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公开(公告)号：US20160214731A1
公开(公告)日：2016-07-28
申请号：US14913449
申请日：2014-08-27
发明人： Philip A. Schmidt
CPC分类号： B64D31/12 , B64C13/16 , B64D31/06 , B64D31/10 , F02C9/42 , G05D1/0005 , G05D1/0072 , Y02T50/44
摘要： An aircraft controller includes a memory for storing instructions. The instructions are operable to cause the controller to perform a thrust balancing method and ensure a balanced thrust output from the aircraft.
摘要翻译： 飞机控制器包括用于存储指令的存储器。 指令可操作以使控制器执行推力平衡方法并确保来自飞行器的平衡的推力输出。
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42.发明授权公开(公告)号：US09327824B2
公开(公告)日：2016-05-03
申请号：US12968383
申请日：2010-12-15
申请人： Mark Good , Paul Johnson
发明人： Mark Good , Paul Johnson
摘要： An aircraft wing system for differentially adjusting a first deployable lift device and a second deployable lift device on a wing during take-off and landing, the system having a controller, which is programmed to determine desired positions for the first and second deployable lift devices, based on a desired position signal, and to activate high and low horsepower motors to move the first deployable lift devices to desired positions. The system has a controller which determines an adjustment amount for each motor, based on the system architecture.
摘要翻译： 一种飞机机翼系统，用于在起飞和着陆期间差异地调节机翼上的第一可展开提升装置和第二可展开提升装置，所述系统具有控制器，所述控制器被编程以确定所述第一和第二可展开提升装置的期望位置， 基于期望的位置信号，并且激活高和低功率电动机以将第一可展开的提升装置移动到期望的位置。 该系统具有基于系统架构确定每个电机的调节量的控制器。
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公开(公告)号：US20160054350A1
公开(公告)日：2016-02-25
申请号：US14682733
申请日：2015-04-09
CPC分类号： G01P5/16 , B64C5/02 , B64C5/10 , B64C13/16 , B64C27/00 , B64C2027/8263 , B64D43/02 , G01P5/02
摘要： An aircraft is provided and includes an airframe. The airframe includes first and second rotor apparatuses at upper and tail portions of the aircraft, respectively, to provide for control and navigational drive. The aircraft further includes a stabilizer component disposed at the tail portion in a position displaced from downwash of the first and second rotor apparatuses at airspeed ranges and a control system configured to apply a dither actuation signal to the stabilizer component at the airspeed ranges by which an aircraft response to a stabilizer component input is measurable for airspeed estimation purposes.
摘要翻译： 提供飞机并包括机身。 机身分别包括在飞行器的上部和尾部的第一和第二转子装置，以提供控制和导航驱动。 该飞机还包括一个稳定器部件，该稳定器部件设置在尾部处于与第一和第二转子装置在空速范围内从下冲洗中移位的位置;以及控制系统，该控制系统构造成以空速范围向稳定器部件施加抖动致动信号， 飞机对稳定器部件输入的响应可以用于空速估计目的。
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44.发明授权Method of controlling the wing flaps and horizontal stabilizer of a hybrid helicopter 有权控制混合动力直升机翼翼和水平稳定器的方法公开(公告)号：US09150307B2
公开(公告)日：2015-10-06
申请号：US13895700
申请日：2013-05-16
申请人： AIRBUS HELICOPTERS
发明人： Paul Eglin
摘要： A method of controlling a high speed rotary wing aircraft (1) comprising: a fuselage (2); at least one main rotor (3); at least one variable pitch propulsive propeller (4); at least two half-wings (11, 11′) positioned on either side of said fuselage (2); at least one horizontal stabilizer (20) provided with a movable surface (21, 21′); and at least one power plant driving said main rotor (3) and each propulsive propeller (4) in rotation. Said method serves to adjust the lift of said half-wings (11, 11′) and the lift of the horizontal stabilizer (20) so that the collective pitch of said blades (31) of said main rotor (3) is equal to a setpoint collective pitch, so that the longitudinal cyclic pitch of said blades (31) of said main rotor (3) is equal to a setpoint longitudinal cyclic pitch, and so that the lateral cyclic pitch of said blades (31) of said main rotor (3) is equal to a setpoint lateral cyclic pitch during a stabilized stage of flight.
摘要翻译： 一种控制高速旋翼机（1）的方法，包括：机身（2）; 至少一个主转子（3）; 至少一个可变桨距推进螺旋桨（4）; 位于所述机身（2）两侧的至少两个半翼（11,11'）; 至少一个设置有可移动表面（21,21'）的水平稳定器（20）; 以及旋转驱动所述主转子（3）和每个推进推进器（4）的至少一个动力装置。 所述方法用于调节所述半翼（11,11'）的升力和水平稳定器（20）的升力，使得所述主转子（3）的所述叶片（31）的总间距等于 使得所述主转子（3）的所述叶片（31）的纵向循环间距等于设定点纵向循环间距，并且使得所述主转子的所述叶片（31）的横向循环间距（ 3）在稳定的飞行阶段等于设定值侧向循环间距。
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45.发明授权Method of operating actuators simultaneously for moving aircraft flaps, an aircraft flap drive device, and an aircraft provided with such a device 有权同时操作致动器的方法，用于移动飞机襟翼，飞行器襟翼驱动装置以及设置有这种装置的飞机公开(公告)号：US09114872B2
公开(公告)日：2015-08-25
申请号：US14002062
申请日：2012-02-29
CPC分类号： B64C13/16 , B64C13/50 , B64C13/503 , B64D45/00 , B64D2045/001
摘要： A method of operating actuators simultaneously for moving at least two aircraft movable aerodynamic surfaces, the method comprising the steps of: controlling the actuators to move the aerodynamic surfaces towards a predetermined position; during the movement, detecting a slowest actuator; and adapting the control of the actuators to match the actions of the slowest actuator. A drive device for aerodynamic surfaces and an aircraft including such a device.
摘要翻译： 一种同时操作致动器的方法，用于移动至少两个飞行器可移动空气动力学表面，该方法包括以下步骤：控制致动器将空气动力学表面朝向预定位置移动; 在运动期间，检测到最慢的执行器; 并适应致动器的控制以匹配最慢致动器的动作。 用于空气动力学表面的驱动装置和包括这种装置的飞行器。
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公开(公告)号：US20150021430A1
公开(公告)日：2015-01-22
申请号：US14507228
申请日：2014-10-06
CPC分类号： B64C27/52 , B64C3/42 , B64C5/02 , B64C9/00 , B64C13/16 , B64C25/10 , B64C29/00 , B64C29/0033 , B64C29/0091 , B64C29/02 , B64C29/04 , B64C39/024 , B64C2201/021 , B64C2201/088 , B64C2201/102 , B64C2201/108 , B64C2201/162 , B64C2201/187 , B64D27/02 , B64D43/00
摘要： A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends.
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47.发明申请公开(公告)号：US20140350754A1
公开(公告)日：2014-11-27
申请号：US13901089
申请日：2013-05-23
IPC分类号： G08G5/02
摘要： A system and method of generating a landing trajectory for use in landing an aircraft onto a deck of a waterborne ship includes sensing motion of the ship, and sensing wind speed and wind direction. The sensed motion of the ship is processed to generate estimates of ship attitude and vertical speed, and the sensed wind speed and wind direction are processed to generate estimates of air-wake disturbances ahead of the aircraft. The landing trajectory is generated based on the estimates of ship attitude and vertical speed and the estimates of air-wake disturbances. The system and method implement model predictive control to calculate the control maneuvers multiple steps ahead, which provides the capability to smoothly control the timing of the aircraft touchdown phase.
摘要翻译： 一种生成用于将飞机着陆在水上船的甲板上的着陆轨迹的系统和方法包括感测船舶的运动，以及感测风速和风向。 对船舶的感测运动进行处理以产生船舶姿态和垂直速度的估计，并且处理感测到的风速和风向以产生飞机之前的空气 - 苏醒干扰的估计。 基于船舶姿态和垂直速度的估计以及空气 - 尾流扰动的估计值，生成着陆轨迹。 该系统和方法实现模型预测控制，以计算控制操纵前进多个步骤，提供平滑控制飞机着陆阶段时间的能力。
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48.发明授权Structural health management with active control using integrated elasticity measurement 有权结构健康管理与主动控制使用综合弹性测量公开(公告)号：US08880242B2
公开(公告)日：2014-11-04
申请号：US13153469
申请日：2011-06-06
CPC分类号： B64D45/00 , B64C13/16 , B64D2045/0085 , G01L1/26 , G01M5/0041 , G01P15/00 , G05D1/0066 , G05D1/0204 , G07C5/08 , G07C5/0841
摘要： A system and method for actively controlling a structure is disclosed. At least one non-optimal event is identified in real-time based on at least one real-time elasticity measurement, if an event threshold exceeds a predetermined value. In response to an active control command, a control mechanism is then activated in real-time to compensate for the non-optimal event.
摘要翻译： 公开了一种用于主动控制结构的系统和方法。 如果事件阈值超过预定值，则基于至少一个实时弹性测量来实时地识别至少一个非最优事件。 响应于主动控制命令，然后实时地激活控制机构以补偿非最优事件。
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公开(公告)号：US20140306067A1
公开(公告)日：2014-10-16
申请号：US14173746
申请日：2014-02-05
发明人： Nicholas R. Guida
IPC分类号： B64C23/06
CPC分类号： B64C13/16 , B64C23/076 , Y02T50/164 , Y02T50/44
摘要： An active wing extension includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes multiple controllable airflow modification devices coupled thereto. By virtue of having multiple controllable airflow modification devices, the wing extension is capable of adjusting control surfaces of the multiple controllable airflow modification devices in response to in-flight conditions, to reduce wing loads, improve wing fatigue characteristics, increase range, reduce torsional loads, alleviate flutter, and/or increase efficiency.
摘要翻译： 主动翼延伸部包括基本上平行于飞行器的翼的主体部分，好像它是机翼的延伸部分。 主体部分可附接到飞行器机翼并且包括耦合到其上的多个可控气流改变装置。 由于具有多个可控气流改变装置，机翼延伸部能够响应于飞行中的条件来调节多个可控气流改变装置的控制表面，以减少机翼载荷，改善机翼疲劳特性，增加范围，减少扭转载荷 ，减轻颤动，和/或提高效率。
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公开(公告)号：US08788122B1
公开(公告)日：2014-07-22
申请号：US13594446
申请日：2012-08-24
CPC分类号： B64C23/076 , B64C13/16 , G05D1/0066 , G05D1/0808 , Y02T50/164
摘要： Wing load alleviation methods and apparatus are disclosed. An example method includes collecting data related to a condition of an aircraft; and when a condition identifier implemented via a logic circuit indicates that the condition comprises a high load condition, automatically generating a plurality of control signals to coordinate a first deflection of a first control surface of a configurable winglet and a second deflection of a second control surface of a wing adjacent to the winglet.
摘要翻译： 披露了翼载荷减轻方法和装置。 一种示例性方法包括收集与飞行器的状况有关的数据; 并且当通过逻辑电路实现的条件标识符指示条件包括高负载条件时，自动产生多个控制信号以协调可配置小翼的第一控制表面的第一偏转和第二控制表面的第二偏转 靠近小翼的翼。
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