公开(公告)号：WO2016057098A2

公开(公告)日：2016-04-14

申请号：PCT/US2015040607

申请日：2015-07-15

Applicant: POSTREL RICHARD

Inventor： POSTREL RICHARD

IPC: G06F19/00 ,  B64C13/16

CPC classification number: G08G5/0043 ,  B64C39/024 ,  B64C2201/128 ,  B64C2201/145 ,  G05D1/101 ,  G08G5/0008 ,  G08G5/0013 ,  G08G5/0021 ,  G08G5/0026 ,  G08G5/0034 ,  G08G5/0039 ,  G08G5/0069 ,  H04W4/046

Abstract: A drone traffic management system comprising a computer comprising memory means for storing origin coordinates indicating an origin location of a drone, destination coordinates indicating a destination of the drone, and traffic management factors located between the origin location of the drone and the destination of the drone; and processing means for controlling the flight of a drone. This is accomplished by calculating a flight path for the drone to fly automatically from the origin location to the destination location without manual intervention, sending the flight path to the drone, receiving location data of the drone as it travels from the origin location to the destination, re-calculating the flight path of the drone as a function of the traffic management factors and the location data of the drone, and sending the re-calculated flight path to the drone.

Abstract translation: 一种无人驾驶交通管理系统，包括计算机，所述计算机包括用于存储指示无人机的原点位置的原点坐标，指示无人机的目的地的目的地坐标以及位于无人机的起始位置与无人机的目的地之间的交通管理因素的存储装置 ; 以及用于控制无人机飞行的处理装置。 这是通过计算无人机从起始位置到目的地位置的飞行路径而完成的，而无需手动干预，将飞行路径发送到无人机，从无人机从起始位置行进到目的地时接收无人机的位置数据 根据无人机的交通管理因素和位置数据重新计算无人机的飞行路径，并将重新计算的飞行路径发送到无人机。

公开(公告)号：WO2014106273A1

公开(公告)日：2014-07-03

申请号：PCT/US2013/078546

申请日：2013-12-31

Applicant: TELVENT DTN LLC

Inventor： MCCANN, Donald ,  BLOCK, James, H. ,  LENNARTSON, Daniel, W.

IPC: B64C13/16

CPC classification number: G08G5/0091 ,  G08G5/0013 ,  G08G5/0021 ,  G08G5/0034 ,  G08G5/0039

Abstract: The Dynamic Turbulence Engine Controller Apparatuses, Methods And Systems ("DTEC") transform weather, terrain, and flight parameter data via DTEC components into turbulence avoidance optimized flight plans. In one implementation, the DTEC comprises a processor and a memory disposed in communication with the processor and storing processor-issuable instructions to receive anticipated flight plan parameter data, obtain terrain data based on the flight plan parameter data, obtain atmospheric data based on the flight plan parameter data, and determine a plurality of four-dimensional grid points based on the flight plan parameter data. The DTEC may then determine a non-dimensional mountain wave amplitude and mountain top wave drag, an upper level non-dimensional gravity wave amplitude, and a buoyant turbulent kinetic energy. The DTEC determines a boundary layer eddy dissipation rate, storm velocity, and eddy dissipation rate from updrafts, maximum updraft speed at grid point equilibrium level and storm divergence while the updraft speed is above the equilibrium level and identify storm top. The DTEC determines storm overshoot and storm drag, Doppler speed, eddy dissipation rate above the storm top, and determine eddy dissipation rate from downdrafts. The DTEC then determines the turbulent kinetic energy for each grid point and identifies an at least one flight plan based on the flight plan parameter data and the determined turbulent kinetic energy.

Abstract translation: 动态湍流发动机控制器设备，方法和系统（“DTEC”）通过DTEC组件将天气，地形和飞行参数数据转换成湍流避免优化的飞行计划。 在一个实施方案中，DTEC包括处理器和与处理器通信的存储器，并且存储可处理器发出的指令以接收预期的飞行计划参数数据，基于飞行计划参数数据获得地形数据，基于飞行获得大气数据 计划参数数据，并且基于飞行计划参数数据确定多个四维网格点。 然后，DTEC可以确定无量纲山波振幅和山顶波阻力，上层无量纲重力波振幅和浮力湍动动能。 DTEC确定上升气流的边界层涡流耗散率，风速和涡流耗散率，网格点平衡水平下的最大上升气流速度和风向分歧，同时上升气流速度高于平衡水平，识别风暴顶部。 DTEC确定风暴过冲和风暴阻力，多普勒速度，风暴顶部以上的涡流耗散率，并确定来自下降的涡流耗散率。 DTEC然后确定每个网格点的湍流动能，并根据飞行计划参数数据和确定的湍流动能识别至少一个飞行计划。

公开(公告)号：WO2012052438A3

公开(公告)日：2013-03-07

申请号：PCT/EP2011068190

申请日：2011-10-18

Applicant: SAGEM DEFENSE SECURITE ,  BONNY FRANCK

Inventor： BONNY FRANCK

IPC: B64C13/50 ,  B64C13/16

CPC classification number: F01B25/00 ,  B64C13/503

Abstract: The invention relates to a system (100) for motorized displacement of a mobile element (200), comprising at least two actuators (1, 2) which are each provided with means for linking them to the mobile element and which are dimensioned so as to be able to manoeuvre only the mobile element, a central control unit (3) being connected to the two actuators so as to send each of the actuators a position setpoint (Pos1, Pos2). According to the invention, the system comprises control means (10, 20) for simultaneously controlling the two actuators in terms of load in response to the position setpoint dispatched to one of the actuators. The invention also relates to a method of driving such a system and a method of testing such a system.

Abstract translation: 本发明涉及一种用于移动元件（200）的电动移位的系统（100），包括至少两个致动器（1,2），每个致动器（1,2）设置有用于将它们连接到移动元件的装置， 能够仅操纵移动元件，中央控制单元（3）连接到两个致动器，以便将每个致动器发送到位置设定点（Pos1，Pos2）。 根据本发明，系统包括控制装置（10,20），用于响应于调度到一个致动器的位置设定装置，在负载方面同时控制两个致动器。 本发明还涉及一种驱动这种系统的方法和测试这种系统的方法。

公开(公告)号：WO2012083792A1

公开(公告)日：2012-06-28

申请号：PCT/CN2011/083558

申请日：2011-12-06

Applicant: 中国商用飞机有限责任公司 ,  中国商用飞机有限责任公司上海飞机设计研究院 ,  赵京洲 ,  徐德胜 ,  马显超 ,  廖军辉 ,  金荣深 ,  田金强

Inventor： 赵京洲 ,  徐德胜 ,  马显超 ,  廖军辉 ,  金荣深 ,  田金强

IPC: G01P1/04 ,  G05D1/08 ,  B64C13/16

CPC classification number: G01M99/008 ,  B64F5/60

公开(公告)号：WO2011134924A2

公开(公告)日：2011-11-03

申请号：PCT/EP2011/056514

申请日：2011-04-26

Applicant: AIRBUS OPERATIONS GMBH ,  KORDT, Michael

Inventor： KORDT, Michael

IPC: B64C13/16

CPC classification number: B64C13/16 ,  B64C9/34 ,  Y02T50/32 ,  Y02T50/44

Abstract: System and method for minimising buffeting in the case of an aircraft (2), wherein buffeting load control elements (10) which are provided in aerofoils of the aircraft (2) can be at least partly moved out of the aerofoils by a control means (1) to reduce buffeting loads acting on the aircraft (2).

Abstract translation: 在飞机（2）的情况下用于最小化抖振的系统和方法，其中设置在飞行器（2）的翼型中的抖振负载控制元件（10）可以至少部分地移出 通过控制装置（1）减少作用在飞机（2）上的抖振载荷。

公开(公告)号：WO2010105818A3

公开(公告)日：2010-12-16

申请号：PCT/EP2010001684

申请日：2010-03-17

Applicant: AIRBUS OPERATIONS GMBH ,  AIRBUS OPERATIONS SAS ,  WEBER CARSTEN ,  FISCHER MARKUS ,  NAMER ARNAUD

Inventor： WEBER CARSTEN ,  FISCHER MARKUS ,  NAMER ARNAUD

IPC: B64C9/36 ,  B64C13/16

CPC classification number: B64C5/06 ,  B64C9/32 ,  Y02T50/32

Abstract: An aircraft comprising a device for influencing the directional stability of the aircraft, which aircraft comprises: a control-input device; a flight control device; a sensor device for acquiring the rotation rates including the yaw rates, of the aircraft; - wherein the aircraft comprises two tail-mounted flaps (K1, K2), each comprising an actuator that is functionally connected with the flight control device, which tail-mounted flaps (K1, K2) are situated symmetrically to each other in relation to the vertical axis and on opposite sides of the fuselage and are movable between a retracted and an extended position, - wherein the control function is designed in such a manner that the adjusting commands that are generated on the basis of the control commands depending on the acquired rotation rates comprise adjusting commands to the actuators of the tail-mounted flaps (K1, K2) for their actuation, as well as a method for influencing the directional stability of the aircraft (F).

Abstract translation: 一种飞机，包括用于影响飞行器的方向稳定性的装置，该飞机包括：控制输入装置; 飞行控制装置; 用于获取包括飞行器的横摆速度的旋转速率的传感器装置; - 其中所述飞行器包括两个尾部安装的翼片（K1，K2），每个翼片包括与所述飞行控制装置功能性连接的致动器，所述尾部安装的翼片（K1，K2）相对于所述飞行控制装置彼此对称地定位 垂直轴线和机身的相对侧上并且可在缩回位置和延伸位置之间移动，其中控制功能被设计成使得根据所获取的旋转基于控制命令生成的调整命令 速率包括对用于其致动的尾部安装的翼片（K1，K2）的致动器的调节命令，以及用于影响飞行器（F）的方向稳定性的方法。

公开(公告)号：WO2009079178A3

公开(公告)日：2010-01-21

申请号：PCT/US2008084745

申请日：2008-11-25

Applicant: BOEING CO ,  WALTON VINCENT M ,  BORLAND CHRISTOPHER J ,  SIU TZE L ,  NAJMABADI KIOUMARS ,  COLEMAN EDWARD E ,  MARQUIS DAVID P ,  MCMULLIN DIANNE L ,  MILLIGAN KEVIN H

Inventor： WALTON VINCENT M ,  BORLAND CHRISTOPHER J ,  SIU TZE L ,  NAJMABADI KIOUMARS ,  COLEMAN EDWARD E ,  MARQUIS DAVID P ,  MCMULLIN DIANNE L ,  MILLIGAN KEVIN H

IPC: B64C13/16 ,  G05D1/06

CPC classification number: G05D1/046 ,  B64C13/16

Abstract: A method for vertical gust suppression due to turbulence for an aircraft having at least one of direct lift control surfaces or pitch control surfaces. The method includes sensing atmospheric turbulence, measuring the sensed atmospheric turbulence to generate turbulence data, generating a command based on the turbulence data, and applying the command to aircraft controls to actuate the direct lift control surfaces or the pitch control surfaces based on the turbulence data. Therefore, an aircraft response to the actuation of the direct lift control surfaces or the pitch control surfaces reduces a vertical acceleration, a pitch acceleration, a pitch rate, a pitch attitude or a structural load of the aircraft due to the turbulence. Thus, the method reduces the effects of vertical gusts of wind on the aircraft, improves the comfort level for aircraft passengers and crew, and reduces diversions the aircraft may take to avoid the turbulence.

Abstract translation: 一种用于具有直接提升控制表面或俯仰控制表面中的至少一个的飞行器由于湍流引起的垂直阵风抑制的方法。 该方法包括感测大气湍流，测量感测到的大气湍流以产生湍流数据，基于湍流数据生成命令，以及根据湍流数据将命令应用于飞行器控制器以致动直升机控制表面或桨距控制表面 。 因此，飞机对直升升控制表面或俯仰控制表面的致动的响应减少了由于湍流引起的飞行器的垂直加速度，俯仰加速度，俯仰速度，俯仰姿态或结构载荷。 因此，该方法减少了风向垂直阵风对飞机的影响，提高了飞机乘客和机组人员的舒适度，并减少了飞机可能采取的转向以避免湍流。

公开(公告)号：WO2009112213A1

公开(公告)日：2009-09-17

申请号：PCT/EP2009/001638

申请日：2009-03-06

Applicant: EADS DEUTSCHLAND GMBH ,  MAIER, Rudolf ,  WILDSCHEK, Andreas

Inventor： MAIER, Rudolf ,  WILDSCHEK, Andreas

IPC: B64C13/16 ,  F16F15/00

CPC classification number: F16F15/002 ,  B64C13/16

Abstract: Die Erfindung betrifft eine Schwingungsreduktionsvorrichtung zur Reduktion von Schwingungen eines Flugkörpers mit einer Regelungseinrichtung (101) zum Erzeugen zumindest eines Stellsignals für eine gemeinsame Reduktion von Strukturschwingungen und Starrkörperschwingungen auf der Basis von erfassten Strukturschwingungen und von erfassten Starrkörperschwingungen, wobei das Stellsignals die Strukturschwingungen und die Starrkörperschwingungen berücksichtigt.

Abstract translation: 本发明涉及一种减振装置具有用于产生至少一个驱动信号，用于结构振动和感测到的结构振动的和检测到的刚体振动的基础上，刚体振动的一个共同的减少的控制装置（101）减少飞行物体的振动，控制信号考虑了结构振动和刚体振动 ，

公开(公告)号：WO2009110943A9

公开(公告)日：2009-09-11

申请号：PCT/US2008/086791

申请日：2008-12-15

Applicant: MASSACHUSETTS INSTITUTE OF TECHNOLOGY ,  SPAKOVSZKY, Zoltan, S. ,  SHAH, Parthiv, N. ,  MOBED, Darius, D. ,  KERREBROCK, Jack, L.

Inventor： SPAKOVSZKY, Zoltan, S. ,  SHAH, Parthiv, N. ,  MOBED, Darius, D. ,  KERREBROCK, Jack, L.

IPC: B64C13/16

Abstract: Drag management structure. The structure includes a tube having an entrance and exit along a longitudinal axis. At least one row of stationary swirl generating vanes is provided at the entrance, the swirl vanes disposed at an angle with respect to the longitudinal axis selected to produce a steady streamwise vortex in a fluid at the tube exit. A fan rotor may be disposed upstream of the stationary vanes.

公开(公告)号：WO2009110943A2

公开(公告)日：2009-09-11

申请号：PCT/US2008086791

申请日：2008-12-15

Applicant: MASSACHUSETTS INST TECHNOLOGY ,  SPAKOVSZKY ZOLTAN S ,  SHAN PARTIV N ,  MOBED DARIUS D ,  KERREBROCK JACK L

Inventor： SPAKOVSZKY ZOLTAN S ,  SHAN PARTIV N ,  MOBED DARIUS D ,  KERREBROCK JACK L

IPC: B64C13/16

CPC classification number: B64C9/32 ,  B64C23/065 ,  B64D33/04 ,  B64D33/06 ,  Y02T50/164 ,  Y02T50/32

Abstract: Drag management structure. The structure includes a tube having an entrance and exit along a longitudinal axis. At least one row of stationary swirl generating vanes is provided at the entrance, the swirl vanes disposed at an angle with respect to the longitudinal axis selected to produce a steady streamwise vortex in a fluid at the tube exit. A fan rotor may be disposed upstream of the stationary vanes.

Abstract translation: 拖动管理结构。 该结构包括具有沿着纵向轴线的入口和出口的管。 在入口处设置至少一排固定涡流产生叶片，旋流叶片相对于纵向轴线成一角度设置，以在管出口处的流体中产生稳定的流动涡流。 风扇转子可以设置在静止叶片的上游。