摘要： An aircraft architecture may be designed to create an optimal balance between electric power and bleed power in order to match or improve current more electric architecture (MEA) performance while simplifying power extraction from the engines as well as simplifying the electrical system. Conventional aircraft architectures may use electric only ECS and cabin pressurization systems (so-called “no bleed” systems). Alternatively, older conventional aircraft may use strictly engine bleed air to provide power for ECS and cabin pressurization systems. The present invention, on the other hand, provides an architecture which may optimize the use of both engine bleed air and MEA designs to provide a system that may be simpler and potentially more reliable and available as compared to conventional aircraft architectures.
摘要翻译： 飞机架构可以设计成在电力和泄放功率之间创建最佳平衡，以便匹配或改善当前更多的电气结构（MEA）性能，同时简化从发动机的功率提取以及简化电气系统。 传统的飞行器架构可以仅使用电动ECS和客舱加压系统（所谓的“无出血”系统）。 或者，较旧的常规飞行器可以严格地使用发动机排气来为ECS和客舱加压系统提供动力。 另一方面，本发明提供了一种架构，其可以优化发动机放气和MEA设计的使用，以提供与常规飞行器架构相比可以更简单并且可能更可靠和可用的系统。
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公开(公告)号：US20090326737A1
公开(公告)日：2009-12-31
申请号：US11681686
申请日：2007-03-02
CPC分类号： B64D13/06 , B64D2013/0618 , B64D2013/0644 , Y02T50/54 , Y02T50/56
摘要： An aircraft architecture may be designed to create an optimal balance between electric power and bleed power in order to match or improve current more electric architecture (MEA) performance while simplifying power extraction from the engines as well as simplifying the electrical system. Conventional aircraft architectures may use electric only ECS and cabin pressurization systems (so-called “no bleed” systems). Alternatively, older conventional aircraft may use strictly engine bleed air to provide power for ECS and cabin pressurization systems. The present invention, on the other hand, provides an architecture which may optimize the use of both engine bleed air and MEA designs to provide a system that may be simpler and potentially more reliable and available as compared to conventional aircraft architectures.
摘要翻译： 飞机架构可以设计成在电力和泄放功率之间创建最佳平衡，以便匹配或改善当前更多的电气结构（MEA）性能，同时简化从发动机的功率提取以及简化电气系统。 传统的飞行器架构可以仅使用电动ECS和客舱加压系统（所谓的“无出血”系统）。 或者，较旧的常规飞行器可以严格地使用发动机排气来为ECS和客舱加压系统提供动力。 另一方面，本发明提供了一种架构，其可以优化发动机放气和MEA设计的使用，以提供与常规飞行器架构相比可以更简单并且可能更可靠和可用的系统。
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7.发明申请公开(公告)号：US20070271952A1
公开(公告)日：2007-11-29
申请号：US11440486
申请日：2006-05-25
IPC分类号： F25D9/00
CPC分类号： B64D13/06 , B64D2013/0611 , B64D2013/0688 , Y02T50/44 , Y02T50/56
摘要： An integrated environmental control system for an aircraft compartment and aircraft power system comprises first and second air compressors, an auxiliary power unit, and first and second environmental control systems. The first and second compressors receive and compress airflow from the aircraft exterior. The auxiliary power unit comprises a first shaft rotatably mounting a power turbine, a third air compressor to compress airflow from the aircraft exterior, and a first cooling turbine to cool the airflow. Each environmental control system comprises a first heat exchanger, a recycling heat exchanger, and a second shaft rotatably mounting a fourth compressor and a second cooling turbine for compressing and cooling the airflow. The first heat exchanger receives airflow from the first, second, and third air compressors and forwards airflow to the aircraft compartment. The recycling heat exchanger receives airflow from the aircraft compartment and recirculates airflow back to the aircraft compartment.
摘要翻译： 用于飞机舱和飞机动力系统的集成环境控制系统包括第一和第二空气压缩机，辅助动力单元以及第一和第二环境控制系统。 第一和第二压缩机接收和压缩飞机外部的气流。 辅助动力单元包括可旋转地安装动力涡轮的第一轴，用于压缩来自飞行器外部的气流的第三空气压缩机和用于冷却气流的第一冷却涡轮机。 每个环境控制系统包括第一热交换器，再循环热交换器和可旋转地安装第四压缩机的第二轴和用于压缩和冷却气流的第二冷却涡轮机。 第一热交换器接收来自第一，第二和第三空气压缩机的气流并且将气流转向飞行器舱。 回收热交换器接收来自飞机舱的气流并将气流再循环回飞机舱。
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公开(公告)号：US07285871B2
公开(公告)日：2007-10-23
申请号：US11182550
申请日：2005-07-15
申请人： Jean-Luc Derouineau
发明人： Jean-Luc Derouineau
IPC分类号： H02P9/00
CPC分类号： F02C9/26 , F05D2220/76 , F05D2270/05
摘要： An engine power extraction control system controls the main propulsion engines and the electrical machines that are coupled thereto to supply an appropriate amount of aircraft thrust and electrical energy to the aircraft. The engines and electrical machines are also controlled so that the propulsion thrust that is generated is split between the various turbines in the main propulsion engines to maintain an adequate surge margin and to minimize residual thrust generation.
摘要翻译： 发动机功率提取控制系统控制主推进发动机和联接到其上的电机，以向飞行器提供适当量的飞机推力和电能。 发动机和电机也受到控制，使得所产生的推进推力在主推进发动机中的各种涡轮机之间分开，以保持足够的喘振裕度，并使剩余推力产生最小化。
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9.发明授权Hybrid electrical ice protection system and method including an energy saving mode 有权混合式电冰保护系统及方法包括节能模式公开(公告)号：US07124983B2
公开(公告)日：2006-10-24
申请号：US11042764
申请日：2005-01-24
IPC分类号： B64D15/12
CPC分类号： B64D15/12
摘要： A hybrid electrical ice protection system implements three ice protection methods in various combinations. The ice protection methods include the fully-evaporative anti-ice protection method, the wet running anti-ice protection method, and the de-ice method. The particular methods that are implemented vary, depending on the particular aircraft structure for which ice protection is being provided and on the power condition of the aircraft.
摘要翻译： 混合电冰保护系统以各种组合实施三种防冰方法。 防冰方法包括全蒸发防冰保护方法，湿运行防冰保护方法和除冰法。 实施的具体方法取决于提供防冰的特定飞机结构和飞机的功率状况而变化。
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10.发明授权Systems and methods for displaying aircraft braking distance during surface operations 有权在地面作业期间显示飞机制动距离的系统和方法公开(公告)号：US08958942B2
公开(公告)日：2015-02-17
申请号：US13804294
申请日：2013-03-14
IPC分类号： G01M17/00 , G08B21/00 , G06F17/00 , B64C25/42 , B64D43/00 , B64D45/00 , G08G5/00 , G08G5/06 , G01S13/93
CPC分类号： G06F17/00 , B64C25/42 , B64C25/426 , B64D43/00 , B64D45/00 , G01S2013/9335 , G08G5/0021 , G08G5/065
摘要： Systems and methods are operable to present braking distance information to crew of an installation aircraft. An exemplary embodiment determines a braking distance for a braking maneuver of the installation aircraft, wherein the braking distance is based on a current ground speed of the aircraft; and generates a graphical representation that is presented on a display, wherein a location of a graphical icon on the graphical representation indicates the determined braking distance from the installation aircraft.
摘要翻译： 系统和方法可操作以向安装飞机的乘务员呈现制动距离信息。 一个示例性实施例确定了用于安装飞机的制动操纵的制动距离，其中制动距离基于飞行器的当前地面速度; 并且生成呈现在显示器上的图形表示，其中图形表示上的图形图标的位置指示从所述安装飞机确定的制动距离。
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