公开(公告)号：EP0438826A3

公开(公告)日：1992-10-21

申请号：EP90203358.8

申请日：1990-12-14

申请人： THE BOEING COMPANY

发明人： Orgun, Munir ,  Pappu, Venkata Rao ,  Toledo, Alfredo Anthony, Jr.

IPC分类号： G05D1/06

CPC分类号： G05D1/0676

摘要： Disclosed is a method of and apparatus for determining the flare height at which the flare maneuver of an automatic landing procedure is initiated. The method includes the step of generating an adjusted approach sink rate signal, which depends on the ground speed of the aircraft during a landing approach and is compensated for short term deviations from the glideslope angle. The adjusted approach sink rate signal is filtered (first order lag), and the filtered signal is then used to establish: (a) a nominal flare height value when the aircraft sink rate is between two predetermined sink rate values (the aircraft landing approach speed is in a nominal range); (b) a flare height that is above the nominal flare height value and is linearly related to the adjusted approach sink rate of the aircraft when the adjusted approach sink rate exceeds the first predetermined value (relatively high ground speed approach); and (c) a flare height that is less than the nominal flare height value and is linearly related to the magnitude of the adjusted approach sink rate signal when the magnitude of the filtered adjusted approach sink rate signal is less than the second predetermined sink rate magnitude (relatively low ground speed approach). In the disclosed arrangements, provision is made to limit the flare height determined by the invention to maximum and minimum flare height values and provision is made for storing the flare height signal for use by the automatic landing system after the flare maneuver has been initiated.

公开(公告)号：EP0441007A2

公开(公告)日：1991-08-14

申请号：EP90203502.1

申请日：1990-12-21

申请人： THE BOEING COMPANY

发明人： Orgun, Munir ,  Flannigan, Sean Joseph

IPC分类号： G01M1/12 ,  G05D1/06

CPC分类号： G01M1/127

摘要： Disclosed is a method of and an arrangement for real time estimation of the location of the center of gravity of an aircraft. The center of gravity estimate is utilized in an aircraft flight control system for effecting flight control laws in which the center of gravity is a parameter that at least in part establishes open loop compensation or feedback gain. The disclosed method and arrangement are specifically adapted for establishing stabilizer mistrim during a landing procedure in which an aircraft flight control system is automatically controlling the aircraft. The method generally comprises the steps of generating a signal that represents the product of the aircraft stabilizer position and a multiplicative factor, A₁ and adding to that product an additive factor, A₂. The multiplicative factor, A₁, and the additive factor, A₂, both are determined on the basis of the angle of attack of the aircraft and the aircraft flap setting.

摘要翻译： 公开了一种实时估计飞机重心位置的方法和装置。 重心估计用于飞行器飞行控制系统，用于实现飞行控制规则，其中重心是至少部分地建立开环补偿或反馈增益的参数。 所公开的方法和装置特别适用于在飞行器飞行控制系统自动控制飞机的着陆程序期间建立稳定器错误。 该方法通常包括以下步骤：产生表示飞行器稳定器位置和乘法因子A1的乘积的信号，并向该乘积加上加法因子A2。 乘法因子A1和加法因子A2都是基于飞机的迎角和飞机挡板设置来确定的。

公开(公告)号：EP0438826A2

公开(公告)日：1991-07-31

申请号：EP90203358.8

申请日：1990-12-14

申请人： THE BOEING COMPANY

发明人： Orgun, Munir ,  Pappu, Venkata Rao ,  Toledo, Alfredo Anthony, Jr.

IPC分类号： G05D1/06

CPC分类号： G05D1/0676

摘要： Disclosed is a method of and apparatus for determining the flare height at which the flare maneuver of an automatic landing procedure is initiated. The method includes the step of generating an adjusted approach sink rate signal, which depends on the ground speed of the aircraft during a landing approach and is compensated for short term deviations from the glideslope angle. The adjusted approach sink rate signal is filtered (first order lag), and the filtered signal is then used to establish: (a) a nominal flare height value when the aircraft sink rate is between two predetermined sink rate values (the aircraft landing approach speed is in a nominal range); (b) a flare height that is above the nominal flare height value and is linearly related to the adjusted approach sink rate of the aircraft when the adjusted approach sink rate exceeds the first predetermined value (relatively high ground speed approach); and (c) a flare height that is less than the nominal flare height value and is linearly related to the magnitude of the adjusted approach sink rate signal when the magnitude of the filtered adjusted approach sink rate signal is less than the second predetermined sink rate magnitude (relatively low ground speed approach). In the disclosed arrangements, provision is made to limit the flare height determined by the invention to maximum and minimum flare height values and provision is made for storing the flare height signal for use by the automatic landing system after the flare maneuver has been initiated.

摘要翻译： 本发明公开了用于确定性的采矿在哪一个自动着陆过程的耀斑操纵开始火炬高度的方法和装置。 该方法包括在调整的方法的下降率信号，其着陆进场期间取决于飞行器的地面速度和被补偿用于从下滑道角度短期偏差生成的步骤。 调整方法下降率信号进行滤波（一阶滞后），然后将滤波后的信号被用于建立：（a）一种标称火炬高度值。当飞机下降率是两个预定的下降率的值（在飞机着陆进场速度之间 处于额定范围）; （B）一个火炬高度确实是标称光斑高度值之上并且当调整方法下降率超过第一预定值（相对较高的地面速度的方法）是线性相关的飞行器的所述经调整的方法的下降率; 和（c）一个火炬高度所做的是小于标称光斑高度值和线性相关的调整的方法下降率信号的大小当滤波调整方法下降率信号的幅度小于第二预定的下降率的大小 （相对较低的地面速度的方法）。 在盘游离缺失安排中规定，以限制光斑高度确定性通过将本发明的最大和最小光斑高度值和提供开采火炬操纵已经启动之后，由自动着陆系统中存储使用的火炬高度信号而成。

公开(公告)号：EP0471395A3

公开(公告)日：1993-08-25

申请号：EP91201828.0

申请日：1991-07-11

申请人： THE BOEING COMPANY

发明人： Orgun, Munir ,  Nguyen, Dung D.

IPC分类号： G05D1/00 ,  G05D1/08

CPC分类号： G05D1/0072 ,  G05D1/0808

摘要： A controller for generating a bank angle limit for an aircraft during takeoff with an nonoperational engine. The controller operates so that there are minimum and maximum bank angle limits. Between these minimum and maximums, there is a linear relationship between aircraft airspeed and bank angle limit. However, before there is a change in aircraft airspeed from an increasing mode to a decreasing mode or vice versa, the bank angle limit remains constant until the change in aircraft airspeed is greater than or equal to a predetermined airspeed differential.

公开(公告)号：EP0471395A2

公开(公告)日：1992-02-19

申请号：EP91201828.0

申请日：1991-07-11

申请人： THE BOEING COMPANY

发明人： Orgun, Munir ,  Nguyen, Dung D.

IPC分类号： G05D1/00 ,  G05D1/08

CPC分类号： G05D1/0072 ,  G05D1/0808

摘要： A controller for generating a bank angle limit for an aircraft during takeoff with an nonoperational engine. The controller operates so that there are minimum and maximum bank angle limits. Between these minimum and maximums, there is a linear relationship between aircraft airspeed and bank angle limit. However, before there is a change in aircraft airspeed from an increasing mode to a decreasing mode or vice versa, the bank angle limit remains constant until the change in aircraft airspeed is greater than or equal to a predetermined airspeed differential.

摘要翻译： 控制器，用于在飞机起飞期间与不可操作发动机产生坡度角限制。 控制器操作以便thatthere是最小和最大倾斜角的限制。 论文最小值和最大值之间，有飞机空速和银行角界限之间的线性关系。 然而，在存在来自于增加的方式减小的模式或反之亦然空速在飞机的变化，银行角界限直到飞机空速改变大于或等于预定的空速差保持恒定。

公开(公告)号：EP0438816B1

公开(公告)日：1995-09-06

申请号：EP90202722.6

申请日：1990-10-11

申请人： THE BOEING COMPANY

发明人： Orgun, Munir ,  McRoberts, Timothy Clark ,  Virdee, Arvinder Sing

IPC分类号： G05D1/00 ,  B64D31/10 ,  G05D1/08

CPC分类号： G05D1/0676 ,  G05D1/0072

公开(公告)号：EP0438834A2

公开(公告)日：1991-07-31

申请号：EP90203484.2

申请日：1990-12-20

申请人： THE BOEING COMPANY

发明人： Orgun, Munir ,  Pappu, Venkata Rao ,  Toledo, Alfredo Anthony, Jr.

IPC分类号： G05D1/06

CPC分类号： G05D1/0676

摘要： Disclosed is a method of and apparatus for generating a signal representative of aircraft gear altitude after the flare maneuver is initiated in an automatic landing procedure. In accordance with the invention, the gear altitude signal is produced by complementary filtering of the aircraft gear altitude signal and the aircraft inertial vertical acceleration signal, with the complementary filter frequency being varied so that the aircraft filtered gear altitude signal primarily is produced on the basis of the vertical inertial acceleration signals prior to the time at which the aircraft reaches the runway threshold and is primarily produced on the basis of the aircraft gear altitude signal after the aircraft crosses runway threshold. The result is the reduction of the filtered gear altitude signal variation that can be caused by irregular terrain along the landing approach path while maintaining signal sensitivity to runway slope and runway slope variation.

摘要翻译： 公开了一种用于在自动着陆过程中启动火炬机动之后产生代表飞机齿轮高度的信号的方法和装置。 根据本发明，齿轮高度信号是通过对飞行器齿轮高度信号和飞行器惯性垂直加速度信号的互补滤波产生的，其中补偿滤波器频率是变化的，使得飞机过滤齿轮高度信号主要是基于 在航空器达到跑道阈值之前的垂直惯性加速度信号，并且主要基于飞机跨越跑道阈值之后的飞机齿轮高度信号产生。 结果是降低沿着着陆进近路径的不规则地形可能引起的过滤齿轮高度信号变化，同时保持对跑道斜率和跑道坡度变化的信号灵敏度。

公开(公告)号：EP0471395B1

公开(公告)日：1996-05-08

申请号：EP91201828.0

申请日：1991-07-11

申请人： THE BOEING COMPANY

发明人： Orgun, Munir ,  Nguyen, Dung D.

IPC分类号： G05D1/00 ,  G05D1/08

CPC分类号： G05D1/0072 ,  G05D1/0808

公开(公告)号：EP0438834A3

公开(公告)日：1992-09-02

申请号：EP90203484.2

申请日：1990-12-20

申请人： THE BOEING COMPANY

发明人： Orgun, Munir ,  Pappu, Venkata Rao ,  Toledo, Alfredo Anthony, Jr.

IPC分类号： G05D1/06

CPC分类号： G05D1/0676

摘要： Disclosed is a method of and apparatus for generating a signal representative of aircraft gear altitude after the flare maneuver is initiated in an automatic landing procedure. In accordance with the invention, the gear altitude signal is produced by complementary filtering of the aircraft gear altitude signal and the aircraft inertial vertical acceleration signal, with the complementary filter frequency being varied so that the aircraft filtered gear altitude signal primarily is produced on the basis of the vertical inertial acceleration signals prior to the time at which the aircraft reaches the runway threshold and is primarily produced on the basis of the aircraft gear altitude signal after the aircraft crosses runway threshold. The result is the reduction of the filtered gear altitude signal variation that can be caused by irregular terrain along the landing approach path while maintaining signal sensitivity to runway slope and runway slope variation.

公开(公告)号：EP0441007A3

公开(公告)日：1992-08-26

申请号：EP90203502.1

申请日：1990-12-21

申请人： THE BOEING COMPANY

发明人： Orgun, Munir ,  Flannigan, Sean Joseph

IPC分类号： G01M1/12 ,  G05D1/06

CPC分类号： G01M1/127

摘要： Disclosed is a method of and an arrangement for real time estimation of the location of the center of gravity of an aircraft. The center of gravity estimate is utilized in an aircraft flight control system for effecting flight control laws in which the center of gravity is a parameter that at least in part establishes open loop compensation or feedback gain. The disclosed method and arrangement are specifically adapted for establishing stabilizer mistrim during a landing procedure in which an aircraft flight control system is automatically controlling the aircraft. The method generally comprises the steps of generating a signal that represents the product of the aircraft stabilizer position and a multiplicative factor, A₁ and adding to that product an additive factor, A₂. The multiplicative factor, A₁, and the additive factor, A₂, both are determined on the basis of the angle of attack of the aircraft and the aircraft flap setting.