公开(公告)号：US20110276226A1

公开(公告)日：2011-11-10

申请号：US13099450

申请日：2011-05-03

Applicant: David LEMAY ,  David FRANK ,  Michel BASSET ,  Yann CHAMAILLARD

Inventor： David LEMAY ,  David FRANK ,  Michel BASSET ,  Yann CHAMAILLARD

IPC: G05D1/02 ,  B64C25/50

CPC classification number: G05D1/0083 ,  B64C25/405 ,  Y02T50/823

Abstract: The invention relates to a management method for managing a turning movement of an aircraft taxiing on the ground, the aircraft having wheels each fitted with an independent drive device, in which method commands are generated for the independent drive devices so that at least some of those devices contribute to the turning movement. According to the invention, the method comprises the steps of: estimating at each instant during the turning movement: an instantaneous total power developed by all of the independent drive devices in response to the commands; and an instantaneous mean angular acceleration for all of the wheels; and adapting the commands to the independent drive devices such that the total instantaneous power developed by all of the independent drive devices is minimized, while conserving the mean angular acceleration.

Abstract translation: 本发明涉及一种用于管理在地面上滑行的飞行器的转动运动的管理方法，所述飞机具有各自装配有独立驱动装置的轮子，在该方法中为独立驱动装置生成指令，使得至少一些 装置有助于转弯运动。 根据本发明，该方法包括以下步骤：在转动运动期间的每个瞬间估计：由所有独立驱动装置响应命令产生的瞬时总功率; 和所有车轮的瞬时平均角加速度; 并且使命令适应独立的驱动装置，使得由所有独立驱动装置产生的总瞬时功率最小化，同时节省平均角加速度。

公开(公告)号：US20120072057A1

公开(公告)日：2012-03-22

申请号：US13237402

申请日：2011-09-20

Applicant: David LEMAY ,  David FRANK ,  Michel BASSET ,  Yann CHAMAILLARD

Inventor： David LEMAY ,  David FRANK ,  Michel BASSET ,  Yann CHAMAILLARD

IPC: G05D1/02

CPC classification number: G05D1/0083

Abstract: The invention relates to a method of managing movement of an aircraft on the ground, the aircraft including at least one left main undercarriage and at least one right main undercarriage, each comprising wheels associated with torque application members for applying torque to the wheels in response to a general setpoint, the general setpoint comprising a longitudinal acceleration setpoint and an angular speed setpoint, the method including the successive steps of braking down the general setpoint into general torque setpoints for generating by the torque application members associated with each of the wheels.

Abstract translation: 本发明涉及一种管理飞机在地面上的运动的方法，飞行器包括至少一个左主起落架和至少一个右主起落架，每个副底盘包括与扭矩施加构件相关联的轮，用于响应于 通用设定点，所述总设定点包括纵向加速度设定点和角速度设定点，该方法包括将通用设定值制动到通用转矩设定点的连续步骤，用于由与每个车轮相关联的转矩施加构件产生。

公开(公告)号：US20110187180A1

公开(公告)日：2011-08-04

申请号：US13019787

申请日：2011-02-02

Applicant: David FRANK

Inventor： David FRANK

IPC: B64C25/44 ,  B60T11/28

CPC classification number: B60T11/28 ,  B64C25/44

Abstract: A hydraulic braking architecture for aircraft comprising a plurality of wheels fitted with brakes, each including two half-cavities, the architecture comprising: a first braking circuit including servovalves, each powering one or more half-cavities on separate brakes; and a second braking circuit including servovalves, each powering one or more half-cavities on separate brakes; both hydraulic circuits operating simultaneously in such a manner that on each brake, one of the half-cavities is powered by a servovalve of the first braking circuit, and the other half-cavity is powered by a servovalve of the second braking circuit, at least one of the half-cavities being powered by a servovalve that powers only said half-cavity.

Abstract translation: 一种用于飞行器的液压制动架构，其包括装配有制动器的多个车轮，每个车轮包括两个半空腔，该结构包括：第一制动电路，其包括伺服阀，每个驱动单元为分离的制动器上的一个或多个半空腔供电; 以及包括伺服阀的第二制动回路，每个伺服阀为分开的制动器上的一个或多个半腔供电; 两个液压回路同时工作，使得在每个制动器上，其中一个半腔由第一制动回路的伺服阀供电，而另一个半腔由第二制动回路的伺服阀提供动力，至少 一个半腔由仅对所述半腔功率的伺服阀供电。

公开(公告)号：US20110100770A1

公开(公告)日：2011-05-05

申请号：US12916200

申请日：2010-10-29

Applicant: David FRANK

Inventor： David FRANK

IPC: B64C25/44 ,  F16D65/34

CPC classification number: B60T13/741 ,  B60T8/1703 ,  B60T8/885 ,  B60T2270/413 ,  B64C25/44

Abstract: The invention relates to an architecture for powering aircraft brakes for an aircraft having at least two undercarriages, each having a certain number of wheels (L1, L2; R1, R2), each of the wheels being fitted with a brake having a certain number of electromechanical braking actuators (1, 2, 3, 4). The architecture has at least four power supply units that power groups of actuators taken from complementary groups of wheels.

Abstract translation: 本发明涉及一种用于为具有至少两个起落架的飞行器提供飞机制动器的架构，每个底盘具有一定数量的车轮（L1，L2; R1，R2），每个车轮装配有具有一定数量的 机电制动执行器（1,2,3,4）。 该架构至少有四个电源单元，这些电源组是从互补的轮组获取的致动器组。

公开(公告)号：US20120223572A1

公开(公告)日：2012-09-06

申请号：US13411810

申请日：2012-03-05

Applicant: David FRANK

Inventor： David FRANK

IPC: B64C25/44 ,  B60T13/58

CPC classification number: B60T8/00 ,  B60T13/662 ,  B60T13/686 ,  B64C25/44

Abstract: Aircraft hydraulic parking architecture, including a brake with a wheel braking hydraulic actuator, a pressure source (Alim) of high-pressure fluid, a normal braking hydraulic circuit (C1) including at least pressure control servo valve with a supply port (P) connected to the pressure source (Alim), a return port (R), a utilization port (U) connected to the actuator, the brake architecture further including a parking hydraulic circuit (C2) including a parking brake valve (PkBV) having an outlet port (Ps1) selectively connected either to the pressure source (Alim) or a low-pressure return circuit (CR).The outlet port (Ps1) of the parking brake valve (PkBV) is connected to the return port (R) of the pressure control servo valve.

Abstract translation: 飞机液压停车架构，包括具有车轮制动液压致动器的制动器，高压流体的压力源（Alim），至少包括压力控制伺服阀的正常制动液压回路（C1），其中连接有供给口（P） 压力源（Alim），返回端口（R），与致动器连接的利用口（U），制动结构还包括驻车液压回路（C2），其包括驻车制动阀（PkBV），其具有出口 （Ps1）选择性地连接到压力源（Alim）或低压回路（CR）。 驻车制动阀（PkBV）的出口（Ps1）连接到压力控制伺服阀的返回口（R）。

公开(公告)号：US20080203217A1

公开(公告)日：2008-08-28

申请号：US11965413

申请日：2007-12-27

Applicant: David FRANK

Inventor： David FRANK

IPC: B64C25/50

CPC classification number: B64C25/50 ,  B64F1/22

Abstract: The invention relates to a method for managing a steering control of an aircraft landing gear provided with at least one wheel steerable by the steering control, comprising the following steps: monitoring one or several taxi parameter(s) (51, 54, 64, 59, 61) of the aircraft to determine whether said aircraft enters a towing situation, setting the steering control in a free steering mode of the steerable wheel, if the aircraft enters the towing situation; activating the steering control so that the steerable wheel has an angular controlled steering by the steering control if the aircraft leaves said towing situation.

Abstract translation: 本发明涉及一种用于管理飞行器起落架的转向控制的方法，该飞机起落架设有至少一个由转向控制器控制的轮子，包括以下步骤：监测一个或多个出租车参数（51,54,64,59 ，61），以确定所述飞机是否进入牵引状态，如果飞机进入牵引状态，则将转向控制设置在可转向轮的自由转向模式中; 激活转向控制，使得如果飞机离开所述拖曳状态，则可转向轮具有通过转向控制的角​​度控制的转向。

公开(公告)号：US20110100769A1

公开(公告)日：2011-05-05

申请号：US12914492

申请日：2010-10-28

Applicant: David FRANK

Inventor： David FRANK

IPC: B64C25/44 ,  F16D65/34

CPC classification number: B60T8/1703 ,  B60T2270/413 ,  B64C25/44

Abstract: The invention relates to an architecture for powering aircraft brakes for an aircraft having at least two undercarriages, each having a certain number of wheels, each of the wheels being fitted with brakes, each having a certain number of electromechanical braking actuators, the architecture including controllers for delivering power signals to the actuators in response to a braking order, the wheels on each of the undercarriages being grouped together in first and second complementary groups such that for each group of wheels, a first group of actuators is controlled by one controller that controls those actuators only, and a complementary second group of actuators is controlled by another controller that controls only those actuators.

Abstract translation: 本发明涉及一种用于为具有至少两个底盘的飞行器制动器供电的架构，每个具有一定数量的轮子，每个车轮装配有制动器，每个制动器具有一定数量的机电制动致动器，该架构包括控制器 用于响应于制动顺序将功率信号传递到致动器，每个底盘上的车轮在第一和第二互补组中被分组在一起，使得对于每组车轮，第一组致动器由一个控制器控制 只有那些执行器和互补的第二组致动器由仅控制那些致动器的另一控制器控制。