公开(公告)号：US4232839A

公开(公告)日：1980-11-11

申请号：US850134

申请日：1977-11-10

Applicant: Jean-Luc Sicre ,  Daniel Gruaz

Inventor： Jean-Luc Sicre ,  Daniel Gruaz

IPC: B64C13/18 ,  G01S1/02 ,  G05D1/06 ,  G05D1/00 ,  G05D1/12

CPC classification number: G05D1/0676 ,  G01S1/02

Abstract: A method for controlling the decelerated approach of an aerodyne on radioignment generally referred to as "glide," in particular for the purpose of reducing its fuel consumption and reducing the noise, mainly in the final stage of the approach, by approaching the glide at high speed, initiating the descent according to the glide angle, also at high speed then beginning a decelerated phase in order to reach a predetermined speed V sel+k, k being generally equal to 10 knots, on reaching a predetermined altitude, h.sub.F, and then passing progessively from the speed V sel+k to the speed V sel. From the time when the aerodyne reaches the axis of the glide path, a course is determined in two sections, as regards the variables of speed and altitude, for reaching the point situated at the altitude h.sub.F at the given speed V sel+k, namely a first section, at the beginning of which the aerodyne which was previously travelling along the glide, begins a first braking stage, the speed of the aerodyne, during this first section, bein reduced by at least a predetermined speed .DELTA.V.sub.1, and a second section, at the beginning of which the aerodyne initiates a second braking stage, the gradient dv/dh along these two sections having to satisfy the relationshipP.sub.32 =k P.sub.1P.sub.1 and P.sub.2 being the respective gradients on each of the two sections and k being a value determined experimentally.

Abstract translation: 一种用于控制通常称为“滑行”的无线电对准的航空器的减速方法的方法，特别是为了减少其燃料消耗和减少噪声，主要在该方法的最后阶段，通过接近滑翔 在高速下，也以高速开始下降，然后以高速开始减速阶段，以便达到预定速度V sel + k，k达到预定高度hF时通常等于10节， 然后从速度V sel + k进入速度V sel。 从空气到达滑翔道的轴线的时候，就速度和高度的变量而言，以给定速度V sel + k到达位于高度h F处的点的两个部分确定一个路线，即 第一部分，其中先前沿着滑行行进的空气开始第一制动阶段，在该第一部分期间，空气的速度减小至少预定速度DELTA V1，并且第二部分 在开始开始第二制动阶段的情况下，沿着这两个部分的梯度dv / dh必须满足关系P32 = k P1 P1和P2是两个部分中的每个部分上的相应梯度，k是 实验值确定。

公开(公告)号：US6161062A

公开(公告)日：2000-12-12

申请号：US101759

申请日：1998-07-20

Applicant: Jean-Luc Sicre ,  Patrice Guillard

Inventor： Jean-Luc Sicre ,  Patrice Guillard

IPC: B64D45/00 ,  B64D45/08 ,  G01S3/48 ,  G01S5/14 ,  G01S19/36 ,  G01S19/42 ,  G01S19/48 ,  G01S19/52 ,  G01S19/54 ,  G02B27/01 ,  G08G5/00 ,  G01C21/00

CPC classification number: G01S19/52 ,  G01C21/165 ,  G01S3/48 ,  G01S19/36 ,  G01S19/42 ,  G01S19/54 ,  G02B27/01

Abstract: The invention relates to systems for aiding the piloting of aircraft, mainly for take-off and landing under poor conditions of visibility.In order to benefit from the contribution of head-up displays, which exhibit symbols for the artificial horizon line, aircraft longitudinal attitude and ground speed vector, without using an IRS inertial unit to supply the heading and attitude information, it is proposed to use a non-inertial AHRS unit associated with a compass, and periodically to correct the information which it supplies, in order to exhibit the attitude symbols with the aid of the corrected information rather than the raw information from the AHRS unit. The correction is given by two GPS receivers (GPS1, GPS2) associated with antennas (A1, A2) on the top of the aircraft, an interferometric measurement of radiofrequency carrier phase being made to determine a direction vector of the aircraft.Application to the modernisation of aircraft equipped with non-inertial AHRS units so as to allow landings and take-offs in all conditions, including conditions of very poor visibility.

Abstract translation: PCT No.PCT / FR97 / 00058 Sec。 371日期：1998年7月20日 102（e）1998年7月20日PCT PCT 1997年1月14日PCT公布。 公开号WO97 / 26553 日期1997年7月24日本发明涉及用于协助飞机驾驶的系统，主要用于在不良的可视性条件下起飞和着陆。 为了从不用IRS惯性单元提供标题和姿态信息的人造地平线，飞机纵向姿态和地面速度矢量的符号的平视显示器的贡献中获益，建议使用 与罗盘相关联的非惯性AHRS单元，并且周期性地校正其提供的信息，以便借助于校正的信息而不是来自AHRS单元的原始信息来展现姿态符号。 校正由与飞机顶部的天线（A1，A2）相关联的两个GPS接收器（GPS1，GPS2）给出，进行射频载波相位的干涉测量以确定飞行器的方向矢量。 适用于配备非惯性AHRS装置的飞机现代化，以便在所有条件下，包括非常差的可见性条件下允许着陆和起飞。

公开(公告)号：US5666111A

公开(公告)日：1997-09-09

申请号：US603084

申请日：1996-02-16

Applicant: Thierry Servat ,  Jean-Luc Sicre

Inventor： Thierry Servat ,  Jean-Luc Sicre

IPC: B64D45/08 ,  G01C23/00 ,  G05D1/06 ,  G08G5/02 ,  G01C21/00

CPC classification number: G08G5/0021 ,  G01C23/005 ,  G05D1/0676 ,  G08G5/025

Abstract: Disclosed is an improvement to the guidance, during the approach and landing stages, of aircraft operating in the categories 2 or 3A of the certification system used by recognized civilian organizations such as the DGAC, the FAA or the JAA, this improvement being designed to render the aircraft capable of working in the immediately lower category, namely the 3A or 3B category, at lower cost. The improvement consists of the addition of a head-up display visor HUD to the attitude heading reference system AHRS and to the air data computer ADC and of the displaying, on the head-up display visor HUD, of the flight path vector whose angular coordinates are drawn from information on east-west and north-south horizontal ground speed delivered by a global positioning receiver GPS according to the avionics standard furthermore used for the localization and navigation of the aircraft. This improvement has the advantage of enabling passage to the immediately lower certification category without requiring the on-board carriage of an inertial platform which is a device that is costly to purchase as well as to maintain.

Abstract translation: 披露了在公认的民航组织（如DGAC，FAA或JAA）使用的认证体系的类别2或3A中运行的飞机在进场和着陆阶段的指导性改进，这种改进旨在呈现 该飞机能够以较低的成本工作在紧邻较低的类别，即3A或3B类别。 改进之处在于向姿态标题参考系统AHRS和空中数据计算机ADC添加平视显示屏HUD，并在平视显示屏HUD上显示飞行路径向量的角坐标 来自全球定位接收机GPS的东西向和南北水平地面速度的信息，根据航空电子标准进一步用于飞机的本地化和导航。 这种改进具有能够通过到即将下降的认证类别的优点，而不需要作为购买成本高且维护成本高的设备的惯性平台的车载运送。

公开(公告)号：US4331032A

公开(公告)日：1982-05-25

申请号：US113829

申请日：1980-01-21

Applicant: Jean-Luc Sicre

Inventor： Jean-Luc Sicre

IPC: G01D5/00 ,  G01P1/07 ,  G01P3/62 ,  G05D1/06 ,  G01C21/10

CPC classification number: G05D1/0615 ,  G01P3/62

Abstract: A variometer for an aerodyne. The variometer has at least one dial conventionally graduated to represent speed, a needle indicating on said graduation the instantaneous vertical speed. The variometer also has an indicator which is representative of the potential vertical speed, and can move around the dial so that the position of the indicator with respect to the needle indicates instantaneously the acceleration on the trajectory of the aircraft.

Abstract translation: 气球变速器。 变速仪具有至少一个刻度表示传统刻度以表示速度的表盘，指示所述刻度上的瞬时垂直速度的针。 变速仪还具有代表潜在垂直速度的指示器，并且可以围绕表盘移动，使得指示器相对于针的位置立即指示飞行器轨迹上的加速度。

公开(公告)号：USRE31159E

公开(公告)日：1983-02-22

申请号：US125879

申请日：1980-02-29

Applicant: Jean-Luc Sicre

Inventor： Jean-Luc Sicre

IPC: G05D1/06 ,  G06G7/78

CPC classification number: G05D1/0607 ,  G06G7/78

Abstract: A flying method using total .[.power.]. .Iadd.energy.Iaddend., in particular for the take-off and overshoot of an aircraft, is disclosed in which the aerodynamic .[.gradient.]. .Iadd.flight path angle .Iaddend..gamma.a is governed by reference to a desired .[.gradient.]. .Iadd.flight path angle .Iaddend..gamma.d which is the .[.total gradient.]. .Iadd.potential flight path .Iaddend..gamma.t modulated by the difference between the aircraft speed V and a reference speed V.sub.2. An error signal .delta. representative of the difference between the aerodynamic .[.gradient.]. .Iadd.flight path angle .Iaddend..gamma.a and the desired .[.gradient.]. .Iadd.flight path angle .Iaddend..gamma.d is displayed. The display of the desired .[.gradient.]. .Iadd.flight path angle .Iaddend..gamma.d may be by means of the .[.pitching tendency bar of the artificial horizon.]. .Iadd.pitch command bar of an attitude director indicator .Iaddend.for example.

公开(公告)号：US4071893A

公开(公告)日：1978-01-31

申请号：US703006

申请日：1976-07-06

Applicant: Jean-Luc Sicre

Inventor： Jean-Luc Sicre

IPC: G05D1/06 ,  G06G7/78 ,  B64C13/50

CPC classification number: G05D1/0607 ,  G06G7/78

Abstract: A flying method using total power, in particular for the take-off and overshoot of an aircraft, is disclosed in which the aerodynamic gradient .gamma.a is governed by reference to a desired gradient .gamma.d which is the total gradient .gamma.t modulated by the difference between the aircraft speed V and a reference speed V.sub.2. An error signal .delta. representative of the difference between the aerodynamic gradient .gamma.a and the desired gradient .gamma.d is displayed. The display of the desired gradient .gamma.d may be by means of the pitching tendency bar of an artificial horizon for example.

Abstract translation: 公开了使用总功率的飞行方法，特别是用于飞行器的起飞和过冲的飞行方法，其中空气动力学梯度γa通过参考由差异调制的总梯度γt的期望梯度γd来控制 在飞行器速度V和参考速度V2之间。 显示代表空气动力学梯度γa和期望梯度γd之间的差的误差信号δ。 期望的梯度γd的显示可以通过例如人造水平仪的俯仰倾向条来进行。