1
Norman G Tarleton Jr, Dean R Wilkens, Peter F Symosek: Method and apparatus for navigating an aircraft from an image of the runway. Honeywell International, December 5, 2000: US06157876 (37 worldwide citation)

An image sensor attached to an aircraft generates an image. The image includes a runway and other objects. The edges within the image are detected and Nav Data is used to predict the coordinates defining the runway. The predicted coordinates and the detected edges are correlated to determine the loc ...


2
Mark I Snyder, Dean R Wilkens: Cockpit display having 3D flight path error symbology. Honeywell International, November 20, 2001: US06320579 (27 worldwide citation)

A primary flight display (PFD) for an aircraft generating a 3-dimensional (3D) symbology indicative of the aircraft situational information. The 3D symbology includes a 3D vertical path error symbol and a 3D lateral flight path error symbol. Several 3D altitude symbols are also displayed which colle ...


3
Ronald E Strong, Dean R Wilkens: Dual lane control of a permanent magnet brushless motor using non-trapezoidal commutation control. Honeywell International, Ingrassia Fisher & Lorenz P C, December 27, 2011: US08084972 (4 worldwide citation)

A motor control system and method implements non-trapezoidal motor control and meets established “fail passive” regulatory guidelines. In particular, a system and method of controlling a multi-phase brushless motor that includes a multi-pole permanent magnet rotor, and an individual, electrically is ...


4
Dean R Wilkens, Dan B Harned, Norman W Hawn: Ripple free amplitude demodulator. Sperry Corporation, Howard P Terry, January 17, 1984: US04426623 (4 worldwide citation)

A pulse sample demodulator which has a first sample and hold circuit detects the peak amplitude of the time varying waveform during a short sampling interval. The first sample and hold circuit is triggered by narrow pulses produced by a circuit responsive to the occurrence of each peak in the time v ...


5
Dean R Wilkens: Rate limited active pilot inceptor system and method. Honeywell International, Ingrassia Fisher & Lorenz P C, August 23, 2011: US08002220 (3 worldwide citation)

A variable rate limit is implemented in an active inceptor haptic feedback control system. The rate limit is modulated based on a rate error between an aircraft rate command supplied from the active inceptor, and actual aircraft rate. As the rate error increases, the rate limit is reduced, which lim ...


6
Casey Hanlon, Dean R Wilkens, Pablo Bandera, Toren S Davis: Aircraft flight control user interface linkage system. Honeywell International, Ingrassia Fisher & Lorenz P C, January 5, 2010: US07640743

A user interface linkage system includes first and second user interfaces that are linked by a single hydraulic circuit. The system is configured to provide compensation for relatively slow changes in hydraulic fluid pressure due, for example, to temperature variations. The system is also configured ...


7
Casey Hanlon, Calvin C Potter, Paul T Wingett, Dean R Wilkens, Stephen G Abel: Active pilot flight control stick system with passive electromagnetic feedback. Honeywell International, Honeywell International, July 3, 2008: US20080156939-A1

A pilot flight control stick haptic feedback mechanism provides variable force feedback to the pilot flight control stick. The flight control stick is movable to a control position in a displacement direction. A motor control unit is operable to selectively supply motor feedback signals to a motor t ...


8
Bryan H Hill, Dean R Wilkens: Method and apparatus for fine resolution brushless motor control. Honeywell International, April 29, 2004: US20040080290-A1

A motor controller (30) includes three analog Hall-effect sensors (42, 44, 46) for forming continuous-time signals proportional to the sine and cosine of the position of the rotor (24) of a motor (20). The sine and cosine signals are differentiated to obtain signals proportional to the rotor rate ti ...


9
Dean R Wilkens: Rate limited active pilot inceptor system and method. Honeywell International, Honeywell International, December 10, 2009: US20090302171-A1

A variable rate limit is implemented in an active inceptor haptic feedback control system. The rate limit is modulated based on a rate error between an aircraft rate command supplied from the active inceptor, and actual aircraft rate. As the rate error increases, the rate limit is reduced, which lim ...


10
Casey Hanlon, Dean R Wilkens, Pablo Bandera, Toren S Davis: Aircraft flight control user interface linkage system. Honeywell International, Honeywell International, February 12, 2009: US20090039205-A1

A user interface linkage system includes first and second user interfaces that are linked by a single hydraulic circuit. The system is configured to provide compensation for relatively slow changes in hydraulic fluid pressure due, for example, to temperature variations. The system is also configured ...