By Steering Or Yaw Patents (Class 244/184)
  • Patent number: 10438494
    Abstract: Methods and systems for generating flight plans for aerial vehicles based at least in part on communication performance are described. First information about a set of access points may be accessed. Second information about a flight path for an aerial vehicle to move from a first point to a second point may be accessed. A set of directions for the aerial vehicle to move between the first point and the second point may be generated. The set of directions may be generated based at least in part on a communication criterion and the second information about the flight path. The flight path may be updated based at least in part on the set of directions.
    Type: Grant
    Filed: October 10, 2016
    Date of Patent: October 8, 2019
    Assignee: Amazon Technologies, Inc.
    Inventor: Camerin Cole Hahn
  • Patent number: 10407179
    Abstract: A vehicle system includes a control unit with a weather module configured to receive weather data and to identify a wind shear zone at a location based on the weather data, the weather module further configured to generate wind shear coordinate data and wind shear characteristic data based on the weather data. The control unit further includes a display module configured to generate display commands based on the wind shear coordinate data and wind shear characteristic data from the weather module. The vehicle system further includes a display device coupled to receive the display commands from the control unit and configured to display a three-dimensional forward perspective view corresponding to a vehicle environment. The display device is further configured to display first wind shear symbology within the view at a position that indicates the location of the wind shear zone.
    Type: Grant
    Filed: October 17, 2016
    Date of Patent: September 10, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Jayasenthilnathan B, Saravanakumar Gurusamy, Madhava Gadicherla, Roger Burgin
  • Patent number: 10189513
    Abstract: A method of controlling an active aerodynamic element for a vehicle includes determining a target position for the active aerodynamic element from a target aerodynamic force, which may be a given value that is provided based on dynamic conditions of the vehicle. The method actuates the active aerodynamic element to the target position and senses an aerodynamic response characteristic of the active aerodynamic element while actuated to the target position. An estimated applied aerodynamic force is determined from the aerodynamic response characteristic, and is compared to the target aerodynamic force. A force error is determined from the comparison of the estimated applied aerodynamic force and the target aerodynamic force, and a modified position for the active aerodynamic element is determined from the force error and the target aerodynamic force. The active aerodynamic element is actuated to the modified position.
    Type: Grant
    Filed: September 14, 2016
    Date of Patent: January 29, 2019
    Assignee: GM Global Technology Operations LLC
    Inventor: Edward T. Heil
  • Patent number: 9933451
    Abstract: A method for determining a state of credibility of measurements of an angle-of-attack sensor of an aircraft is provided. This method includes at least one coherence test between angle-of-attack measurements from said angle-of-attack sensor, and the measurements of a flight characteristic of the aircraft, distinct from the angle-of-attack. The coherence test includes determining an angle-of-attack value from said angle-of-attack sensor, determining said flight characteristic of the aircraft, determining a value of at least one indicator of the coherence of the angle-of-attack value with the value of said flight characteristic, and activating a low state of credibility, in which the measurements of said angle-of-attack sensor are deemed unreliable, or an intermediate state of credibility, in which the measurements from said angle-of-attack sensor are deemed coherent with said flight characteristic, based on the value of said coherence indicator.
    Type: Grant
    Filed: March 26, 2013
    Date of Patent: April 3, 2018
    Assignee: DASSAULT AVIATION
    Inventor: Sebastien Dupont De Dinechin
  • Patent number: 9805609
    Abstract: A system for determining a region of interest for an imaging device based on instrument landing system (ILS) is provided herein. The system may include an imaging device attached to an aircraft; an ILS detector; a computer processor configured in to calculate in a line of sight between said aircraft and a planned touch down point, based on the received ILS signals; a touchdown positioning module executed by the computer processor and configured to calculate a position in a field of view (FOV) of said imaging device which represents the planned touchdown point, based on said line of sight; and a region of interest (ROI) module executed by the computer processor and configured to define a region of interest (ROI) of the imaging device based on said position in said FOV, wherein said computer processor is further configured to apply an image processing operation only to data within said ROI.
    Type: Grant
    Filed: June 2, 2014
    Date of Patent: October 31, 2017
    Assignee: ELBIT SYSTEMS LTD.
    Inventor: Omer Hasharoni
  • Patent number: 9731818
    Abstract: A control system configured to control a deceleration process of an air vehicle which comprises at least one tiltable propulsion unit, each of the at least one tiltable propulsion units is tiltable to provide a thrust whose direction is variable at least between a general vertical thrust vector direction and a general longitudinal thrust vector direction with respect to the air vehicle.
    Type: Grant
    Filed: January 10, 2013
    Date of Patent: August 15, 2017
    Assignee: ISRAEL AEROSPACE INDUSTRIES LTD.
    Inventors: Guy Dekel, Lior Zivan, Yoav Efraty, Amit Wolff, Avner Volovick
  • Patent number: 9632622
    Abstract: Ground detection of a touch sensitive device is disclosed. The device can detect its grounded state so that poor grounding can be selectively compensated for in touch signals outputted by the device. The device can include one or more components to monitor certain conditions of the device. The device can analyze the monitored conditions to determine the grounding condition of the device. The device can apply a function to compensate its touch signal outputs if the device determines that it is poorly grounded. Conversely, the device can omit the function if the device determines that it is well grounded.
    Type: Grant
    Filed: July 16, 2009
    Date of Patent: April 25, 2017
    Assignee: Apple Inc.
    Inventors: Steven Porter Hotelling, David T. Amm, Michael Lammers, John T. Orchard, Brian Michael King, Omar Leung, Deniz Teoman
  • Patent number: 9274523
    Abstract: A method for reducing yawing motions of an aircraft in-flight, wherein a spoiler adjustment drive of a spoiler and a regulating flap adjustment drive of a regulating flap of the same respective airfoil are adjusted in a time segment in such a way that the motion of the spoiler being adjusted and the motion of the regulating flap of the same airfoil deflect in mutually opposite directions in the time segment. The spoiler and the regulating flap are adjusted on the airfoil, on which the adjusted deflections counteract the respectively occurring yawing motion. Also provided are a computer program product for carrying out this method and an aircraft with a directional stabilization device for carrying out this method.
    Type: Grant
    Filed: May 4, 2012
    Date of Patent: March 1, 2016
    Assignee: Airbus Operations GmbH
    Inventor: Hans-Gerd Giesseler
  • Patent number: 9272770
    Abstract: A method and apparatus for carrying out a symmetric deflection of the spoilers so as to reduce the lift of the aircraft during a takeoff roll thereby improving lateral and directional control on the ground.
    Type: Grant
    Filed: March 8, 2013
    Date of Patent: March 1, 2016
    Assignee: Airbus Operations (SAS)
    Inventors: Benoit Joalland, Martin Delporte
  • Patent number: 9139295
    Abstract: The invention relates to a method of controlling the steering of a steerable portion of an aircraft undercarriage that is fitted both with a steering member for steering the steerable portion and also with at least two angular position sensors for sensing the angular position of the steerable portion in order to deliver respective signals representative of the angular position of the steerable portion, wherein the steering member is controlled by means of servo-control using information that is representative of the angular position of the steerable portion. According to the invention, the information representative of the angular position that is used is a mean of the angular positions sensed by the at least two angular position sensors.
    Type: Grant
    Filed: June 22, 2012
    Date of Patent: September 22, 2015
    Assignee: MESSIER-BUGATTI-DOWTY
    Inventor: Michaël Benmoussa
  • Patent number: 8584989
    Abstract: The invention relates to a method of managing movement of an aircraft on the ground, the aircraft including at least one left main undercarriage and at least one right main undercarriage, each comprising wheels associated with torque application members for applying torque to the wheels in response to a general setpoint, the general setpoint comprising a longitudinal acceleration setpoint and an angular speed setpoint, the method including the successive steps of braking down the general setpoint into general torque setpoints for generating by the torque application members associated with each of the wheels.
    Type: Grant
    Filed: September 20, 2011
    Date of Patent: November 19, 2013
    Assignee: Messier-Bugatti-Dowty
    Inventors: David Lemay, David Frank, Michel Basset, Yann Chamaillard
  • Patent number: 8478456
    Abstract: Some embodiments relate to a method of controlling a flight of a flight vehicle according to a first mode of operation and changing the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation. Other embodiments relate to a flight-control system for a flight vehicle configured to control a flight of a flight vehicle according to a first mode of operation and to control the flight of the flight vehicle according to a second mode of operation to use less energy than the first mode of operation. Other embodiments relate to a control actuation system configured to control positions of aerodynamic elements in a flight vehicle in response to commands from a guidance system according to a first mode of operation and to change the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation.
    Type: Grant
    Filed: August 8, 2011
    Date of Patent: July 2, 2013
    Assignee: Raytheon Company
    Inventors: Jeffery P. Sowers, Karl F. Spiessbach, Donald E. Croft
  • Patent number: 8376266
    Abstract: A method of controlling the yaw attitude of a hybrid helicopter including a fuselage and an additional lift surface provided with first and second half-wings extending from either side of the fuselage, each half-wing being provided with a respective first or second propeller. The hybrid helicopter has a thrust control suitable for modifying the first pitch of the first blades of the first propeller and the second pitch of the second blades of the second propeller by the same amount. The hybrid helicopter includes yaw control elements for generating an original order for modifying the yaw attitude of the hybrid helicopter by increasing the pitch of the blades of one propeller and decreasing the pitch of the blades of the other propeller, the original order is optimized as a function of the position of the thrust control to obtain an optimized yaw control order that is applied to the first and second blades.
    Type: Grant
    Filed: May 5, 2010
    Date of Patent: February 19, 2013
    Assignee: Eurocopter
    Inventors: Bernard Gemmati, Nicolas Queiras, Paul Eglin
  • Patent number: 8359129
    Abstract: A method and device control the thrust of a multi-engine aircraft. At least one engine command is determined by a command determining unit, with the determined command commanding each engine that has not failed to deliver a thrust substantially equal to a reduced thrust value. A command application unit is configured to apply the determined command to each aircraft engine that has not failed. The reduced thrust value is determined, by a weight determining device, according to the current weight of the aircraft and according to a reduced thrust value FOEI, which is calculated by a thrust calculation unit.
    Type: Grant
    Filed: March 8, 2007
    Date of Patent: January 22, 2013
    Assignee: Airbus Operations SAS
    Inventors: Benoît Lemaignan, Gérard Mathieu
  • Patent number: 8209068
    Abstract: A control system (12) for controlling velocity and attitude of a dynamic system (20) includes a velocity controller configured to receive a desired velocity command and output a velocity error in the form of Euler angle commands to an attitude controller system. The attitude controller system includes a converter (14) configured to receive the Euler angle commands and output a desired quaternion based on the Euler angle commands. The attitude controller system further includes an attitude error generator (16) configured to receive the desired quaternion and an estimated quaternion indicative of an estimated velocity and attitude of the dynamic system (20) and to output attitude errors associated with the dynamic system (20). The attitude controller system also includes an attitude controller (18) configured to receive the attitude errors and to output error commands to the dynamic system (20) based on the attitude errors.
    Type: Grant
    Filed: June 2, 2005
    Date of Patent: June 26, 2012
    Assignee: Rockwell Collins Control Technologies, Inc.
    Inventors: David William Vos, Vladislav Gavrilets, Michael Daniel Piedmonte
  • Patent number: 8200421
    Abstract: An altitude profile representative of the terrain overflown by an aircraft is established. Thereafter, an altitude limit curve which comprises an intersection with the altitude profile upon the engagement of a terrain avoidance maneuver is determined. As soon as there is no longer any intersection of the limit curve with the altitude profile, the terrain avoidance maneuver is interrupted.
    Type: Grant
    Filed: October 20, 2009
    Date of Patent: June 12, 2012
    Assignee: Airbus Operations SAS
    Inventors: Paule Botargues, Nicolas Caule, Christelle Ledauphin, Jerome Bailly, Isabelle Lacaze, Sylvain Thezelais, Jerome Goyet
  • Patent number: 8185259
    Abstract: The fuzzy logic-based control method for helicopters carrying suspended loads utilizes a controller based on fuzzy logic membership distributions of sets of load swing angles. The anti-swing controller is fuzzy-based and has controller outputs that include additional displacements added to the helicopter trajectory in the longitudinal and lateral directions. This simple implementation requires only a small modification to the software of the helicopter position controller. The membership functions govern control parameters that are optimized using a particle swarm algorithm. The rules of the anti-swing controller are derived to mimic the performance of a time-delayed feedback controller. A tracking controller stabilizes the helicopter and tracks the trajectory generated by the anti-swing controller.
    Type: Grant
    Filed: August 23, 2010
    Date of Patent: May 22, 2012
    Assignee: King Fahd University of Petroleum & Minerals
    Inventor: Hanafy M. Omar
  • Patent number: 8175760
    Abstract: A device comprises means for computing the air-craft (A) current position, means for determining at least one maximum permitted deviation (E1) around a set position of the flight path of the flight plan according to accuracy and integrity performances of said current position computation and to the restriction of a flight range authorized in a flight corridor (6A, 6B), and a display system (7) for displaying at least one a distance scale (9) on a viewing screen (8), at least one a fixed symbol (10) displaying the current position and two movable pointers (13, 14) displaying the limits of said maximum permitted deviation (E1).
    Type: Grant
    Filed: June 19, 2006
    Date of Patent: May 8, 2012
    Assignee: Airbus Operations SAS
    Inventors: Patrice Rouquette, Nolween Laveant, Didier Have, Arnaud Le Tellier
  • Patent number: 8072172
    Abstract: A redundant electromechanical actuator is provided that includes first and second electric motors, a common output shaft, first and second drive cable drums, first and second driven cable drums, a first cable, and a second cable. The first and second electric motors are each adapted to be controllably energized to supply a drive torque. The common output shaft is coupled to receive the drive torque supplied from one or both of the motors. The first and second drive cable drums are coupled to the common output shaft to receive the drive torque from one or both of the motors. The first and second driven cable drums are each configured, upon being driven, to rotate. The first cable is coupled between the first drive cable drum and the first driven cable drum, and the second cable is coupled between the second drive cable drum and the second driven cable drum.
    Type: Grant
    Filed: January 29, 2009
    Date of Patent: December 6, 2011
    Assignee: Honeywell International Inc.
    Inventors: Casey Hanlon, David M. Eschborn
  • Patent number: 7756637
    Abstract: Methods and systems for a position indicating display system for an aircraft are provided. The system includes a map display unit configured to display a map representative of an area being traversed by the aircraft, and an overlay comprising an own ship depiction, said overlay displayed on the map for a period of time in response to an input from at least one of a user and an aircraft sensor.
    Type: Grant
    Filed: December 21, 2006
    Date of Patent: July 13, 2010
    Assignee: The Boeing Company
    Inventors: Patrick Ralf Wipplinger, Richard William Ellerbrock
  • Patent number: 7731122
    Abstract: The invention relates to a method for managing a steering control of an aircraft landing gear provided with at least one wheel steerable by the steering control, comprising the following steps: monitoring one or several taxi parameter(s) (51, 54, 64, 59, 61) of the aircraft to determine whether said aircraft enters a towing situation, setting the steering control in a free steering mode of the steerable wheel, if the aircraft enters the towing situation; activating the steering control so that the steerable wheel has an angular controlled steering by the steering control if the aircraft leaves said towing situation.
    Type: Grant
    Filed: December 27, 2007
    Date of Patent: June 8, 2010
    Assignee: Messier-Bugatti
    Inventor: David Frank
  • Patent number: 7539561
    Abstract: An objective of the invention, focusing on these issues involved in the use of a small, hobby-type, unmanned helicopter, is to develop an autonomous control system comprising autonomous control systems for a small unmanned helicopter, to be mounted on said small unmanned helicopter; a servo pulse mixing/switching unit; a radio-controlled pulse generator; and autonomous control algorithms that are appropriate for the autonomous control of the aforementioned small unmanned helicopter, thereby providing an autonomous control system that provides autonomous control on the helicopter toward target values.
    Type: Grant
    Filed: December 26, 2006
    Date of Patent: May 26, 2009
    Assignees: Hirobo Limited
    Inventors: Kenzo Nonami, Jin Ok Shin, Daigo Fujiwara, Kensaku Hazawa, Keitaro Matsusaka
  • Patent number: 7367530
    Abstract: Aerospace vehicle yaw generating systems and associated methods are disclosed herein. One aspect of the invention is directed toward a yaw generating system that can include an aerospace vehicle having a fuselage with a first portion and a second portion. The system can further include a movable control surface coupled to the fuselage and extending generally in a horizontal plane. The control surface can be movable to a deflected position in which the control surface can be positioned to create a flow pattern proximate to the fuselage when the aerospace vehicle is located in a flow field. The flow pattern can be positioned to create a pressure differential between the first portion of the fuselage and the second portion of the fuselage. The first and second portions can be located so that the pressure differential produces a yawing moment on the aerospace vehicle.
    Type: Grant
    Filed: June 21, 2005
    Date of Patent: May 6, 2008
    Assignee: The Boeing Company
    Inventors: Jeffery S. Harrigan, Henry L. Beaufrere
  • Patent number: 7206674
    Abstract: Method and system for displaying information on one or more aircraft flights, where at least one flight is determined to have at least one atypical flight phase according to specified criteria. A flight parameter trace for an atypical phase is displayed and compared graphically with a group of traces, for the corresponding flight phase and corresponding flight parameter, for flights that do not manifest atypicality in that phase.
    Type: Grant
    Filed: August 13, 2004
    Date of Patent: April 17, 2007
    Assignee: United States of America as represented by the Administrator of the National Aeronautics and Space Administration (NASA)
    Inventors: Irving C. Statler, Thomas A. Ferryman, Brett G. Amidan, Paul D. Whitney, Amanda M. White, Alan R. Willse, Scott K. Cooley, Joseph Griffith Jay, Robert E. Lawrence, Chris J. Mosbrucker, Loren J. Rosenthal, Robert E. Lynch, Thomas R. Chidester, Gary L. Prothero, Adi Andrei, Timothy P. Romanowski, Daniel E. Robin, Jason W. Prothero
  • Patent number: 7185859
    Abstract: Aerospace vehicle yaw generating systems and associated methods are disclosed herein. One aspect of the invention is directed toward a yaw generating system that can include an aerospace vehicle having a fuselage with a first portion and a second portion. The system can further include a movable control surface coupled to the fuselage and extending generally in a horizontal plane. The control surface can be movable to a deflected position in which the control surface can be positioned to create a flow pattern proximate to the fuselage when the aerospace vehicle is located in a flow field. The flow pattern can be positioned to create a pressure differential between the first portion of the fuselage and the second portion of the fuselage. The first and second portions can be located so that the pressure differential produces a yawing moment on the aerospace vehicle.
    Type: Grant
    Filed: June 21, 2005
    Date of Patent: March 6, 2007
    Assignee: The Boeing Company
    Inventors: Jeffery S. Harrigan, Henry L. Beaufrere
  • Patent number: 6937924
    Abstract: Method and system for analyzing aircraft data, including multiple selected flight parameters for a selected phase of a selected flight, and for determining when the selected phase of the selected flight is atypical, when compared with corresponding data for the same phase for other similar flights. A flight signature is computed using continuous-valued and discrete-valued flight parameters for the selected flight parameters and is optionally compared with a statistical distribution of other observed flight signatures, yielding atypicality scores for the same phase for other similar flights. A cluster analysis is optionally applied to the flight signatures to define an optimal collection of clusters. A level of atypicality for a selected flight is estimated, based upon an index associated with the cluster analysis.
    Type: Grant
    Filed: May 21, 2004
    Date of Patent: August 30, 2005
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Irving C. Statler, Thomas A. Ferryman, Brett G. Amidan, Paul D. Whitney, Amanda M. White, Alan R. Willse, Scott K. Cooley, Joseph Griffith Jay, Robert E. Lawrence, Chris Mosbrucker, Loren J. Rosenthal, Robert E. Lynch, Thomas R. Chidester, Gary L. Prothero, Adi L. Andrei, Timothy P. Romanowski, Daniel E. Robin, Jason W. Prothero
  • Patent number: 6575410
    Abstract: An airborne glide slope tracking system includes a radio altimeter for producing a signal indicative of the instantaneous altitude of the aircraft and a glide slope error indicator for producing a signal indicative of the angular deviation from glide slope. The two signals are multiplied to produce a glide slope error signal in feet and fed to a summing device directly and through a lead filter to generate a signal for a throttle servo to increase or decrease the thrust of the aircraft. A longitudinal accelerometer signal is then added to a signal indicative of a difference between an aircraft's reference angle of attack and actual angle of attack to produce a signal to a pitch command to provide an angle which will be sustained by the power of the aircraft.
    Type: Grant
    Filed: April 25, 2001
    Date of Patent: June 10, 2003
    Assignee: Safe Flight Instrument Corporation
    Inventor: Leonard M. Greene
  • Patent number: 6549829
    Abstract: The present method and apparatus consists of storing past values of estimated IRU error and using these past values to update the coasting filter when switching from GPS to inertial mode. Through the storage of past IRU error estimates, it is possible to avoid misdirected guidance from an erroneous GPS signal. The MMR and ground station can require up to 6 seconds to identify a failed GLS signal.
    Type: Grant
    Filed: October 31, 2001
    Date of Patent: April 15, 2003
    Assignee: The Boeing Company
    Inventors: Leonard R. Anderson, Steven B. Krogh, Melville D. McIntyre, Timothy Murphy
  • Patent number: 6341247
    Abstract: A measurement-based method to control and optimize the performance of an airborne vehicle. The stability and control of the vehicle is modified to induce a response in the airborne vehicle as reflected by a plurality of response signals. Excitations signals having multi-term sinusoidal waveforms are generated and applied to control signals controlling one or more control effectors. A time domain response of each of the state variables, response signals, and control signals arising from the application of the excitation inputs to the control signals is then measured. These time domain responses are then transformed into frequency domain models. The effectiveness and vehicle stability and control derivatives may then be identified from the frequency domain models of the state variables, response signals, and control signals.
    Type: Grant
    Filed: December 17, 1999
    Date of Patent: January 22, 2002
    Assignee: McDonell Douglas Corporation
    Inventors: Mark A. Hreha, Gerard Schkolnik
  • Patent number: 6102330
    Abstract: An emergency flight control system is disclosed for lateral control using only differential engine thrust modulation of multiengine aircraft having at least two engines laterally displaced to the left and right from the axis of the aircraft in response to a heading angle command .psi..sub.c to be tracked. By continually sensing the heading angle .psi. of the aircraft and computing a heading error signal .psi..sub.e as a function of the difference between the heading angle command .psi..sub.c and the sensed heading angle .psi., a track control signal is developed with compensation as a function of sensed bank angle .PHI., bank angle rate .phi., or roll rate p, yaw rate .tau., and true velocity to produce an aircraft thrust control signal ATC.sub..psi.(L,R).
    Type: Grant
    Filed: July 29, 1997
    Date of Patent: August 15, 2000
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: John J. Burken, Frank W. Burcham, Jr., John Bull
  • Patent number: 6061611
    Abstract: The invention is embodied in a method of integrating kinematics equations for updating a set of vehicle attitude angles of a vehicle using 3-dimensional angular velocities of the vehicle, which includes computing an integrating factor matrix from quantities corresponding to the 3-dimensional angular velocities, computing a total integrated angular rate from the quantities corresponding to a 3-dimensional angular velocities, computing a state transition matrix as a sum of (a) a first complementary function of the total integrated angular rate and (b) the integrating factor matrix multiplied by a second complementary function of the total integrated angular rate, and updating the set of vehicle attitude angles using the state transition matrix.
    Type: Grant
    Filed: January 6, 1998
    Date of Patent: May 9, 2000
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Stephen A. Whitmore
  • Patent number: 5712785
    Abstract: An aircraft landing determination apparatus and method for determining landing status of an aircraft by tracking arriving aircrafts and providing a unique runway assignment therefor. The aircraft landing determination apparatus includes a target processor, a track administrator, and a track reporter. The target processor culls multiple target tracks from a target data transmission provided by a target sensor. The track administrator receives the target tracks, selects at least one arrival track therefrom, and allocates a unique runway assignment to each arrival track. The track reporter receives the arrival track and runway assignment, prepares a track report thereabout, and transmits the track report to a position monitoring apparatus.
    Type: Grant
    Filed: June 23, 1995
    Date of Patent: January 27, 1998
    Assignee: Northrop Grumman Corporation
    Inventors: Din Mok, Marshall Watnick
  • Patent number: 5677685
    Abstract: This optoelectronic device is designed to provide assistance in the piloting of an aircraft under conditions of poor visibility, at the final approach stage, during taxiing and at take-off from a runway equipped with an ILS. The device consists of a collimator displaying a reticule symbolizing a runway centerline that is shown to the pilot during flight as well as on the ground, without any break between the in-flight final approach stage and the ground stage of taxiing on the runway. The device takes account of the pilot's off-centered position in the aircraft cockpit.
    Type: Grant
    Filed: October 4, 1995
    Date of Patent: October 14, 1997
    Assignee: Sextant Avionique
    Inventors: Philippe Coirier, Roger Parus
  • Patent number: 5669582
    Abstract: 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.
    Type: Grant
    Filed: May 12, 1995
    Date of Patent: September 23, 1997
    Assignee: The Boeing Company
    Inventors: William F. Bryant, Arun A. Nadkarni, Paul Salo
  • Patent number: 5657949
    Abstract: A method and apparatus for producing a dynamic thrust asymmetry airplane rudder compensation command with no direct thrust measurement is disclosed. An excess thrust estimate based on measured acceleration along the flight path of the airplane and measured vertical speed of the airplane is low pass filtered (11) to attenuate noise from the inertially derived data. The low pass filtered data is further filtered by a washout filter (15) to produce data that is sensitive only to changes in the excess thrust estimate. The input to the washout filter is frozen (13) and the output of the washout filter reduced to zero if the go-around or flare modes of the control system of the airplane are active or if the thrust asymmetry compensation feature of the primary flight computer is armed. The output of the washout filter is also zeroed when both engines are running, or multiplied by either -1 or +1 when one engine is out. Whether the multiplication is by -1 or +1 depends upon which engine is out.
    Type: Grant
    Filed: May 10, 1995
    Date of Patent: August 19, 1997
    Assignee: The Boeing Company
    Inventors: Timothy D. Deck, David W. Lochtie
  • Patent number: 5590853
    Abstract: An aircraft control system for computing a yaw compensated angle of attack is disclosed. The system includes an angle of attack sensor for generating a signal which represents an aircraft's angle of attack as determined by an angle of attack vane and a transverse accelerometer for generating a signal in response to the lateral acceleration of the aircraft. A summing device sums the two signals to thereby provide a yaw compensated angle of attack signal. The system may also include a rudder deflection sensor for generating a signal which represents the deflection of an aircraft's rudder. The rudder deflection signal is then subtracted from the yaw compensated angle of attack in the summing device. A stall warning system incorporating the yaw compensation system includes a stall warning computer for comparing the yaw compensated angle of attack signal to a predetermined value.
    Type: Grant
    Filed: February 3, 1992
    Date of Patent: January 7, 1997
    Assignee: Safe Flight Instrument Corporation
    Inventor: Leonard M. Greene
  • Patent number: 5458304
    Abstract: Spoilers, mounted on vertical stabilizer tail surfaces of large aircraft release controllable Bernoulli forces to augment rudder and aileron aircraft controls. Data from surface pressure sensors, also mounted on vertical stabilizer tail surface, is computer-interpreted to minimize tail drag and structural flight-stress. The spoilers suitable for this role include parallel lines of controllable height barriers, located on the fore part of each side of symmetrical airfoils of airplane tails.
    Type: Grant
    Filed: November 26, 1993
    Date of Patent: October 17, 1995
    Inventor: Raymond D. Gilbert
  • Patent number: 5375793
    Abstract: The present invention relates to a process for the automatic control of the control surfaces of an aircraft for the low speed compensation of a lateral path deviation, in which beyond a given deflection threshold (20) of the deflected rudder (17), there is a control of a deflection, proportional to the exceeding of the threshold, of the wing surfaces (13, 14) of one of the two wings (18), said wing being that on the side of the deflected rudder (17), so as to provide a drag supplement to said wing and therefore yaw on the aircraft.Application to the take-off of large civil transport aircraft.
    Type: Grant
    Filed: August 11, 1993
    Date of Patent: December 27, 1994
    Assignee: Aerospatiale Societe Nationale Industrielle
    Inventors: Vincent Rivron, Cecile Vollard
  • Patent number: 5361065
    Abstract: A windshear guidance system for guiding an aircraft during a microburst windshear is provided. This system includes a time comparison subassembly, an airspeed comparison subassembly and a pitch command subassembly. The pitch command subassembly includes a calibrated air speed source, latch means connected to the calibrated air speed source, switch means connected to the latch means, and a pitch guidance command unit connected to the switch means.
    Type: Grant
    Filed: May 11, 1990
    Date of Patent: November 1, 1994
    Assignee: Honeywell Inc.
    Inventors: David A. Johnson, Terry L. Zweifel, J. Rene Barrios
  • Patent number: 5265825
    Abstract: A helicopter engine fuel control anticipates sudden changes in engine power demand during yaw inputs to thereby minimize engine and main rotor speed droop and overspeed during yaw maneuvers. The rate (121,123) of yaw control (107) position change generates (110) a yaw component (104) of a helicopter fuel control (52) fuel command signal (70). The magnitude of the yaw component is also dependant upon the rate of yaw control position change (703). The fuel command signal yaw component (104) is overridden (113,115) when rotor decay rate (209,217) has been arrested during a sharp left hover turn (216); when the yaw component is removing fuel (239) during rotor droop (238); and when the yaw component is adding fuel (228) during rotor overspeed (227).
    Type: Grant
    Filed: August 26, 1992
    Date of Patent: November 30, 1993
    Assignee: United Technologies Corporation
    Inventors: Frederick J. Ebert, Joseph T. Driscoll, David H. Sweet
  • Patent number: 5213283
    Abstract: A helicopter flight control system (21) includes a model following control system architecture which automatically provides a coordinating yaw command signal to the helicopter tail rotor to coordinate helicopter flight during a low speed banked turn. The control system processes information from a variety of helicopter sensors (31) in order to provide the coordinating yaw command signal on an output line (72) to the tail rotor (20) of the helicopter.
    Type: Grant
    Filed: August 28, 1991
    Date of Patent: May 25, 1993
    Assignee: United Technologies Corporation
    Inventors: Phillip J. Gold, Walter R. Faull
  • Patent number: 5178307
    Abstract: A helicopter flight control system includes a model following control system architecture to control helicopter response about the yaw axis. The control system processes information from a variety of helicopter sensors in order to provide an output command signal to the tail rotor. Yaw control is accomplished by applying a force on a sidearm controller which provides a yaw axis command signal that is used to schedule a desired yaw rate of change. The lateral acceleration and airspeed signals are used to compute a synthesized yaw rate signal which is compared against the desired yaw rate of change, thus allowing the pilot to control lateral acceleration when he applies force on the sidearm controller.
    Type: Grant
    Filed: August 28, 1991
    Date of Patent: January 12, 1993
    Assignee: United Technologies Corporation
    Inventors: Stuart C. Wright, Don L. Adams, Phillip J. Gold
  • Patent number: 5060889
    Abstract: When an aircraft is operating in an asymmetrical flight condition, such as during a landing decrab maneuver or during inflight engine out, the pilot is normally required to make precise compensatory roll control inputs to keep the aircraft moving along its original track angle. The pilot is relieved of this compensatory roll control task by providing a control system which automatically banks the aircraft to maintain the flight of the aircraft along the selected track angle while in the asymmetrical flight condition. Further adjustments in the bank angle of the aircraft are made automatically by a track angle feedback control system so that the aircraft remains on the selected track angle even when subject to external disturbances such as crosswind gusts and shear.
    Type: Grant
    Filed: May 1, 1989
    Date of Patent: October 29, 1991
    Assignee: The Boeing Company
    Inventors: Arun A. Nadkarni, Mithra M. K. V. Sankrithi
  • Patent number: 5014053
    Abstract: A method of and apparatus for determining the actual lateral deviation from the centerline of a runway of an aircraft located outside the normal region covered by a glideslope beam is disclosed. The method comprises the steps of scaling a geometrically developed estimated lateral deviation value (Y.sub.estimate) with a compensation factor (K) and passing the result through a complementary filter. The complementary filter produces an estimated lateral deviation rate value (Y.sub.estimate) that is divided into the actual lateral deviation rate value (Y.sub.actual) produced by the inertial navigation system of the aircraft. The result of the division is the compensation factor (K) that is used to scale the geometrically developed estimated lateral deviation value. Preferably, the compensation factor is filtered by a first order lag filter prior to being used to scale the geometrically developed estimated lateral deviation value.
    Type: Grant
    Filed: January 18, 1990
    Date of Patent: May 7, 1991
    Assignee: The Boeing Company
    Inventor: Dung D. Nguyen
  • Patent number: 4916612
    Abstract: A signal selection and fault detection system that provides triple functional redundancy using the outputs (Y.sub.A, Y.sub.B) of two unmonitored primary channels and the output of one or the other of two complementary filters (22, 34) that each receive and process a signal (Y dot IRU) that is derived from a third, independent primary signal source (18) and that is representative of the rate or first derivative of the primary signals (Y.sub.A, Y.sub.B). During non-failure conditions, the system output (Y.sub.CF1) is generated by a normal mode complementary filter 22 from the synthesized rate signal (Y dot IRU) and the selected (10) midvalue one of this output signal (Y.sub.CF1) and the primary signals (Y.sub.A, Y.sub.B). In the event of a suspected failure in one of the primary signals, the output (Y.sub.IRU) of a failure mode complementary filter is substituted (16) for the system output signal (Y.sub.CF1) as the third input (C) to the midvalue selector (10).
    Type: Grant
    Filed: November 2, 1987
    Date of Patent: April 10, 1990
    Assignee: The Boeing Company
    Inventors: Richard H. Chin, Asamitsu Maeshiro, Richard W. Hess
  • Patent number: 4814764
    Abstract: A system for warning the pilot when the aircraft has reached a high yaw condition. A differential in pressure or angle of attack between the port and starboard sides of the aircraft is measured and converted into a measured sideslip angle. If the measured sideslip angle exceeds a predetermined maximum acceptable sideslip angle, a warning device, such as a rudder pedal shaker, is activated. The maximum acceptable sideslip angle is determined as a function of the ability of the aircraft flight controls to counteract a rolling moment generated by the yaw condition.
    Type: Grant
    Filed: September 30, 1986
    Date of Patent: March 21, 1989
    Assignee: The Boeing Company
    Inventor: Robin Middleton
  • Patent number: 4471280
    Abstract: An anti-log power amplifier for energizing a reversible electric motor of an electrically assisted power steering system for an automotive vehicle. The power amplifier has a preamplifier which amplifies the output signal of a torque sensor detecting the torque applied to the vehicle's steering wheel, an anti-log signal generator exponentially modifying the amplified output signal, a pulse width modulator converting the exponentially modified signal to a pair of complementary pulse width signals, and a pair of bridged power amplifiers for energizing the reversible electric motor in response to the complementary pulse width signal. The bridged power amplifiers are further responsive to the exponentially modified signal for increasing the electrical power delivered to the reversible electric motor under high torque loads.
    Type: Grant
    Filed: May 6, 1983
    Date of Patent: September 11, 1984
    Assignee: The Bendix Corporation
    Inventor: Thomas E. Stack
  • Patent number: 4354240
    Abstract: The flight path transition control apparatus provides a roll attitude command to control the aircraft to execute an exponential transition path to a predetermined course in accordance with the exponential control law Y+KY where Y is the lateral displacement of the aircraft from the predetermined course, Y is the rate of change of the lateral displacement and K is a time constant of the system. A predictive roll command .phi..sub.p is generated in accordance with ##EQU1## where V.sub.g is the aircraft ground speed,TAE is the track angle error of the aircraft with respect to the predetermined course,TAE.sub.0 is the track angle error of the aircraft with respect to the predetermined course at capture maneuver initiation,g is the gravitational constant, andt is the elapsed time following capture initiation.The predictive roll command .phi..sub.p is combined with the exponential control law to provide the aircraft roll attitude command .phi..sub.c =.phi..sub.
    Type: Grant
    Filed: March 24, 1980
    Date of Patent: October 12, 1982
    Assignee: Sperry Corporation
    Inventor: Edmond E. Olive
  • Patent number: 4098215
    Abstract: An improved steering control system is provided for improving the handling qualities of hydrofoil craft during takeoff. In steering control systems for hydrofoils, the craft is banked by operation of control surfaces and the rudder is turned in the corresponding direction to coordinate the turn. To improve the handling qualities and maneuverability during the period of acceleration from hull-borne to foil-borne operation, the steering control system is modified during this period by decreasing the gain of the control loop for the control surfaces and by increasing the gain of the control loop for the rudder. A lag filter is also introduced into both loops.
    Type: Grant
    Filed: July 21, 1977
    Date of Patent: July 4, 1978
    Assignee: The Boeing Company
    Inventor: Thomas A. Owan
  • Patent number: 4094479
    Abstract: A yaw axis stability and command augmentation system (SCAS) particularly applicable to STOL type aircraft includes three primary control terms proportional to side slip angle, side slip angle rate and rudder pedal force, wherein side slip angle rate is synthesized from measures of yaw rate, bank angle and lateral acceleration. These primary system feedback terms are supplied to the rudder electro-hydraulic secondary actuator which is positioned in accordance with their sum. The system serves to provide improved automatic damping of the Dutch roll modes, to suppress aircraft motion transients in yaw and roll under engine failure situations, to provide automatic turn-coordination in maneuvering flight, and to provide a side slip angle command capability to improve manual control precision in approach and landing under crosswind and lateral wind shear conditions.
    Type: Grant
    Filed: March 25, 1977
    Date of Patent: June 13, 1978
    Assignee: Sperry Rand Corporation
    Inventor: Thomas W. Kennedy, Jr.