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公开(公告)号：US07383104B2
公开(公告)日：2008-06-03
申请号：US11196397
申请日：2005-08-04
申请人： Hirokazu Ishii , Kohei Funabiki , Yoshinori Okuno , Hiromi Gomi
发明人： Hirokazu Ishii , Kohei Funabiki , Yoshinori Okuno , Hiromi Gomi
摘要： It is an object of the present invention to provide a system that is used to provide support so that a pilot can perform flight operations that reduce noise pollution, by devising this system so that noise conditions on the ground are calculated and displayed on the basis of map information for the flight area in which facilities and the like are described, environmental conditions in the flight area such as the wind direction and wind velocity, or the temperature and density of the atmosphere, and noise generation data for the aircraft itself. The apparatus for supporting low-noise flight according to the present invention comprises means for estimating the noise generated by an aircraft using flight data such as the flight speed, the climb and descent rates, the engine power and the like of the aircraft, means for calculating the level at which the noise generated by the aircraft is propagated in the respective regions on the ground, and means for displaying the calculation results on a map in quantitative terms.
摘要翻译： 本发明的目的是提供一种用于提供支撑的系统，使得飞行员可以通过设计该系统来执行降低噪声污染的飞行操作，从而基于地面上的噪声条件被计算和显示 描述设施等的飞行区域的地图信息，飞行区域中的风向和风速的环境条件，大气的温度和密度，以及飞机本身的噪声产生数据。 根据本发明的用于支持低噪声飞行的装置包括用于使用诸如飞行速度，爬升和下降速率，飞机功率等飞行数据来估计飞行器产生的噪声的装置， 计算飞机产生的噪声在地面上相应区域中传播的水平，以及用于在地图上以数量显示计算结果的装置。
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公开(公告)号：US20060111818A1
公开(公告)日：2006-05-25
申请号：US11196397
申请日：2005-08-04
申请人： Hirokazu Ishii , Kohei Funabiki , Yoshinori Okuno , Hiromi Gomi
发明人： Hirokazu Ishii , Kohei Funabiki , Yoshinori Okuno , Hiromi Gomi
IPC分类号： G01C23/00
摘要： It is an object of the present invention to provide a system that is used to provide support so that a pilot can perform flight operations that reduce noise pollution, by devising this system so that noise conditions on the ground are calculated and displayed on the basis of map information for the flight area in which facilities and the like are described, environmental conditions in the flight area such as the wind direction and wind velocity, or the temperature and density of the atmosphere, and noise generation data for the aircraft itself. The apparatus for supporting low-noise flight according to the present invention comprises means for estimating the noise generated by an aircraft using flight data such as the flight speed, the climb and descent rates, the engine power and the like of the aircraft, means for calculating the level at which the noise generated by the aircraft is propagated in the respective regions on the ground, and means for displaying the calculation results on a map in quantitative terms.
摘要翻译： 本发明的目的是提供一种用于提供支撑的系统，使得飞行员可以通过设计该系统来执行降低噪声污染的飞行操作，从而基于地面上的噪声条件被计算和显示 描述设施等的飞行区域的地图信息，飞行区域中的风向和风速的环境条件，大气的温度和密度，以及飞机本身的噪声产生数据。 根据本发明的用于支持低噪声飞行的装置包括用于使用诸如飞行速度，爬升和下降速率，飞机功率等飞行数据来估计飞行器产生的噪声的装置， 计算飞机产生的噪声在地面上相应区域中传播的水平，以及用于在地图上以数量显示计算结果的装置。
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公开(公告)号：US08874285B2
公开(公告)日：2014-10-28
申请号：US13378473
申请日：2010-06-22
CPC分类号： B64C25/50 , G05D1/0083
摘要： An aircraft steering angle control system is provided that minimizes the amount of skidding of an airframe that is turning on a low-μ taxiway surface, such as an icy taxiway surface, and allows for directional control of the airframe by a steering command. The aircraft steering angle control system outputs an operation signal related to a steering angle as a control command signal for a nose steering wheel, and includes: a nose steering wheel envelope protection function including a reference steering angle setting unit that calculates a reference steering angle on the assumption that the airframe is not skidding; a skid detection unit that detects a skidding state of the airframe based on the reference steering angle; and a switch unit that selects a control command signal for the nose steering wheel in conjunction with the skid detection unit.
摘要翻译： 提供一种飞行器转向角度控制系统，其最小化打开低μ滑行道表面（例如冰冷的滑行道表面）的机身的打滑量，并且允许通过转向命令来对机身进行方向控制。 飞行器转向角控制系统输出与转向角相关的操作信号作为用于鼻子方向盘的控制命令信号，并且包括：鼻子方向盘包络保护功能，包括参考转向角设置单元，其计算参考转向角 机身不打滑的假设; 滑行检测单元，其基于所述基准转向角度来检测所述机身的打滑状态; 以及开关单元，其与滑动检测单元一起选择用于鼻子方向盘的控制命令信号。
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公开(公告)号：US20120158218A1
公开(公告)日：2012-06-21
申请号：US13378473
申请日：2010-06-22
IPC分类号： B64C25/50
CPC分类号： B64C25/50 , G05D1/0083
摘要： To provide an aircraft steering angle control system that minimizes the amount of skidding of an airframe that is turning on a low-μ taxiway surface such as an icy taxiway surface and allows for directional control of the airframe by a steering command, an aircraft steering angle control system that outputs an operation signal related to a steering angle as a control command signal for a nose steering wheel incorporates a nose wheel envelope protection including a reference steering angle setting unit that calculates a reference steering angle on the assumption that the airframe is not skidding; a skid detection unit that detects a skidding state of the airframe based on the reference steering angle; and a switch unit that selects a control command signal for a nose wheel in conjunction with the skid detection unit.
摘要翻译： 为了提供一种飞行器转向角度控制系统，其最小化打开低μ滑行道表面（例如冰冷的滑行道表面）并且允许通过转向命令对机身的方向控制的机身的打滑量，飞机转向角 输出与转向角相关的操作信号的控制系统作为鼻子方向盘的控制命令信号，包括前轮包围保护，包括基准转向角设定单元，该基准转向角设定单元假设机身不打滑时计算参考转向角 ; 滑行检测单元，其基于所述基准转向角度来检测所述机身的打滑状态; 以及与滑移检测单元一起选择用于前轮的控制指令信号的开关单元。
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