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公开(公告)号：US07578136B2
公开(公告)日：2009-08-25
申请号：US11165729
申请日：2005-06-23
申请人： Jean-Luc Derouineau , Bjoern Schenk , Clarence Lui
发明人： Jean-Luc Derouineau , Bjoern Schenk , Clarence Lui
CPC分类号： B64D13/02 , B64D13/06 , B64D2013/0611 , Y02T50/44 , Y02T50/56
摘要： An integrated power and pressurization management system supplies electrical power and cabin pressurization and cooling air during both airborne and ground operations. The system includes an integral auxiliary power unit (APU) that has a compressor, a motor-generator, and a power turbine all mounted on one shaft. The integral APU can supply compressed air for cabin pressurization and environmental cooling functions, and can generate electrical power for various electrical loads. The system further includes one or more electrically driven compressors.
摘要翻译： 集成的电力和加压管理系统在机载和地面操作期间提供电力和客舱加压和冷却空气。 该系统包括一个整体辅助动力装置（APU），它具有一个全部安装在一个轴上的压缩机，电动发电机和动力涡轮机。 集成APU可以为客舱加压和环境冷却功能提供压缩空气，并可以为各种电气负载产生电力。 该系统还包括一个或多个电动压缩机。
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公开(公告)号：US20060231680A1
公开(公告)日：2006-10-19
申请号：US11165729
申请日：2005-06-23
申请人： Jean-Luc Derouineau , Bjoern Schenk , Clarence Lui
发明人： Jean-Luc Derouineau , Bjoern Schenk , Clarence Lui
IPC分类号： B64D11/00
CPC分类号： B64D13/02 , B64D13/06 , B64D2013/0611 , Y02T50/44 , Y02T50/56
摘要： An integrated power and pressurization management system supplies electrical power and cabin pressurization and cooling air during both airborne and ground operations. The system includes an integral auxiliary power unit (APU) that has a compressor, a motor-generator, and a power turbine all mounted on one shaft. The integral APU can supply compressed air for cabin pressurization and environmental cooling functions, and can generate electrical power for various electrical loads. The system further includes one or more electrically driven compressors.
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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：US07936086B2
公开(公告)日：2011-05-03
申请号：US12043374
申请日：2008-03-06
申请人： Edwin Yue , Jean-Luc Derouineau , Wayne T. Pearson
发明人： Edwin Yue , Jean-Luc Derouineau , Wayne T. Pearson
CPC分类号： H02J1/10 , H02J1/102 , H02J4/00 , Y02T50/54 , Y10T307/718
摘要： A power generation and distribution system utilizes two or more AC generators each of which may be driven by a separate prime mover such as a turbine. The generators may be driven at different rotational speeds. AC power from the generators may be rectified and applied to a common DC bus. Electrical loads may be applied to the common bus and may establish an electrical power requirement. Allocation of electrical power requirement may be made among the generators based on power available from the turbines.
摘要翻译： 发电和分配系统利用两个或更多个AC发电机，每个发电机可以由单独的原动机例如涡轮机驱动。 发电机可以以不同的转速驱动。 来自发电机的交流电源可以被整流并应用于公共直流母线。 电负载可以施加到公共总线，并可以建立电力需求。 可以根据来自涡轮机的功率在发电机中进行电力需求分配。
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7.发明申请HYBRID ELECTRICAL ICE PROTECTION SYSTEM AND METHOD INCLUDING AN ENERGY SAVING MODE 有权混合电冰保护系统和包括节能模式的方法公开(公告)号：US20060196994A1
公开(公告)日：2006-09-07
申请号：US11042764
申请日：2005-01-24
申请人： Philip Chow , Jean-Luc Derouineau
发明人： Philip Chow , Jean-Luc Derouineau
IPC分类号： B64D15/20
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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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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9.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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