公开(公告)号：US20100131125A1

公开(公告)日：2010-05-27

申请号：US12624725

申请日：2009-11-24

Applicant: Xavier Blanchon ,  Philippe Chaix ,  Christophe Caillaud

Inventor： Xavier Blanchon ,  Philippe Chaix ,  Christophe Caillaud

IPC: G01C23/00

CPC classification number: G05D1/0005 ,  G08G5/0052 ,  G08G5/0078

Abstract: The invention relates to the field of civil aviation and, more specifically, relates to the flight management systems, more commonly known by the English acronym FMS. The method for assisting in the management of the flight of an aircraft in order to keep to a time constraint according to the present invention allows for a control of the keeping to the time constraint that presents a rapid dynamic, by avoiding as far as possible having the estimated time of arrival (ETA) at a particular point (P) able to drift relative to a required time of arrival (RTA) at said particular point (P), thanks to the use of a manoeuvring margin (M) granted to the guidance module of the aircraft.

Abstract translation: 本发明涉及民用航空领域，更具体地涉及飞行管理系统，其通常被英文首字母缩略词FMS所熟知。 为了保持根据本发明的时间限制的协助飞行器飞行的管理的方法允许通过避免尽​​可能避免具有快速动态的时间约束来控制， 在特定点（P）处可以相对于在所述特定点（P）处的所需到达时间（RTA）漂移的特定点（P）的估计到达时间（ETA），这归功于使用授予 飞机的指导模块。

公开(公告)号：US08352169B2

公开(公告)日：2013-01-08

申请号：US12870666

申请日：2010-08-27

Applicant: François Coulmeau ,  Xavier Blanchon ,  Philippe Chaix

Inventor： François Coulmeau ,  Xavier Blanchon ,  Philippe Chaix

IPC: G06G7/76 ,  G06F19/00

CPC classification number: G05D1/101 ,  G08G5/0039 ,  G08G5/0052

Abstract: Method for assisting in the flight management of an aircraft aiming to reach a constraint point on a predetermined lateral trajectory that is assumed to have to be followed by the aircraft, at a required time of arrival RTA, said aircraft occupying a current position defined by a current altitude with a current horizontal speed. The method including, when it follows a rallying flight plan, calculating a new rallying flight plan following the lateral trajectory to be followed and including a new estimated speed profile different from the estimated speed profile over at least one update area, the new estimated speed profile including, over said update areas, either a value greater than that of the estimated speed profile, if the arrival time difference is positive, or a value less than that of the estimated speed profile, if the arrival time difference is negative.

Abstract translation: 一种用于协助飞机管理飞行管理的方法，该飞行器旨在达到预定的横向轨迹上的约束点，该预定横向轨迹假设必须在飞行器的后方到达所需的到达时间RTA，所述飞行器占据当前位置 当前高度与当前水平速度。 该方法包括当遵循升级飞行计划时，根据要遵循的横向轨迹计算新的升降飞行计划，并且在至少一个更新区域上包括与估计的速度曲线不同的新的估计速度曲线，新的估计速度曲线 如果到达时间差为正，则在所述更新区域上包括大于估计速度曲线的值的值，或者如果到达时间差为负值则为包括估计速度曲线的值。

公开(公告)号：US08340843B2

公开(公告)日：2012-12-25

申请号：US12613203

申请日：2009-11-05

Applicant: François Coulmeau ,  Manuel Gutierrez-Castaneda ,  Nicolas Simi ,  Xavier Blanchon

Inventor： François Coulmeau ,  Manuel Gutierrez-Castaneda ,  Nicolas Simi ,  Xavier Blanchon

IPC: G06F7/00

CPC classification number: G05D1/0202 ,  G08G5/0043

Abstract: The invention relates to a method for determining the speed of an aircraft that is subject to a time constraint. The invention consists no longer in calculating a single CAS/MACH pair during climb/descent but in adapting the speed in a continuous manner to the bounds of curves of minimum Vmin and maximum Vmax speed defining a flight envelope of the aircraft. The calculation of these speeds is carried out on the basis of constant maximum and minimum speed setpoints and of a coefficient taking into account a deviation to the time constraint.

Abstract translation: 本发明涉及一种用于确定经受时间限制的飞行器的速度的方法。 本发明不再在爬升/下降期间计算单个CAS / MACH对，而是以连续的方式将速度适应于限定飞机的飞行包线的最小Vmin和最大Vmax速度的曲线的边界。 这些速度的计算是基于恒定的最大和最小速度设定值以及考虑到时间约束的偏差的系数进行的。

公开(公告)号：US08718933B2

公开(公告)日：2014-05-06

申请号：US12870683

申请日：2010-08-27

Applicant: François Coulmeau ,  Xavier Blanchon ,  Philippe Chaix

Inventor： François Coulmeau ,  Xavier Blanchon ,  Philippe Chaix

IPC: G01C21/00 ,  G01C21/34 ,  G08G1/123

CPC classification number: G05D1/101 ,  G08G5/0039 ,  G08G5/0052

Abstract: A method of flight management of an aircraft aimed at reaching a constrained point on a predetermined lateral trajectory assumed to be followed by the aircraft, at a required time of arrival RTA to within an absolute tolerance. The method including calculating a flight plan to be followed and a homing flight plan and when the estimated time of arrival ETA based on the homing flight plan strays from an absolute tolerance with respect to the calculation required time of arrival RTAc, calculating a new calculation required time of arrival NRTAc dependent on the calculation required time of arrival RTAc and a function f of the difference between the calculation required time of arrival RTAc and the estimated time of arrival ETA, and replacing the calculation required time of arrival RTAc with the new calculation required time of arrival NRTAc, before recalculating a flight plan to be followed.

Abstract translation: 一种飞行器的飞行管理方法，其目的是到达假定为飞行器所遵循的预定侧向轨迹上的约束点，在到达RTA的所需时间内达到绝对公差。 该方法包括计算要遵循的飞行计划和归位飞行计划，以及当基于归位飞行计划的估计到达时间ETA相对于计算所需到达时间RTAc的绝对公差偏离时，计算所需的新计算 到达时间NRTAc取决于计算所需的到达时间RTAc和计算所需到达时间RTAc与预计到达时间ETA之间的差异的函数f，并且用新的计算替换计算所需的到达时间RTAc 时间到达NRTAc，然后重新计算要遵循的飞行计划。

公开(公告)号：US08386174B2

公开(公告)日：2013-02-26

申请号：US12973438

申请日：2010-12-20

Applicant: François Coulmeau ,  Antoine Lacombe ,  Xavier Blanchon ,  Fany Barailler

Inventor： François Coulmeau ,  Antoine Lacombe ,  Xavier Blanchon ,  Fany Barailler

IPC: G01C21/00

CPC classification number: G06Q10/04 ,  G08G5/0052

Abstract: The invention relates to a method and a device for calculating a time window for a time constraint of arrival of an aircraft at a given point, the aircraft receiving wind predictions and including a sensor for measuring the wind. The method includes a calculation of a first time window, and the calculation of an overall confidence index having the determination of a first confidence index on the basis of a deviation between wind predictions and wind measurements performed by the aircraft, the calculation of a margin for the time constraint on the basis of the overall confidence index, and the calculation of a second window on the basis of the first time window and of the calculated margin.

Abstract translation: 本发明涉及一种用于计算飞行器在给定点的到达时间约束的时间窗的方法和装置，飞行器接收风预测并且包括用于测量风的传感器。 该方法包括第一时间窗口的计算，以及基于风预测与飞行器执行的风测量之间的偏差确定第一置信指数的总体置信指数的计算， 基于总体信心指数的时间约束，以及基于第一时间窗口计算的第二窗口和计算的余量。

公开(公告)号：US08332145B2

公开(公告)日：2012-12-11

申请号：US12790596

申请日：2010-05-28

Applicant: Benoît Dacre-Wright ,  Guy Deker ,  Xavier Blanchon

Inventor： Benoît Dacre-Wright ,  Guy Deker ,  Xavier Blanchon

IPC: G05D1/00

CPC classification number: G05D1/101

Abstract: Method for generating a flight speed profile of an aircraft (100) according to an RTA constraint, characterized in that it permanently calculates, at any point of the flight plan, a speed setpoint VΩ(X) of the aircraft determined on the basis of reference speed profiles, comprising at least a minimum speed profile Vmin(X), and a maximum speed profile Vmax(X). The method can also take into account an optimum speed profile Vopt(X) determined, for example, on the basis of a cost or performance index.

Abstract translation: 用于根据RTA约束产生飞行器（100）的飞行速度曲线的方法，其特征在于，其在飞行计划的任何点处永久地计算基于以下方式确定的飞行器的速度设定点V＆OHgr;（X） 参考速度曲线，包括至少最小速度曲线Vmin（X）和最大速度曲线Vmax（X）。 该方法还可以考虑例如基于成本或性能指标确定的最佳速度曲线Vopt（X）。

公开(公告)号：US20110172914A1

公开(公告)日：2011-07-14

申请号：US13004704

申请日：2011-01-11

Applicant: François COULMEAU ,  Nicolas MARTY ,  Xavier BLANCHON ,  Pierre GAMET

Inventor： François COULMEAU ,  Nicolas MARTY ,  Xavier BLANCHON ,  Pierre GAMET

IPC: G01C21/00

CPC classification number: G08G5/0034

Abstract: A method and device checks the conformity of a trajectory calculated by a flight management system of an aircraft in relation to reference data comprising a reference map. The method includes: geo-referencing of a reference map; determination of a reference trajectory from the geo-referenced reference map; detection of nonconformity in the trajectory calculated by the flight management system by comparison of the trajectory calculated by the flight management system with the reference trajectory; and emission of a warning if a nonconformity is detected.

Abstract translation: 一种方法和装置检查由飞行器的飞行管理系统计算的轨迹与包括参考图的参考数据的一致性。 该方法包括：参考地图的地理参考; 从地理参考参考图确定参考轨迹; 通过飞行管理系统计算的轨迹与参考轨迹进行比较，检测飞行管理系统计算出的轨迹中的不符合度; 并且如果检测到不合格，则发出警告。

公开(公告)号：US20110077859A1

公开(公告)日：2011-03-31

申请号：US12870683

申请日：2010-08-27

Applicant: François Coulmeau ,  Xavier Blanchon ,  Philippe Chaix

Inventor： François Coulmeau ,  Xavier Blanchon ,  Philippe Chaix

IPC: G01C21/00

CPC classification number: G05D1/101 ,  G08G5/0039 ,  G08G5/0052

Abstract: A method of flight management of an aircraft aimed at reaching a constrained point on a predetermined lateral trajectory assumed to be followed by the aircraft, at a required time of arrival RTA to within an absolute tolerance. The method including calculating a flight plan to be followed and a homing flight plan and when the estimated time of arrival ETA based on the homing flight plan strays from an absolute tolerance with respect to the calculation required time of arrival RTAc, calculating a new calculation required time of arrival NRTAc dependent on the calculation required time of arrival RTAc and a function f of the difference between the calculation required time of arrival RTAc and the estimated time of arrival ETA, and replacing the calculation required time of arrival RTAc with the new calculation required time of arrival NRTAc, before recalculating a flight plan to be followed.

Abstract translation: 一种飞行器的飞行管理方法，其目的是到达假定为飞行器所遵循的预定侧向轨迹上的约束点，在到达RTA的所需时间内达到绝对公差。 该方法包括计算要遵循的飞行计划和归位飞行计划，以及当基于归位飞行计划的估计到达时间ETA相对于计算所需到达时间RTAc的绝对公差偏离时，计算需要的新计算 到达时间NRTAc取决于计算所需的到达时间RTAc和计算所需到达时间RTAc与预计到达时间ETA之间的差异的函数f，并且用新的计算替换计算所需的到达时间RTAc 时间到达NRTAc，然后重新计算要遵循的飞行计划。

公开(公告)号：US20110077858A1

公开(公告)日：2011-03-31

申请号：US12870666

申请日：2010-08-27

Applicant: François Coulmeau ,  Xavier Blanchon ,  Phillippe Chaix

Inventor： François Coulmeau ,  Xavier Blanchon ,  Phillippe Chaix

IPC: G01C21/00

CPC classification number: G05D1/101 ,  G08G5/0039 ,  G08G5/0052

Abstract: Method for assisting in the flight management of an aircraft aiming to reach a constraint point on a predetermined lateral trajectory that is assumed to have to be followed by the aircraft, at a required time of arrival RTA, said aircraft occupying a current position defined by a current altitude with a current horizontal speed. The method including, when it follows a rallying flight plan, calculating a new rallying flight plan following the lateral trajectory to be followed and including a new estimated speed profile different from the estimated speed profile over at least one update area, the new estimated speed profile including, over said update areas, either a value greater than that of the estimated speed profile, if the arrival time difference is positive, or a value less than that of the estimated speed profile, if the arrival time difference is negative.

Abstract translation: 一种用于协助飞机管理飞行管理的方法，该飞行器旨在达到预定的横向轨迹上的约束点，该预定横向轨迹假设必须在飞行器的后方到达所需的到达时间RTA，所述飞行器占据当前位置 当前高度与当前水平速度。 该方法包括当遵循升级飞行计划时，根据要遵循的横向轨迹计算新的升降飞行计划，并且在至少一个更新区域上包括与估计的速度曲线不同的新的估计速度曲线，新的估计速度曲线 如果到达时间差为正，则在所述更新区域上包括大于估计速度曲线的值的值，或者如果到达时间差为负值则为包括估计速度曲线的值。

公开(公告)号：US20100274419A1

公开(公告)日：2010-10-28

申请号：US12766892

申请日：2010-04-25

Applicant: Antoine Lacombe ,  Xavier Blanchon ,  Francois Coulmeau

Inventor： Antoine Lacombe ,  Xavier Blanchon ,  Francois Coulmeau

IPC: G05D1/00

CPC classification number: G08G5/0065 ,  G05D1/0661

Abstract: A method of adjusting the trajectory of an aircraft flying a climb circuit, of substantially helical form corresponding to a succession of racetracks, denoted HOLD, the last HOLD, called the exit HOLD, having predefined geometric characteristics and comprising a lock-on point, allowing the aircraft to enter and to exit in the HOLD, the aircraft attaining the setpoint altitude of the climb circuit during the flight of the exit HOLD, comprises at least three steps, including: a step of computing the prediction of the position of the aircraft when the setpoint altitude will be attained; a step of computing the remaining distance to be traveled, between the position of the aircraft when the setpoint altitude will be attained and the lock-on point; and a step making it possible to carry out an adaptation of the form of the exit HOLD so as to minimize the remaining distance to be traveled DELTA.

Abstract translation: 调整飞行爬升电路的飞行器的轨迹的方法，其基本上螺旋形式对应于连续的赛道，表示为HOLD，称为出口HOLD的最后一个HOLD，具有预定义的几何特征并包括锁定点，允许 所述飞机进入并在所述HOLD中退出，所述飞机在所述出口HOLD的飞行期间达到所述爬升回路的设定点高度，包括至少三个步骤，包括：计算所述飞行器的位置的预测的步骤 将达到设定点高度; 在达到设定点高度时计算飞机剩余距离，飞行器位置和锁定点之间的步骤; 以及使得可以执行出口保持装置的形式的适应，以便最小化要行驶的剩余距离DELTA。