公开(公告)号：WO1997048028A1

公开(公告)日：1997-12-18

申请号：PCT/FR1997001077

申请日：1997-06-13

Applicant: SEXTANT AVIONIQUE ,  SAINTHUILE, Gérard ,  PERENNEC, Myriam

Inventor： SEXTANT AVIONIQUE

IPC: G05D01/00

CPC classification number: G01C21/00 ,  G05D1/0005

Abstract: A method comprising a first step of determining the point on the flightpath wherefrom it is theoretically no longer possible to comply with the required time constraint by following a pre-established speed profile, and a second step of computing a speed change and determining a fresh speed profile obtained by determining segment-by-segment speed corrections from said point up to the last modifiable segment. The speed change in each segment is restricted to a maximum value and the new speed is computed on the basis of the curve showing the flight time t as a function of the speed V, said curve being converged upon by a curve corresponding to the following equation having three coefficients (c1, c2, c3): V = c1 / t + c2 / t + c3 / t . Compliance with time constraints may thus be ensured while meeting the requirements of the pilot and air traffic controllers.

Abstract translation: 一种方法，包括确定飞行路径上的点的第一步骤，从理论上讲，不再可能通过遵循预先建立的速度曲线来符合所需的时间约束，以及计算速度变化并确定新速度的第二步骤 通过确定从所述点到最后可修改段的逐段速度校正获得的轮廓。 每个段的速度变化被限制为最大值，并且基于显示作为速度V的函数的飞行时间t的曲线来计算新速度，所述曲线由对应于以下等式的曲线收敛 具有三个系数（c1，c2，c3）：V = c1 / t + c2 / t2 + c3 / t3。 因此可以确保符合时间限制，同时满足飞行员和空中交通管制员的要求。

公开(公告)号：WO1996026472A1

公开(公告)日：1996-08-29

申请号：PCT/FR1996000284

申请日：1996-02-22

Applicant: PELLETIER, Patrick

IPC: G05D01/00

CPC classification number: G05D1/0055 ,  B64D43/00

Abstract: The invention pertains to the field of measurement devices for providing results other than an instantaneous value for a variable, and more particularly to an aircraft flight control assistance device comprising means (10) for detecting an instantaneous value of physical variables relating, for instance, to the aircraft propulsion system and to environmental conditions, characterized in that said device includes means (70) for displaying, at any point of a flight envelope using power and on the basis of said measured values, data representative of the difference between the power consumption of the propulsion system and a predetermined maximum power value, said means (70) having an on-board processor (80) in which a model of the flight mechanics and engines throughout the aircraft flight envelope has been input, as well as a display means (90).

Abstract translation: 本发明涉及用于提供不同于变量的瞬时值的结果的测量装置领域，更具体地涉及一种包括用于检测物理变量的瞬时值的装置（10）的飞行器飞行控制辅助装置，所述物理变量与例如 飞行器推进系统和环境条件，其特征在于，所述设备包括用于在飞行包线的任何点处使用功率并且基于所述测量值在所述飞行包线的任何点显示表示所述飞行包线的功率消耗之间的差异的数据的装置（70） 推进系统和预定的最大功率值，所述装置（70）具有车载处理器（80），其中已经输入了整个飞行器飞行包线上的飞行力学和发动机的模型，以及显示装置 90）。

公开(公告)号：WO1996010222A1

公开(公告)日：1996-04-04

申请号：PCT/FR1995001230

申请日：1995-09-25

Applicant: AEROSPATIALE SOCIETE NATIONALE INDUSTRIELLE ,  COQUIN, Laurent ,  LE DRAOULLEC, Christine

Inventor： AEROSPATIALE SOCIETE NATIONALE INDUSTRIELLE

IPC: G05D01/00

CPC classification number: G05D1/0083

Abstract: System for generating on board of an aircraft a signal of information, warning or alarm in the case of an abnormality during take-off. According to the invention, the system comprises means (4) which calculate the position Dstop on the runway where the aircraft has to stop if the pilot decides to interrupt immediately the take-off procedure, representing the distance for stopping the aircraft during the acceleration phase of the aircraft during take-off; means (5) for comparing Dstop to the length of the runway L available in order to determine if a take-off interruption is still possible.

Abstract translation: 在起飞时发生异常情况的信号，警告或报警信号的系统。 根据本发明，该系统包括如果飞行员决定立即中断起飞程序的飞机必须停下的跑道上计算位置Dstop的装置（4），表示在加速阶段停止飞行器的距离 起飞时的飞机; 用于将Dstop与跑道L的长度进行比较的装置（5），以便确定起飞中断是否仍然可行。

公开(公告)号：WO1996000933A1

公开(公告)日：1996-01-11

申请号：PCT/US1995008185

申请日：1995-06-29

Applicant: HONEYWELL INC.

Inventor： HONEYWELL INC. ,  GREGORY, William, W. ,  LANCE, Wayne, E. ,  HEGG, Jeffrey, W.

IPC: G05D01/00

CPC classification number: G05D1/0077 ,  G05D1/0061

Abstract: A redundant active hand controller system has first and second motors connected to a common shaft. A compensator which differentiates a motor command signal from a first proportional and integral controller, differentiates a motor command signal from a second proportional and integral controller and subtracts the first differentiated motor command signal from the second differentiated motor command signal to provide a correction signal. The correction signal is summed with the error signal into the first proportional and integral controller to correct for slight differences in the integral control function of the first and second proportional and integral controllers.

Abstract translation: 冗余主动手控制器系统具有连接到公共轴的第一和第二马达。 一种补偿器，其将电动机命令信号与第一比例积分控制器区分开来，将电动机命令信号与第二比例积分控制器区分开，并从第二微分电动机命令信号中减去第一微分电动机命令信号以提供校正信号。 校正信号与误差信号相加到第一比例和积分控制器中，以校正第一和第二比例和积分控制器的积分控制功能的微小差异。

公开(公告)号：WO1987001216A1

公开(公告)日：1987-02-26

申请号：PCT/SE1986000375

申请日：1986-08-22

Applicant: TELLUS CARRAGO AB ,  LUNDSTRÖM, Mats

Inventor： TELLUS CARRAGO AB

IPC: G05D01/00

CPC classification number: G05D1/0246

Abstract: A navigation system for detecting the position and controlling the movement of an automatically guided vehicle (1) comprises at least one light source (4) and at least one detector (5) responsive to the light emitted from the light source (4), the vehicle (1) being accompanied by either the light source (4) or the detector (5). A signal processing unit (10) has memory means (13) in which path control information (12) corresponding to the path (3) of the vehicle is stored, and comparator means (11) adapted to compare the path control informaton (12) stored in the memory means (13) with positional information produced by the system, in order, when the path control information and the positional information differ, to emit control signals (15) for the movement of the vehicle. The detector (5) is a position-sensitive semiconductor detector having a substantially planar, extended, continuous sensing area (7) and is adapted to receive light within a restricted part (P) of the sensing area of the detector. In response to the detected light, electric signals are produced from which said positional information (9) corresponding to the actual position of the vehicle (1) in at least one direction is derived.

Abstract translation: 用于检测位置并控制自动导向车辆（1）的运动的导航系统包括响应于从光源（4）发射的光的至少一个光源（4）和至少一个检测器（5）， 车辆（1）由光源（4）或检测器（5）伴随。 信号处理单元（10）具有存储装置（13），其中存储与车辆的路径（3）相对应的路径控制信息（12），并且比较装置（11）适于比较路径控制信息（12） 存储在存储装置（13）中的位置信息，以便当路径控制信息和位置信息不同时，发出用于车辆移动的控制信号（15）。 检测器（5）是具有基本上平面的，延伸的，连续的感测区域（7）的位置敏感半导体检测器，并且适于在检测器的感测区域的受限部分（P）内接收光。 响应于检测到的光，产生电信号，从而从其导出与至少一个方向上的车辆（1）的实际位置相对应的所述位置信息（9）。

公开(公告)号：WO1997041495A1

公开(公告)日：1997-11-06

申请号：PCT/FR1997000718

申请日：1997-04-22

Applicant: SEXTANT AVIONIQUE ,  BOMANS, Muriel ,  GRAND-PERRET, Sylvie

Inventor： SEXTANT AVIONIQUE

IPC: G05D01/00

CPC classification number: G08G5/0034 ,  G01C23/00 ,  G06F3/0489 ,  G08G5/0021

Abstract: The invention relates to air navigation assistance methods and devices, used in flight management systems on board aircraft. To facilitate the work of the pilot, the onboard computer (FMS) communicates with the pilot through a display and data input console (MCDU). This console displays a list of tasks to be executed in the form of a series of selectable and activatable main zones (40). Each zone corresponds to a task to be executed through the console, and when the task has been executed (validation key actuated by the pilot), the task-list is redisplayed, the zone for which the task has been executed and validated appearing in a different colour from the other zones. The zones preferably appear in duplicate (40, 50) when there is a co-pilot and it can clearly be seen which tasks have been executed and by which pilot, and which tasks remain to be executed.

Abstract translation: 本发明涉及用于飞机上的飞行管理系统中的空中导航辅助方法和装置。 为了方便飞行员的工作，车载计算机（FMS）通过显示器和数据输入控制台（MCDU）与飞行员进行通信。 该控制台以一系列可选择和可激活的主区域的形式显示要执行的任务列表（40）。 每个区域对应于要通过控制台执行的任务，并且当任务已被执行（由飞行员启动的验证键）时，重新显示任务列表，任务被执行和验证的区域出现在 与其他区域不同的颜色。 当有共同飞行员时，这些区域优选地重复出现（40,50），并且可以清楚地看出执行了哪些任务以及哪个飞行员以及哪些任务仍然执行。

公开(公告)号：WO1997026588A1

公开(公告)日：1997-07-24

申请号：PCT/GB1997000174

申请日：1997-01-17

Applicant: HECKETT MULTISERV PLC ,  EVANS, Darrel ,  KIRKWOOD, Clyde, Alexander

Inventor： HECKETT MULTISERV PLC

IPC: G05D01/00

CPC classification number: G08G1/20 ,  G01S5/0027 ,  G05B19/4183 ,  G05B2219/31432 ,  G05D1/0278 ,  G05D1/0282 ,  G05D2201/0216 ,  Y02P90/10

Abstract: The absolute position of a vehicle (V) transporting articles between sites (SS) at an installation, e.g. stations of a steel works, is determined by satellite navigation signal and logged on a CPU with a database to ensure that the intended articles (SR) are processed on different sites as required.

Abstract translation: 在安装场所（SS）之间运输物品的车辆（V）的绝对位置，例如， 钢铁工程站由卫星导航信号确定，并登录到具有数据库的CPU上，以确保根据需要在不同的站点处理预期的物品（SR）。

公开(公告)号：WO1995012153A1

公开(公告)日：1995-05-04

申请号：PCT/US1993010459

申请日：1993-10-29

Applicant: HONEYWELL INC.

Inventor： HONEYWELL INC. ,  GREGORY, William, W. ,  KAUFFMAN, James, W.

IPC: G05D01/00

CPC classification number: G05D1/0061 ,  B64C13/04

Abstract: A control system for an active hand controller, for example, uses a control stick connected to and controlled by a motor. Electronics are provided to control the motor to eliminate oscillations due to motor torque and high gain due to breakout at the control stick when the control stick is at about its null position. Both hardware as well as software implementations can provide position dependent dampening to the control sticks such that when the control stick is located about a null position, a higher rate of dampening is provided than when the control stick is located outside the null position, when a lower rate of dampening is provided. The system provides a stable active hand controller control stick without degraded force and feel characteristics of the system.

Abstract translation: 例如，用于主动手控制器的控制系统使用连接到电动机并由电动机控制的控制杆。 电子设备用于控制电机，以消除由于电机转矩引起的振荡，并且当控制棒处于其零位置时，由于控制棒上的突出而产生的高增益。 硬件以及软件实现都可以向控制棒提供与位置相关的阻尼，使得当控制棒位于零位置时，提供比当控制棒位于空位置之外时更高的阻尼速率，当 提供较低的阻尼率。 该系统提供稳定的主动手控制器控制棒，而不会降低系统的力和感觉特性。

公开(公告)号：WO1995012152A1

公开(公告)日：1995-05-04

申请号：PCT/US1993010458

申请日：1993-10-29

Applicant: HONEYWELL INC.

Inventor： HONEYWELL INC. ,  GREGORY, William, W. ,  HEGG, Jeffrey, W. ,  LANCE, Wayne, E.

IPC: G05D01/00

CPC classification number: G05B19/409 ,  G05B2219/35438 ,  G05B2219/37396 ,  G05D1/0061 ,  H01H2003/008 ,  Y10T74/20201

Abstract: An active hand controller system is provided wherein a feedback loop detects the position of a control stick to control a motor driving the control stick to thereby provide certain force feel characteristics to the control stick. The feedback loop includes a detector for detecting force exerted for the control stick to generate a signal indicative of the force or torque being applied to the control stick. In a more specific aspect, the invention includes the use of variable reluctance transformers, preferably in a push/pull configuration to detect the forces being exerted on the control stick.

Abstract translation: 提供了一种主动的手控制器系统，其中反馈回路检测控制棒的位置，以控制驱动控制棒的电机，从而向控制棒提供一定的力感觉特性。 反馈回路包括检测器，用于检测施加给控制棒的力，以产生指示施加到控制棒的力或扭矩的信号。 在更具体的方面，本发明包括使用可变磁阻变压器，优选地在推/拉配置中来检测施加在控制棒上的力。

公开(公告)号：WO1993004419A1

公开(公告)日：1993-03-04

申请号：PCT/US1992007282

申请日：1992-08-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  EBERT, Frederick, J. ,  DRISCOLL, Joseph, T. ,  SWEET, David, H.

IPC: G05D01/00

CPC classification number: G05D1/0055 ,  G05D1/0858

Abstract: A helicopter engine fuel control anticipates sudden changes in engine power demand during yaw inputs to thereby minimize engine and main rotor speed droop and overspeed during yaw maneuvers. The rate (121, 123) of yaw control (107) position change generates (10) a yaw component (104) of a helicopter fuel control (52) fuel command signal (70). The magnitude of the yaw component is also dependent upon the rate of yaw control position change (703). The fuel command signal yaw component (104) is overriden (113, 115) when rotor decay rate (209, 217) has been arrested during a sharp left hover turn (216); when the yaw component is removing fuel (239) during rotor droop (238); and when the yaw component is adding fuel (228) during rotor overspeed (227).

Abstract translation: 直升机发动机燃料控制预计在偏航输入期间发动机功率需求的突然变化，从而使偏航操纵期间发动机和主转子速度下降和超速最小化。 偏航控制（107）位置变化的速率（121,123）产生（10）直升机燃料控制（52）燃料指令信号（70）的偏航分量（104）。 偏航分量的大小也取决于偏航控制位置变化的速度（703）。 当旋转衰减速率（209,217）在尖锐的左悬停转弯（216）期间被停止时，燃料指令信号偏航分量（104）被覆盖（113,115）; 当偏转分量在转子下垂期间移除燃料（239）时; 并且当偏转分量在转子超速期间添加燃料（228）（227）时。