-
公开(公告)号：US4817046A
公开(公告)日：1989-03-28
申请号：US849983
申请日：1986-04-10
申请人： Robert W. Rice , David H. Sweet , Charles W. Evans , Gregory P. Wright , James J. Howlett , Nicholas D. Lappos , Mark A. Johnston
发明人： Robert W. Rice , David H. Sweet , Charles W. Evans , Gregory P. Wright , James J. Howlett , Nicholas D. Lappos , Mark A. Johnston
CPC分类号： G05D1/0072 , F02C9/28 , F02C9/42 , F05D2270/09
摘要： Primary logic (116-128) for engine failure detection in a multi-engine aircraft is based on thresholds for engine torque (Q), gas generator speed (NG), power turbine inner stage temperature (T5), power turbine speed (NF), throttle setting (PLA), and throttle manipulation (PLADOT).Subroutines for return to dual engine operation (110), backup of the primary logic (200,300) and remaining engine failure (200) are disclosed.
摘要翻译： 在多引擎飞机中用于发动机故障检测的主要逻辑（116-128）基于发动机扭矩（Q），气体发生器速度（NG），动力涡轮机内部温度（T5），动力涡轮机速度（NF） ，油门设定（PLA）和油门操纵（PLADOT）。 公开了用于返回双发动机操作（110），主逻辑（200,300）的备份和剩余发动机故障（200）的子程序。
-
2.发明授权
公开(公告)号：US4168045A
公开(公告)日：1979-09-18
申请号：US881994
申请日：1978-02-28
申请人： Gregory P. Wright , Don L. Adams
发明人： Gregory P. Wright , Don L. Adams
CPC分类号： G05D1/0841
摘要： A bias actuator, such as an extensible link, in the longitudinal cyclic pitch channel of a helicopter is provided with inputs as a function of airspeed multiplied inversely with collective pitch, and as a function of the rate of change of collective pitch stick position, so as to enforce positive angle of attack and speed stability and positive static pitch trim gradient and to decouple collective pitch from the longitudinal cyclic pitch channel at cruise airspeeds, the invention compensates, inter alia, adverse control effects of tail stabilizer surfaces at cruise speeds. A pair of indicators display bias commands and actual bias responses.
摘要翻译： 在直升机的纵向循环俯仰通道中的PG，1A等偏置致动器（例如可伸缩的连杆）被提供有作为与共同桨距相反的空速的函数的输入，并且作为集体节距的变化率的函数 从而实现正的迎角和速度稳定性以及正的静态俯仰修剪梯度，并且在巡航速度下将集体节距与纵向循环俯仰通道分离，本发明尤其补偿尾部稳定器表面的不利控制效果 巡航速度。 一对指示器显示偏置命令和实际偏置响应。
-
公开(公告)号：US5339244A
公开(公告)日：1994-08-16
申请号：US929323
申请日：1992-08-13
CPC分类号： G05D1/0066
摘要： An integrated time/limit exceedance cue system including a plurality of dedicated subsystem sensors, a processing unit, and a graphics generating/processing unit that is operative to generate an event dependent, time varying visual cue indicative of the exceedance of an established normal operating limit of a specific aircraft subsystem and operation thereof in a time critical exceedance condition. The time varying visual cue provides a relative indication of the elapsed time of operation of the specific subsystem in the time critical exceedance condition. The time varying visual cue is a symbolic image in the form of an outline, having a predetermined length, that defines a void region. The void region is proportionately opaqued or "filled in" in correspondence with the elapsed time of operation of the specific subsystem in the time critical exceedance condition. The outline of the visual cue may be shaped and/or have a spatial orientation that is cognitively connected to the particular subsystem and/or to a symbolic image or display representing the specific generated status data provided by the dedicated subsystem sensors for monitoring the operation of the particular subsystem. The cue system may provide a corrective action cue in conjunction with the time varying visual cue that provides information as to the appropriate recovery procedure to restore the particular subsystem to operation within its established normal operating range.
摘要翻译： 包括多个专用子系统传感器，处理单元和图形生成/处理单元的集成时间/极限超越提示系统，其可操作以产生指示所建立的正常操作极限超时的事件依赖的时变视觉提示 的特定飞机子系统及其在时间关键超越条件下的操作。 时变视觉提示提供了在时间关键超越条件下特定子系统的经过时间的相对指示。 时变视觉提示是具有限定空隙区域的具有预定长度的轮廓形式的符号图像。 空隙区域与时间关键超过条件下特定子系统的经过时间相对应地成比例地不透明或“填充”。 视觉提示的轮廓可以被成形和/或具有认知连接到特定子系统和/或表示由专用子系统传感器提供的特定生成状态数据的符号图像或显示器的空间取向，用于监视操作 特定子系统。 提示系统可以与时变视觉提示一起提供校正动作提示，该视频提示提供关于将特定子系统还原到其建立的正常操作范围内的操作的适当恢复过程的信息。
-
公开(公告)号：USD266431S
公开(公告)日：1982-10-05
申请号：US174779
申请日：1980-08-04
-
-
-
搜索结果
4 条记录 (耗时 0.018 秒)
