-
公开(公告)号：US5860625A
公开(公告)日：1999-01-19
申请号：US827875
申请日：1996-12-30
申请人： Chuong B. Tran , Stephen White
发明人： Chuong B. Tran , Stephen White
CPC分类号： G05D1/0825
摘要： An aircraft modal suppression system which recognizes that the frequency and phase of the body bending mode varies when the weight of the aircraft differs from the design gross weight. An active damper notch filter which is tabulated as a function of aircraft gross weight is utilized, thereby enabling not only the frequency, but also the width and depth of the notch filter to vary according to the gross weight of the aircraft.
-
公开(公告)号：US5667166A
公开(公告)日：1997-09-16
申请号：US600779
申请日：1996-02-13
申请人： Chuong B. Tran , Stephen White
发明人： Chuong B. Tran , Stephen White
CPC分类号： G05D1/0816
摘要： An aircraft modal suppression system which recognizes that the frequency and phase of the body bending mode varies when the weight of the aircraft differs from the design gross weight. An active damper notch filter which is tabulated as a function of aircraft gross weight is utilized, thereby enabling not only the frequency, but also the width and depth of the notch filter to vary according to the gross weight of the aircraft.
摘要翻译： 一种飞机模态抑制系统，其识别当飞行器的重量与设计总重量不同时，身体弯曲模式的频率和相位发生变化。 利用作为飞机总重量的列表的主动阻尼器陷波滤波器，从而不仅使陷波滤波器的频率而且宽度和深度都根据飞行器的总重量而变化。
-
公开(公告)号：US5833173A
公开(公告)日：1998-11-10
申请号：US731043
申请日：1996-10-08
申请人： Chuong B. Tran , Stephen White
发明人： Chuong B. Tran , Stephen White
CPC分类号： G05D1/0816
摘要： An aircraft modal suppression system which recognizes that the frequency and phase of the body bending mode varies when the weight of the aircraft differs from the design gross weight. An active damper notch filter which is tabulated as a function of aircraft gross weight is utilized, thereby enabling not only the frequency, but also the width and depth of the notch filter to vary according to the gross weight of the aircraft.
-
公开(公告)号：US5452865A
公开(公告)日：1995-09-26
申请号：US86447
申请日：1993-06-28
申请人： Chuong B. Tran , Stephen White
发明人： Chuong B. Tran , Stephen White
CPC分类号： G05D1/0825
摘要： An aircraft modal suppression system which recognizes that the frequency and phase of the body bending mode varies when the weight of the aircraft differs from the design gross weight. An active damper notch filter which is tabulated as a function of aircraft gross weight is utilized, thereby enabling not only the frequency, but also the width and depth of the notch filter to vary according to the gross weight of the aircraft.
摘要翻译： 一种飞机模态抑制系统，其识别当飞行器的重量与设计总重量不同时，身体弯曲模式的频率和相位发生变化。 利用作为飞机总重量的列表的主动阻尼器陷波滤波器，从而不仅使陷波滤波器的频率而且宽度和深度都根据飞行器的总重量而变化。
-
公开(公告)号：US5072893A
公开(公告)日：1991-12-17
申请号：US055801
申请日：1987-05-28
IPC分类号： G05D1/08
CPC分类号： G05D1/0825
摘要： Accelerations due to excitation of the natural modes of an aircraft's body are suppressed by an active suppression system. Dedicated accelerometers are positioned in the aircraft at optimal locations for sensing modal induced lateral accelerations. The accelerometer produced signals are processed through control logic which, in response thereto, and in response to aircraft velocity and altitude related signals produces output control signals. The control signals effect rudder deployment creating forces to suppress the natural mode induced accelerations.
-
公开(公告)号：US06915989B2
公开(公告)日：2005-07-12
申请号：US10136907
申请日：2002-05-01
IPC分类号： B64C13/16
CPC分类号： B64C13/16 , B64C2220/00
摘要： Vibrations due to excitation of the natural modes of an aircraft's body are suppressed by an active multi-axis modal suppression system. Dedicated sensors are positioned in the aircraft at optimal locations for sensing modal induced vibrations. The sensor produced signals are processed through control logic which, in response thereto, and in response to aircraft inertial, velocity and altitude related signals produces output control signals. The control signals effect control surface deployment creating forces to suppress the natural mode induced vibrations on multiple geometric axis's. More particularly, symmetric and anti-symmetric control surface deployments are used on one or more geometric axis's to damp lateral, longitudinal, vertical and most importantly torsional vibrational modes.
摘要翻译： 通过主动多轴模态抑制系统抑制由于飞机身体的自然模式的激发引起的振动。 专用传感器位于飞行器的最佳位置，用于感测模态诱发的振动。 传感器产生的信号通过控制逻辑进行处理，响应于此，响应于飞机惯性，速度和高度相关的信号产生输出控制信号。 控制信号影响控制表面部署，产生力以抑制多个几何轴上的自然模式引起的振动。 更具体地说，在一个或多个几何轴上使用对称和反对称的控制表面布置以阻止侧向，纵向，垂直和最重要的扭转振动模式。
-
公开(公告)号：US20100078518A1
公开(公告)日：2010-04-01
申请号：US12239278
申请日：2008-09-26
CPC分类号： B64C13/26 , B64C13/16 , B64C13/44 , G05D1/0066 , Y02T50/44
摘要： A method for controlling control surfaces. A position limit is identified for movement of a control surface based on a load limit set for the control surface and a number of vehicle current operation parameters to form an identified position limit. Responsive to receiving a command to move the control surface on a vehicle to a new position, the control surface is commanded to move to a position within the identified position limit.
摘要翻译： 一种控制面的控制方法。 基于为控制表面设置的负载极限和车辆当前操作参数的数量来识别用于控制表面的移动的位置限制，以形成所识别的位置限制。 响应于接收到将车辆上的控制表面移动到新位置的命令，控制表面被命令移动到所识别的位置限制内的位置。
-
公开(公告)号：US08342445B2
公开(公告)日：2013-01-01
申请号：US12239278
申请日：2008-09-26
IPC分类号： B64C9/00
CPC分类号： B64C13/26 , B64C13/16 , B64C13/44 , G05D1/0066 , Y02T50/44
摘要： A method for controlling control surfaces. A position limit is identified for movement of a control surface based on a load limit set for the control surface and a number of vehicle current operation parameters to form an identified position limit. Responsive to receiving a command to move the control surface on a vehicle to a new position, the control surface is commanded to move to a position within the identified position limit.
摘要翻译： 一种控制面的控制方法。 基于为控制表面设置的负载极限和车辆当前操作参数的数量来识别用于控制表面的移动的位置限制，以形成所识别的位置限制。 响应于接收到将车辆上的控制表面移动到新位置的命令，控制表面被命令移动到所识别的位置限制内的位置。
-
公开(公告)号：US07191985B2
公开(公告)日：2007-03-20
申请号：US11180309
申请日：2005-07-12
IPC分类号： B64C13/16
CPC分类号： B64C13/16 , B64C2220/00
摘要： Vibrations due to excitation of the natural modes of an aircraft's body are suppressed by an active multi-axis modal suppression system. Dedicated sensors are positioned in the aircraft at optimal locations for sensing modal induced vibrations. The sensor produced signals are processed through control logic which, in response thereto, and in response to aircraft inertial, velocity and altitude related signals produces output control signals. The control signals effect control surface deployment creating forces to suppress the natural mode induced vibrations on multiple geometric axis's. More particularly, a symmetric and anti-symmetric control surface deployments are used on one or more geometric axis'to damp lateral, longitudinal, vertical and most importantly torsional vibrational modes.
摘要翻译： 通过主动多轴模态抑制系统抑制由于飞机身体的自然模式的激发引起的振动。 专用传感器位于飞行器的最佳位置，用于感测模态诱发的振动。 传感器产生的信号通过控制逻辑进行处理，响应于此，响应于飞机惯性，速度和高度相关的信号产生输出控制信号。 控制信号影响控制表面部署，产生力以抑制多个几何轴上的自然模式引起的振动。 更具体地，在一个或多个几何轴线上使用对称和反对称的控制表面布置来减弱横向，纵向，垂直和最重要的扭转振动模式。
-
10.发明授权Method and apparatus for turn coordination gain as a function of flap position 失效旋转协调增益作为挡板位置的函数的方法和装置
公开(公告)号：US5839697A
公开(公告)日：1998-11-24
申请号：US645616
申请日：1996-05-14
申请人： Chuong B. Tran
发明人： Chuong B. Tran
CPC分类号： G05D1/085
摘要： An improved method and apparatus for determining the amount of turn coordination gain in an aircraft yaw damper during a turn maneuver is disclosed. The yaw damper includes inputs from the inertial reference units of the aircraft and also from the flight management computer of the aircraft. The flight management computer provides to the yaw damper a signal indicative of the position of the flaps of the aircraft. The yaw damper includes a turn coordination gain box that receives the flap position signal and outputs a turn coordination gain value, dependent upon the flap position. Generally, the turn coordination gain value increases as the flap position is more extended. The precise turn coordination gain value for each flap position is dependent upon the particular aerodynamic characteristics of the aircraft.
摘要翻译： 公开了一种改进的方法和装置，用于在转弯机动期间确定飞行器偏航阻尼器中的转向协调增益的量。 偏航阻尼器包括来自飞行器的惯性参考单元以及飞行器的飞行管理计算机的输入。 飞行管理计算机向偏航阻尼器提供指示飞行器襟翼位置的信号。 偏航阻尼器包括转向协调增益箱，其接收挡板位置信号并根据挡板位置输出转弯协调增益值。 通常，转动协调增益值随着挡板位置的延伸而增加。 每个襟翼位置的精确转弯协调增益值取决于飞机的特定空气动力特性。
-
-
-
-
-
-
-
-
-
搜索结果
10 条记录 (耗时 0.016 秒)
