公开(公告)号：WO2012168086A3

公开(公告)日：2012-12-13

申请号：PCT/EP2012/059718

申请日：2012-05-24

Applicant: EADS DEUTSCHLAND GMBH ,  WILDSCHEK, Andreas

Inventor： WILDSCHEK, Andreas

IPC: B64C13/16 ,  G05D1/00 ,  G05D1/02 ,  G05D1/06

Abstract: The invention provides a method of dynamically alleviating loads generated on an aircraft (2) by a disturbance of gust and/or turbulence, the method comprising the steps of: on a flight of the aircraft (2), a monitoring is applied for automatically detecting a disturbance due to gust and/or turbulence and determining an incidence angle or angle of attack of the disturbance; when a disturbance due to gust and/or turbulence is detected, automatically generating control commands (36; 32, 38, 40, 42) for deflecting control surfaces dependent on the incidence angle or angle of attack; and applying the control commands (36; 32, 38, 40, 42) to deflect the control surfaces. For optimizing the performance, it is proposed to conduct at least one of the following step sequences A) and/or B): A) adapting the control commands (36; 32, 38, 40, 42) not only to the amount of the incidence angle or angle of attack but also to the gust length in order to adapt the deflection of the control surfaces both to the incidence angle or angle of attack and the gust length; and/or B) generating first control commands (y, 34; 32, 38) for first control surfaces and second control commands (36; 32, 38, 40, 42) for second control surfaces, comparing the incidence angle or angle of attack with a predetermined value and generating the first control commands (y, 34; 32, 38) to actuate the first control surface until the incidence angle reaches this predetermined value and generating the second control commands (36; 32, 38, 40, 42) to add a deflection of the second control surfaces when the incidence angle or angle of attack is above the predetermined value.

公开(公告)号：WO2011068659A2

公开(公告)日：2011-06-09

申请号：PCT/US2010/056586

申请日：2010-11-12

Applicant: GUIDA ASSOCIATES CONSULTING, INC. ,  GUIDA, Nicholas, R.

Inventor： GUIDA, Nicholas, R.

IPC: B64C23/06 ,  B64C3/56 ,  B64C5/10 ,  B64C13/16

CPC classification number: B64C23/065 ,  B64C13/16 ,  B64C23/076 ,  Y02T50/164

Abstract: An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing, and an angled portion that projects at an upward angle from the body portion. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and increase efficiency.

Abstract translation: 主动小翼包括基本平行于飞行器机翼的主体部分，就好像它是机翼的延伸部分，以及倾斜部分，其从主体部分以向上角度突出。 本体部分可附接到飞机机翼并且包括与其耦合的可控气流修改装置。 通过具有可控的气流改变装置，小翼能够根据飞行中的条件调整可控气流改变装置的控制表面，以减少机翼载荷，增加范围并提高效率。

公开(公告)号：WO2011052822A1

公开(公告)日：2011-05-05

申请号：PCT/KR2009/006300

申请日：2009-10-29

Applicant: 한국지질자원연구원 ,  조성준 ,  박종서 ,  박계순

Inventor： 조성준 ,  박종서 ,  박계순

IPC: B64B1/06 ,  B64C13/16 ,  B64D47/00 ,  B25J5/00

CPC classification number: G01R33/0385 ,  B64B1/06 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/127 ,  B82Y25/00 ,  G01R33/038

Abstract: 본 발명은 자력탐사용 휴대용 무인비행선 및 이를 이용한 자력탐사 시스템에 관한 것으로, 기체의 부력을 이용하며 자체 동력으로 추진하는 비행선 본체; 상기 비행선 본체를 자동으로 운항시키기 위한 자동운항장치; 상기 비행선 본체에 설치되며 지표나 지층의 자력을 측정하기 위한 자력측정장치; 상기 자력측정장치를 통해 획득된 자기데이터를 외부로 송신하기 위한 무선통신장치; 및 상기 자동운항장치 및 상기 자력측정장치의 작동을 제어하기 위한 제어모듈; 을 포함한다. 이에 따라, 무인비행선의 전체적인 운항시간을 늘릴 수 있으며, 무인비행선에 적재되는 페이로드(payload)의 하중을 늘릴 수 있는 기술이 개시된다.

Abstract translation: 本发明涉及一种用于磁力测量的便携式无人飞艇和采用该方法的磁力测量系统，包括：使用气体浮力在其自身动力下推进的主飞艇身体; 用于自动飞行主飞艇身体的自动飞行装置; 磁力测量装置，设在主飞艇身上，用于测量地球表面或地质层的磁力; 用于将经由磁力测量装置获取的磁数据发送到外部的无线通信装置; 以及用于控制自动飞行装置和磁力测量装置的操作的控制模块。 因此，公开了能够增加无人飞艇的总飞行时间并且可以增加载入无人飞艇上的载荷的重量的技术。

公开(公告)号：WO2010011388A2

公开(公告)日：2010-01-28

申请号：PCT/US2009/042398

申请日：2009-04-30

Applicant: THE BOEING COMPANY ,  NAJMABADI, Kioumars ,  SHIVITZ, William, F. ,  COLEMAN, Edward, E. ,  HO, John, K. ,  JOHNSON, Richard, D. ,  CARVER, William, F. ,  GRUBB, David, W. ,  MCINTOSH, Robert, J.

Inventor： NAJMABADI, Kioumars ,  SHIVITZ, William, F. ,  COLEMAN, Edward, E. ,  HO, John, K. ,  JOHNSON, Richard, D. ,  CARVER, William, F. ,  GRUBB, David, W. ,  MCINTOSH, Robert, J.

IPC: B64C13/16 ,  B64C13/50 ,  G05D1/08

CPC classification number: B64C13/16 ,  B64C13/503 ,  Y02T50/44

Abstract: A computer implemented method, apparatus, and computer usable program product for symmetric and anti-symmetric control of aircraft flight control surfaces to reduce wing-body loads. Commands are sent to symmetrically deploy outboard control surfaces to shift wing air-loads inboard based on airplane state and speed brake deployment. Surface rate retraction on a wing with peak loads is limited to reduce maximum loads due to wheel checkback accompanied by utilization of opposite wing control surfaces to retain roll characteristics. Airloads are shifted inboard on a swept wing to move the center of pressure forward, thereby reducing the tail load required to perform a positive gravity maneuver. In a negative gravity maneuver, speed brakes are retracted, thereby reducing the positive tail load and reducing the aft body design loads. High gain feedback commands are filtered from wing structural modes above one hertz by a set of linear and non-linear filters.

Abstract translation: 一种用于对称和反对称控制飞机飞行控制表面以减少机翼载荷的计算机实现的方法，装置和计算机可用程序产品。 根据飞机状态和加速制动器部署，命令被发送到对称地部署外侧控制表面，以机翼内空气载荷向内侧移动。 带有峰值载荷的机翼上的表面速度收缩受到限制，以减少由于车轮反馈而产生的最大载荷，同时利用相对的机翼控制表面来保持滚动特性。 空中载荷在掠翼上向内侧移动以向前移动压力中心，由此减小执行正向重力机动所需的尾部载荷。 在负重力机动中，减速器将缩回，从而减少正尾负载并减小尾部车身设计载荷。 高增益反馈命令通过一组线性和非线性滤波器从一赫兹以上的机翼结构模式滤除。

公开(公告)号：WO2009053649A8

公开(公告)日：2009-12-17

申请号：PCT/FR2008051869

申请日：2008-10-16

Applicant: AIRBUS FRANCE ,  JOURNADE JEROME

Inventor： JOURNADE JEROME

IPC: B64C9/12 ,  B64C13/16 ,  B64C23/06

CPC classification number: B64C23/06 ,  B64C9/12 ,  B64C13/16 ,  Y02T50/162

Abstract: The invention relates to a method and a device for creating a continuous protected space along the path of an aircraft (1), in which protected space a maximum induced speed Vtc in a vortex (3) of radius Rtc in the wake of an aircraft (1) is decreased by increasing the radius Rtc. The method comprises - a preliminary step of identifying changes in the aerodynamic configurations of the aircraft (1) liable to initiate disruptions in the wake that will have the effect of increasing the radius Rtc, - for each change in configuration determining beforehand the characteristics of propagation of the wake disturbances in the vortex (3), - carrying out, along the course of the aircraft (1), at least two configuration changes separated by a distance such that spaces, in which the effects of the wake disturbances resulting from each of the configuration changes propagated for a predetermined length of time, forms a substantially continuous protected space

Abstract translation: 本发明涉及一种用于沿着飞机（1）的路径创建连续受保护空间的方法和设备，其中受保护空间在飞机尾部（RTC）中具有半径Rtc的涡旋（3）中的最大感应速度Vtc 1）通过增加半径Rtc而减小。 该方法包括 - 识别飞机（1）的空气动力学配置中的变化的初步步骤，其容易在尾流中引起中断，这将具有增加半径Rtc的效果， - 对于预先确定传播特性的每个配置变化 - 涡流（3）中的尾流扰动， - 沿着飞机（1）的走向实现至少两个由距离分开的配置变化，以使得空间（其中由每个 配置变化传播预定的时间长度，形成基本上连续的保护空间

公开(公告)号：WO2009079178A2

公开(公告)日：2009-06-25

申请号：PCT/US2008/084745

申请日：2008-11-25

Applicant: THE BOEING COMPANY ,  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

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：WO2008110384B1

公开(公告)日：2008-12-11

申请号：PCT/EP2008002100

申请日：2008-03-17

Applicant: AIRBUS GMBH ,  HOLZHAUSEN TORSTEN

Inventor： HOLZHAUSEN TORSTEN

IPC: B64C13/16

CPC classification number: B64C9/04 ,  B64C13/16 ,  B64C13/38

Abstract: The invention relates to a method for actuating an adjusting drive for adjusting an elevator (12) and an adjusting drive for adjusting a moveable tail (23) provided with the steps : Generation of an elevator command to actuate the elevator adjusting drive; Calculating a moveable tail command (IHCl) for actuating the moveable tail adjusting drive in such a manner that the moveable tail (23) is tracked to the elevator input signal (10); Depending on the adjusting states of the elevator (12) and/or the moveable tail (23) or flight states, retaining the adjusting state of the moveable tail adjusting drive or actuating the moveable tail adjusting drive with a moveable tail command (IHCMD) for changing the adjusting state of the moveable tail (23), during actuation of the elevator adjusting drive with an elevator command for changing the adjusting state of the elevator (23) and in the event of a deviation from the calculated moveable tail command (IHCl) and the commanded moveable tail command (IHCMD), acting upon the elevator command to compensate for retention of the adjusting state of the moveable tail adjusting drive and a control device for carrying out the method.

Abstract translation: 本发明涉及一种用于致动用于调节电梯（12）的调节驱动器的方法以及一种用于调节可移动尾部（23）的调节驱动器，该调节驱动器设置有以下步骤：产生用于致动升降机调节驱动器的升降机命令; 计算可移动的尾部命令（IHC1），用于以可移动的尾部（23）跟踪到升降机输入信号（10）的方式致动可移动的尾部调整驱动器; 根据电梯（12）和/或可移动尾部（23）或飞行状态的调节状态，保持可移动尾部调节驱动装置的调节状态或用可移动尾部调节驱动装置（IHCMD）驱动可移动尾部调节驱动装置 在利用用于改变电梯（23）的调节状态的电梯命令启动电梯调节驱动装置期间以及在与计算的可移动尾部命令（IHC1）偏离的情况下改变可移动尾部（23）的调节状态， 以及作用于电梯命令以补偿可移动尾部调节驱动装置的调节状态的保持的命令的可移动尾部命令（IHCMD）以及用于执行该方法的控制装置。

公开(公告)号：WO2008137217A2

公开(公告)日：2008-11-13

申请号：PCT/US2008057309

申请日：2008-03-18

Applicant: SIKORSKY AIRCRAFT CORP ,  CHEREPINSKY IGOR ,  SKAGGS MICHAEL R

Inventor： CHEREPINSKY IGOR ,  SKAGGS MICHAEL R

IPC: B64C13/16 ,  B64C13/00

CPC classification number: G05D1/0858 ,  B64C13/503 ,  B64C27/04 ,  G05D1/0607

Abstract: A flight control system includes a collective position command algorithm for a lift axis (collective pitch) which, in combination with an active collective system, provides a force feedback such that a pilot may seamlessly command vertical speed, flight path angle or directly change collective blade pitch. The collective position command algorithm utilizes displacement of the collective controller to command direct collective blade pitch change, while a constant force application to the collective controller within a "level flight" detent commands vertical velocity or flight path angle. The "level flight" detent provides a tactile cue for collective position to reference the aircraft level flight attitude without the pilot having to refer to the instruments and without excessive collective controller movement.

Abstract translation: 飞行控制系统包括用于提升轴（集体俯仰）的集体位置命令算法，其与主动集合系统组合提供力反馈，使得飞行员可以无缝地命令垂直速度，飞行路径角度或直接改变集体叶片 沥青。 集体位置命令算法利用集体控制器的位移来命令直接集体叶片桨距变化，而在“水平飞行”制动器内的集体控制器的恒力施加命令垂直速度或飞行路径角度。 “级别飞行”制动器提供了集体立场的触觉提示，以引用飞机水平飞行姿态，而飞行员必须参考仪器，没有过度的集体控制器移动。

公开(公告)号：WO2008127854A2

公开(公告)日：2008-10-23

申请号：PCT/US2008/058285

申请日：2008-03-26

Applicant: THE BOEING COMPANY ,  ONU, Dan ,  WINTER, John D. ,  CARR, Candy L. ,  VIJGEN, Paul M. ,  EMCH, Gary A. ,  RENZELMANN, Michael E.

Inventor： ONU, Dan ,  WINTER, John D. ,  CARR, Candy L. ,  VIJGEN, Paul M. ,  EMCH, Gary A. ,  RENZELMANN, Michael E.

IPC: B64C9/12 ,  B64C13/16

CPC classification number: B64C9/12 ,  Y02T50/32 ,  Y02T50/44

Abstract: The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity, vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.

Abstract translation: 在给定的飞行阶段期间，在变化的条件下，动态地调整影响机翼弧度的可移动表面，以优化机翼弧度以获得最佳升力/牵引比。 在优选实施例中，附加动态调节控制模块提供用于最终定位后缘可移动表面（即，内侧翼片，外侧翼片，副翼和襟翼）的命令信号，其用于代替标准的预定位置 飞行控制系统。 动态调整控制模块利用改变飞行器条件的输入，如高度，马赫数，重量，重心，垂直速度和飞行阶段。 动态调整控制模块用于重新定位机翼的可移动表面的命令通过标准飞行控制系统传输到用于移动飞行控制表面的致动器。

公开(公告)号：WO2008031620A3

公开(公告)日：2008-05-08

申请号：PCT/EP2007008038

申请日：2007-09-15

Applicant: AIRBUS GMBH ,  UNIV MUENCHEN TECH ,  BREITSAMTER CHRISTIAN ,  ALLEN ALEXANDER

Inventor： BREITSAMTER CHRISTIAN ,  ALLEN ALEXANDER

IPC: B64C23/06 ,  B64C5/10 ,  B64C13/16

CPC classification number: B64C13/16 ,  B64C23/076 ,  Y02T50/164

Abstract: The invention relates to an aerodynamic body (4) for applying to a carrier wing on which at least two flow flaps (5a, 5b) adjacently arranged in the longitudinal direction of the aerodynamic body are mounted, to a carrier wing comprising a main carrier wing (2) and the at least one additional aerodynamic body, and to a computer comprising an actuating drive control module which generates time-variable command signals for actuating drives. The actuating drive control module has a function which, when activated, generates at least two oscillatory command signals on each actuator drive, said signals being in opposition of phase. The invention also relates to a computer program for implementing in a computer with an actuating drive control module, to a method for influencing command signals for an actuating drive system, and to combinations of such a computer with an actuating drive control module, a carrier wing, and at least one actuating drive.

Abstract translation: 流线型体（4）用于附连到在其中在流线型体并列流翼片的长度方向的至少两个（5A，5B）被布置的翼型; 翼包括主翼（2）和所述至少一个附加的流线型体; 用于致动器包括致动器-Ansteuermodul，时间改变命令，其中，所述致动器的激活产生了由于它们的活化的相应的致动器，这是在相彼此相对的至少两个振荡指令信号的功能的计算机产生的信号; 在与致动器激活的计算机执行的计算机程序; 一种用于致动器系统影响命令信号的方法; 与致动器激活，翼型件和至少一个致动器这样的计算机的组合。