公开(公告)号：US10023159B2

公开(公告)日：2018-07-17

申请号：US12955397

申请日：2010-11-29

Applicant: Anthony Sorin ,  David Lemay ,  Michel Basset ,  Yann Chamaillard

Inventor： Anthony Sorin ,  David Lemay ,  Michel Basset ,  Yann Chamaillard

IPC: B60T1/10 ,  B60T13/58

Abstract: A method of managing the braking of an aircraft having landing gear with wheels fitted with friction brakes and with auxiliary brakes that enable energy to be dissipated by other than friction. The method comprises the steps of, (1) when braking is requested, testing the braking parameters to determine whether the aircraft is in a braking situation for which the friction brakes are not essential for providing the requested braking, and (2) performing the requested braking by giving priority to actuating the auxiliary brakes so long as the aircraft remains within the braking situation, and actuating the friction brakes only if the aircraft departs from the braking situation.

公开(公告)号：US20150175257A1

公开(公告)日：2015-06-25

申请号：US14568185

申请日：2014-12-12

Applicant: Clement Gorce ,  David Lemay

Inventor： Clement Gorce ,  David Lemay

IPC: B64C25/40 ,  H02P23/00 ,  H02P29/00

CPC classification number: B64C25/405 ,  H02P23/0004 ,  H02P29/10 ,  Y02T50/823

Abstract: A control method for controlling an electric motor driving rotation of an aircraft wheel (4a, 4b) for generating a torque command for controlling the motor, the method being characterized in that it comprises implementing: a first servo-control loop (23) having as its input signal a speed setpoint, having as its return signal a signal representative of the speed of the wheel or of the aircraft, and having as its output signal an acceleration setpoint (Cons_a); and a second servo-control loop (24) having as its input signal the acceleration setpoint (Cons_a), as its return signal a signal representative of the acceleration (Ar) of the wheel or of the aircraft, and as its output signal the torque command.

Abstract translation: 一种用于控制用于产生用于控制所述电动机的转矩指令的飞行器轮（4a，4b）的电动机驱动旋转的控制方法，其特征在于包括实现：第一伺服控制回路（23），其具有 其输入信号为速度设定点，具有代表车轮或飞行器速度的信号，并具有作为其输出信号的加速度设定点（Cons_a）作为其返回信号; 作为其输入信号加速设定值（Cons_a）的第二伺服控制回路（24）作为其返回信号，表示车轮或飞行器的加速度（Ar）的信号，作为其输出信号的扭矩 命令。

公开(公告)号：US08584989B2

公开(公告)日：2013-11-19

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: G05D3/00

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：US20120046834A1

公开(公告)日：2012-02-23

申请号：US13211659

申请日：2011-08-17

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 ,  B64C25/50 ,  Y10T70/5664

Abstract: The invention relates to a method of controlling a yawing movement of an aircraft running along the ground, the aircraft comprising at least one first landing gear with a steerable bottom part bearing wheels. According to the invention, the method comprises the steps of: on the basis of a yaw rate setpoint {dot over (φ)}c, determining a wheel-steering prepositioning angle θp; using closed-loop control which as its input has the yaw rate setpoint and which generates a command to steer the bottom part in order to steer it through a steering angle θc equal to the sum of this prepositioning angle θp and of an angle θz which is determined taking account of an error between the yaw rate setpoint {dot over (φ)}c and the measured yaw rate {dot over (φ)}m when the steerable bottom part is steered by the steering angle θc.

Abstract translation: 本发明涉及一种控制沿着地面运行的飞行器的偏航运动的方法，该飞行器包括至少一个具有可转向的底部轴承轮的第一起落架。 根据本发明，该方法包括以下步骤：基于偏航率设定点{dot over（＆phgr;）} c，确定车轮导向预定位角; 使用闭环控制，其作为其输入具有横摆率设定点，并且产生用于引导底部的指令，以便引导其转向角度; c等于该预定位角与该点的和 考虑到横向速度设定点{dot over（＆phgr）} c与所测量的横摆率{dot over（＆phgr）} m之间的误差确定的角度和角度;当可转向的底部由转向 角度和角度; c。

公开(公告)号：US20110127828A1

公开(公告)日：2011-06-02

申请号：US12955397

申请日：2010-11-29

Applicant: Anthony SORIN ,  David Lemay ,  Michel Basset ,  Yann Chamaillard

Inventor： Anthony SORIN ,  David Lemay ,  Michel Basset ,  Yann Chamaillard

IPC: B64C25/42 ,  G06F19/00 ,  B64C25/44

CPC classification number: B60T1/10 ,  B60T13/586

Abstract: The invention relates to a method of managing the braking of an aircraft having landing gear with wheels fitted with friction brakes and with auxiliary brakes that enable energy to be dissipated by means other than friction, the method comprising the steps of: when braking is requested, testing the braking parameters to determine whether the aircraft is in a braking situation for which the friction brakes are not essential for providing the requested braking; and performing the requested braking by giving priority to actuating the auxiliary brakes so long as the aircraft remains within said braking situation, and actuating the friction brakes only if the aircraft departs from said braking situation.

Abstract translation: 本发明涉及一种管理具有起落架的飞行器的制动方法，所述起落架具有装配有摩擦制动器的轮子，以及辅助制动器，其能够通过摩擦以外的方式消耗能量，所述方法包括以下步骤：当要求制动时， 测试制动参数以确定飞机是否处于制动状态，摩擦制动器对于提供所要求的制动而言不是必需的; 并且只要飞机保持在所述制动状态内，优先执行辅助制动器来执行所要求的制动，并且只有在飞机离开所述制动状况时才致动摩擦制动器。

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：US09452826B2

公开(公告)日：2016-09-27

申请号：US14568185

申请日：2014-12-12

Applicant: Clement Gorce ,  David Lemay

Inventor： Clement Gorce ,  David Lemay

IPC: B64C25/40 ,  H02P29/00 ,  H02P23/00

CPC classification number: B64C25/405 ,  H02P23/0004 ,  H02P29/10 ,  Y02T50/823

Abstract: A control method for controlling an electric motor driving rotation of an aircraft wheel (4a, 4b) for generating a torque command for controlling the motor, the method being characterized in that it comprises implementing: a first servo-control loop (23) having as its input signal a speed setpoint, having as its return signal a signal representative of the speed of the wheel or of the aircraft, and having as its output signal an acceleration setpoint (Cons_a); and a second servo-control loop (24) having as its input signal the acceleration setpoint (Cons_a), as its return signal a signal representative of the acceleration (Ar) of the wheel or of the aircraft, and as its output signal the torque command.

公开(公告)号：US09134730B2

公开(公告)日：2015-09-15

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: A01B69/00 ,  B62D6/00 ,  B62D11/00 ,  B62D12/00 ,  B63G8/20 ,  B63H25/04 ,  G05D1/00 ,  G06F7/00 ,  G06F17/00 ,  G06F19/00 ,  B64C25/40

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，其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：US20050106296A1

公开(公告)日：2005-05-19

申请号：US10977540

申请日：2004-10-29

Applicant: Richard Merrill ,  David LeMay ,  Laura Colin-Diaz

Inventor： Richard Merrill ,  David LeMay ,  Laura Colin-Diaz

IPC: A23B4/00 ,  A23L20060101 ,  A23L33/20

CPC classification number: A23L33/20 ,  A23L5/11 ,  A23L5/20 ,  A23L29/045 ,  A23P20/12 ,  A23P20/18 ,  A23V2002/00 ,  A23V2200/3324 ,  A23V2250/54252

Abstract: Coatings containing one or more thermally coagulating proteins (e.g., whey protein) and foodstuffs coated with such coatings are provided. The coatings render foodstuffs less permeable to fat and oil in the frying medium, and thus reduce the amount of fat or oil absorbed by the foodstuff during cooking. The coatings also improve the color, texture and crispiness of the cooked foodstuff. Methods for applying such coatings to obtain the coated foodstuff are also provided.

Abstract translation: 提供了含有一种或多种热凝固蛋白（例如乳清蛋白）和涂覆有这种涂层的食品的涂层。 涂料使油炸介质中的油脂对食物的渗透性较差，从而减少烹饪过程中被食物吸收的脂肪或油的量。 涂层还可以改善熟食的颜色，质感和脆性。 还提供了涂覆这种涂层以获得涂覆食品的方法。

公开(公告)号：US08666598B2

公开(公告)日：2014-03-04

申请号：US13211659

申请日：2011-08-17

Applicant: David Lemay ,  David Frank ,  Michel Basset ,  Yann Chamaillard

Inventor： David Lemay ,  David Frank ,  Michel Basset ,  Yann Chamaillard

IPC: G05D1/00

CPC classification number: G05D1/0083 ,  B64C25/50 ,  Y10T70/5664

Abstract: A method of controlling a yawing movement of an aircraft running along the ground, the aircraft comprising at least one first landing gear with a steerable bottom part bearing wheels. The method comprises the steps of (1) on the basis of a yaw rate setpoint {dot over (φ)}c, determining a wheel-steering prepositioning angle θp; and (2) using closed-loop control which as its input has the yaw rate setpoint and which generates a command to steer the bottom part in order to steer it through a steering angle θc equal to the sum of this prepositioning angle θp and of an angle θz which is determined taking account of an error between the yaw rate setpoint {dot over (φ)}c and the measured yaw rate {dot over (φ)}m when the steerable bottom part is steered by the steering angle θc.

Abstract translation: 一种控制沿着地面运行的飞行器的偏航运动的方法，该飞行器包括至少一个具有可转向的底部轴承轮的第一起落架。 该方法包括以下步骤：（1）基于偏航率设定点{dot over（phi）} c，确定车轮导向预定位角; 和（2）使用闭环控制，其作为其输入具有横摆率设定点，并且产生用于引导底部的指令，以便通过转向角等于该预定位角和 考虑到当可转向底部通过转向角度转向时横摆率设定点{dot over（phi）} c和测量的横摆率{dot over（phi）} m之间的误差而确定的角度。