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1. 发明授权

US5669582A Method and apparatus for reducing unwanted sideways motion in the aft cabin and roll-yaw upsets of an airplane due to atmospheric turbulence and wind gusts 失效
公开(公告)号：US5669582A
公开(公告)日：1997-09-23
申请号：US440339
申请日：1995-05-12
申请人： William F. Bryant , Arun A. Nadkarni , Paul Salo
发明人： William F. Bryant , Arun A. Nadkarni , Paul Salo
IPC分类号： B64C13/18 , B64C13/16 , G05D1/00 , G05D1/08
CPC分类号： B64C13/16 , G05D1/0816
摘要： A method and apparatus for reducing the unwanted sideways motion of an airplane by reducing the lateral side loads and upsets caused by atmospheric turbulence and gusts is disclosed. A rudder modification command that causes the rudder command of the airplane to be changed in a manner that relieves the net force across the vertical stabilizer of the airplane caused by atmospheric turbulence and gusts is produced. More specifically, the pressure differential across opposite sides of the vertical stabilizer is measured and used to produce a rudder deflection value that is roll rate and yaw rate compensated. The compensated deflection value is high-pass filtered with a corner frequency that is twenty-five percent (25%) of the Dutch roll frequency of the airplane. The result is a first rudder deflection value that is subtractively combined with a second rudder deflection value. The second rudder deflection value is derived by gain adjusting and low-pass filtering the inertial sideslip angle rate value produced by the airplane's yaw damper. The low-pass filter has a corner frequency that is also twenty-five percent (25%) of the Dutch roll frequency of the airplane. The combined rudder deflection value is modified by a steady sideslip gain value and filtered by a gain shaping filter. The gain shaping filter increases the gain above the Dutch roll frequency of the airplane. The resultant rudder modification command is subtractively combined with the yaw damper rudder command to produce a rudder command. Preferably, a flow separation monitor is included to prevent the rudder modification command from producing a rudder command that exceeds allowable structural limits. Also, preferably, the rudder modification command is used to produce a lateral control command that is used to suppress rigid body roll response and improve handling qualities by gain adjusting and low-pass filtering the rudder modification command.

2. 发明授权

US5598991A Method and apparatus for detecting oscillatory phenomena indicative of airflow separation 失效
标题翻译：用于检测指示气流分离的振荡现象的方法和装置
公开(公告)号：US5598991A
公开(公告)日：1997-02-04
申请号：US437405
申请日：1995-05-12
申请人： Arun A. Nadkarni , William F. Bryant
发明人： Arun A. Nadkarni , William F. Bryant
IPC分类号： B64C5/00 , B64D45/00 , G05D1/00 , G05D1/08 , B64C13/16
CPC分类号： G05D1/0816 , G05D1/0055
摘要： A method and apparatus for detecting oscillatory phenomena indicative of airflow separation or sensor common mode oscillatory failure is disclosed. The oscillations of a differential pressure transducer that senses the pressure difference on the opposite sides of an airfoil are bandpass filtered to remove oscillations lying outside of a band of interest. Oscillation peaks lying within the passband that exceed a positive or negative threshold produce pulses that are counted. The counter value is decremented each time an alternating peak is not detected within one-half cycle of a minimum frequency. If the allowable count threshold is exceeded, a latch is set. Setting the latch produces a command that can be used to inhibit the operation of systems that rely on data produced by the differential pressure transducer. An alternative path senses the position of a control element (e.g., rudder pedal position) and sets the latch if the control element position reaches an extreme value likely to produce an oscillation condition at the pressure differential transducer. The latch is reset if the oscillation condition subsides for a predetermined period of time. This provides protection against transient conditions without inhibiting control system operation for the balance of a flight.
摘要翻译：公开了一种用于检测指示气流分离或传感器共模振荡故障的振荡现象的方法和装置。感测翼型的相对侧上的压力差的差压传感器的振荡被带通滤波以去除位于感兴趣的带外的振荡。位于通带内的超过正或负阈值的振荡峰产生计数的脉冲。每当在最小频率的半个周期内没有检测到交替峰值时，计数器值递减。如果超过允许的计数阈值，则设置锁存器。设置闩锁产生一个命令，可用于禁止依赖差压传感器产生的数据的系统的操作。替代的路径感测控制元件的位置（例如，方向舵踏板位置），并且如果控制元件位置达到可能在压差传感器处产生振荡状态的极值，则设置闩锁。如果振荡条件消除了预定的时间段，则锁存器被复位。这提供了对瞬态条件的保护，而不会妨碍飞行平衡的控制系统操作。

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