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31. 发明公开

EP2955673A1 AIRCRAFT DEPARTURE PROFILE GENERATION COMPLIANT WITH NOISE ABATEMENT LIMITS 审中-公开
标题翻译：埃及UNG ES S S S S S S S S S S S S S S S S S S S
公开(公告)号：EP2955673A1
公开(公告)日：2015-12-16
申请号：EP15171832.7
申请日：2015-06-12
申请人： The Boeing Company
发明人： McGREGOR, Daniel L. , BENT, Paul Henry , STOLL, Douglas A.
IPC分类号： G06Q10/06
CPC分类号： G05D1/0214 , B64F1/26 , G01C5/00 , G01C5/005 , G01C23/00 , G05D1/00 , G05D1/0005 , G05D1/0653 , G06Q10/06 , G08G5/0021 , G08G5/0086 , G08G5/065
摘要： Systems and methods are described for dynamically generating flight departure profiles that are in compliance with aircraft emission limits. Emission limits may include noise abatement limits. Flight departure profiles may be generated on a flight by flight basis, and/or may be based on then-current conditions such as wind speed, wind direction, and ambient temperature.
摘要翻译：描述了用于动态生成符合飞机排放限制的航班起飞剖面的系统和方法。排放限制可能包括降噪限制。航班起飞概况可能会以飞行方式飞行生成，和/或可以根据风速，风向和环境温度等当前条件。

32. 发明公开

EP2584422A1 Method for a noise abatement procedure for an aircraft 有权
标题翻译： VerfahrenfüreinSchalldämmungsverfahrenfürFlugzeuge
公开(公告)号：EP2584422A1
公开(公告)日：2013-04-24
申请号：EP12188911.7
申请日：2012-10-17
申请人： General Electric Company
发明人： Bakker, Michael John , Hochwarth, Joachim Karl Ulf , Flanary, Sean Edward
IPC分类号： G05D1/10
CPC分类号： G05D1/0653 , G08G5/006
摘要： A method of reducing noise from an aircraft (30) in a noise abatement zone (34) during flight of the aircraft (30) includes determining where the flight path (32) of the aircraft (30) will intersect the noise abatement zone (34) and then operating the aircraft (30) in a quieter manner when the aircraft (30) is within the noise abatement zone (34).
摘要翻译：一种在飞行器（30）飞行期间减少噪声消除区（34）中的飞机（30）的噪声的方法包括确定飞行器（30）的飞行路径（32）将与噪声消除区域（34）相交的位置），然后当飞行器（30）在噪声消除区（34）内时，以更安静的方式操作飞行器（30）。

33. 发明授权

EP1727012B1 Aircraft tailstrike avoidance system 有权
标题翻译：系统以避免在飞机上，背面触摸
公开(公告)号：EP1727012B1
公开(公告)日：2007-11-07
申请号：EP06076438.8
申请日：2000-11-30
申请人： The Boeing Company
发明人： Dewitt, Wendi M. , Evans, Monte R. , Wells, Stephen L.
IPC分类号： G05D1/06
CPC分类号： G05D1/0808 , G05D1/0653

34. 发明授权

EP1235712B1 AIRCRAFT TAILSTRIKE AVOIDANCE SYSTEM 有权
标题翻译：系统以防止飞机坠毁REAR
公开(公告)号：EP1235712B1
公开(公告)日：2007-01-31
申请号：EP00992006.7
申请日：2000-11-30
申请人： The Boeing Company
发明人： DEWITT, Wendi, M. , EGGOLD, David, P. , EVANS, Monte, R. , SANKRITHI, Mithra, M., K., V. , WELLS, Stephen, L.
IPC分类号： G05D1/06
CPC分类号： G05D1/0808 , B64C13/503 , B64D45/04 , G05D1/0653
摘要： An improvement to an aircraft flight control system is provided for reducing the likelihood of an aircraft tailstrike. The flight control system includes a pitch command provided to a pitch control device for altering the aircraft's pitch attitute. The improvement is a system of altering the pitch command to avoid an aircraft tailstrike. The improvement includes determining a current tailskid closure rate and a current tail height; comparing the current tailskid closure rate with a threshold closure rate to determine an excess closure rate amount; and adding an incremental nose-down pitch command with the pitch command to avoid a potential aircraft tailstrike. The threshold closure rate is dependent upon the current tailskid height. The incremental nose-down pitch command is calculated as a function of the excess closure rate amount. An alternative embodiment is provided in which the current height is compared with a threshold height (that is a function of the current tailskid closure rate) to determine an excess height amount. The excess height is then used to form an incremental nose-down pitch command. Another embodiment is described using both height and rate thresholds to calculate the incremental nose-down pitch command. Alternative arrangements may be used in which other non-derivative and derivative values are used, e.g., pitch angle margin and pitch rate.

35. 发明公开

KR20180068469A 무인비행장치 및 이를 포함하는 시스템 审中-公开
公开(公告)号：KR20180068469A
公开(公告)日：2018-06-22
申请号：KR20160170187
申请日：2016-12-14
申请人： HYUNDAI MOTOR CO LTD
发明人： CHUN CHANG WOO
IPC分类号： G06Q50/10 , B64C39/02
CPC分类号： G08G5/0013 , B64C39/024 , B64C2201/088 , B64C2201/108 , B64C2201/128 , B64C2201/141 , B64C2201/165 , B64C2201/18 , B64C2201/208 , G05D1/0005 , G05D1/0653 , G05D1/0669 , G05D1/0684 , G05D1/102 , G08G5/0034 , G08G5/0069 , G08G5/025
摘要： 개시된실시예는비행중 이동경로가유사한차량에착륙하여차량과함께이동할수 있는무인비행장치및 이를포함하는시스템을제공한다. 개시된실시예에따른시스템은, 무인비행장치와의통신을통해무인비행장치의이동을모니터링하는관제센터; 및상기관제센터와의통신을통해이동과관련된정보를송수신하고, 이동경로중 적어도일부와대응되는경로로이동하는차량에착륙하여차량과함께이동하는무인비행장치;를포함한다.

36. 发明公开

EP2672357A1 Takeoff/landing touchdown protection management system 有权
标题翻译：起飞/着陆触地保护管理系统
公开(公告)号：EP2672357A1
公开(公告)日：2013-12-11
申请号：EP12178520.8
申请日：2012-07-30
申请人： Bell Helicopter Textron Inc.
发明人： Shue, Shyhpyng Jack
IPC分类号： G05D1/06 , G05D1/08
CPC分类号： B64C13/04 , B64C13/16 , B64C13/503 , B64C25/001 , B64C25/34 , B64C27/57 , B64C2025/325 , B64D45/00 , G05D1/0653 , G05D1/0669 , G05D1/0676 , G05D1/0858
摘要： An air/ground contact logic management system (101) for use with fly-by-wire control systems in an aircraft (11). The system (101) includes a first sensor (127) configured to provide an output signal to determine when the aircraft (11) is in a transition region. A logic management system (118) is in communication with the first sensor (127) and is configured to receive and process the output signal and classify a mode (107, 109, 111, 113, 117, 119, 212, 123) of the aircraft (11). A controller (30) receives signal data from the logic management system (118) and communicates with a control axis actuator to regulate a level of control authority (130) provided to a pilot. The control authority (130) is individually regulated within each integrator as a result of the individual landing gear states.
摘要翻译：一种空中/地面接触逻辑管理系统（101），用于与飞机（11）中的电传控制系统一起使用。系统（101）包括配置成提供输出信号以确定飞机（11）何时处于过渡区域中的第一传感器（127）。逻辑管理系统（118）与第一传感器（127）通信并且被配置为接收和处理输出信号并且将输出信号的模式（107,109,111,113,117,119,212,123）分类为飞机（11）。控制器（30）从逻辑管理系统（118）接收信号数据并与控制轴致动器通信以调节提供给飞行员的控制权限（130）的级别。作为各个起落架状态的结果，控制权（130）在每个积分器内被单独调节。

37. 发明公开

EP1995174A3 Method for vertical takeoff from and landing on inclined surfaces 审中-公开
标题翻译：上倾斜面垂直起始和着陆的方法
公开(公告)号：EP1995174A3
公开(公告)日：2013-04-24
申请号：EP08101858.2
申请日：2008-02-21
申请人： Honeywell International Inc.
发明人： Hursig, David C. , Martinez, Steven D.
IPC分类号： B64C27/20 , B64C39/02 , B64D45/04 , G05D1/08
CPC分类号： B64C27/20 , B64C39/024 , B64C2201/027 , B64C2201/088 , B64C2201/108 , B64C2201/162 , B64D45/04 , G05D1/0653 , G05D1/0858
摘要： Takeoff and landing modes are added to a flight control system of a Vertical Take-Off and Landing (VTOL) Unmanned Air Vehicle (UAV). The takeoff and landing modes use data available to the flight control system and the VTOL UAV's existing control surfaces and throttle control. As a result, the VTOL UAV can takcoff from and land on inclined surfaces without the use of landing gear mechanisms designed to level the UAV on the inclined surfaces.

38. 发明公开

EP0257702A3 Navigational apparatus and methods for displaying aircraft position with respect to a selected vertical flight path profile 失效
标题翻译：用于显示飞机位置的导航装置和方法相对于所选择的垂直飞行路径轮廓
公开(公告)号：EP0257702A3
公开(公告)日：1989-06-07
申请号：EP87201550.8
申请日：1987-08-14
申请人： THE BOEING COMPANY
发明人： King, Ethmer Wesley , Yotsuuye, David Sadao , Kircher, Robert Charles, Jr. , Radfar, Mohammed Reza
IPC分类号： G01C5/00
CPC分类号： G01C5/005 , G05D1/0653
摘要： An aircraft navigational system for providing a geometic display to the pilot of the vertical position of the aircraft relative to a selected vertical flight path profile as the aircraft progresses between its departure and destination. The vertical profile, which has a climb portion, a cruise portion and a descent portion, is formed by a number of navigational points, each of which is defined by an altitude component and a geographical position component. The profile points which form the climb and descent profiles are calculated from controller assigned altitude and waypoint constraints as well as from airspeed and altitude operating limitations which define various selected aircraft performance climb and descent modes.

39. 发明公开

EP0257702A2 Navigational apparatus and methods for displaying aircraft position with respect to a selected vertical flight path profile 失效
标题翻译：导航装置和用于相对于选定垂直Flugwegprofils显示导弹位置的方法。
公开(公告)号：EP0257702A2
公开(公告)日：1988-03-02
申请号：EP87201550.8
申请日：1987-08-14
申请人： THE BOEING COMPANY
发明人： King, Ethmer Wesley , Yotsuuye, David Sadao , Kircher, Robert Charles, Jr. , Radfar, Mohammed Reza
IPC分类号： G01C5/00
CPC分类号： G01C5/005 , G05D1/0653
摘要： An aircraft navigational system for providing a geometic display to the pilot of the vertical position of the aircraft relative to a selected vertical flight path profile as the aircraft progresses between its departure and destination. The vertical profile, which has a climb portion, a cruise portion and a descent portion, is formed by a number of navigational points, each of which is defined by an altitude component and a geographical position component. The profile points which form the climb and descent profiles are calculated from controller assigned altitude and waypoint constraints as well as from airspeed and altitude operating limitations which define various selected aircraft performance climb and descent modes.
摘要翻译：一种飞机导航系统，用于提供geometic显示器以相对于选定垂直飞行路径剖面飞行器的垂直位置的导频作为飞机其出发地和目的地之间进行。垂直剖面，其具有在部分的爬升，巡航部分和下降部分，是由多个导航点的形成，每个的所有这一切是通过在高度分量和地理部件位置来定义。形成该爬升和下降轮廓的剖面图的点从控制器分配高度和路点约束，以及从限定各种选定飞机性能爬升和下降模式空速和高度的操作限制进行计算。

40. 发明公开

EP0078688A1 Speed command apparatus for aircraft 失效
标题翻译： GeschwindigkeitssteuervorrichtungfürFlugzeug。
公开(公告)号：EP0078688A1
公开(公告)日：1983-05-11
申请号：EP82305780.7
申请日：1982-11-01
申请人： SPERRY CORPORATION
发明人： Miller, Harry
IPC分类号： G05D1/06
CPC分类号： G05D1/0638 , G05D1/0653
摘要： Speed command apparatus for use in an aircraft performance management system of the type wherein a target Mach number command is supplied to the aircraft pitch controls to attain the target Mach and is simultaneously supplied to the aircraft throttles to capture a computed engine pressure ratio (EPR) or fan speed (N,), the apparatus being operative during maximum thrust climbs and minimum thrust descents upon an abrupt step function target Mach number command. The step function command is converted to a ramp command, the slope of which is directly proportional to the existing thrust-minus- drag conditions of the aircraft and inversely proportional to its existing weight, thus ensuring a proper division between aircraft acceleration and rate of climb or aircraft deceleration and rate of descent.
摘要翻译：用于飞机性能管理系统的速度指令装置，其中向飞行器俯仰控制提供目标马赫数指令以达到目标马赫，同时提供给飞行器节流阀以捕获计算的发动机压力比（EPR）或风扇速度（N1），该装置在最大推力爬升时起作用，并且在突然的步骤功能目标马赫数指令上最小推力下降。步进功能命令被转换为斜坡命令，其斜率与飞机的现有推力 - 负阻力条件成正比，与其现有重量成反比，从而确保飞机加速度与爬升速率之间的适当分配或飞机减速和下降速度。

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