By Change In Bank Patents (Class 244/179)
  • Patent number: 9764852
    Abstract: Methods and systems are provided for displaying information on a display device of an aircraft. The method comprises receiving aircraft data from one or more aircraft components; displaying on a user interface the aircraft data and at least one interactive display element associated with an autopilot control function; receiving user input based on an interaction with the at least one interactive display element; and selectively changing an appearance of the at least one interactive display element based on the user input.
    Type: Grant
    Filed: March 13, 2015
    Date of Patent: September 19, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Babitha Jajur, Mohan Gowda Chandrashekarappa, Kiran Mancheiah Venkataramana, Deepthi Sethuraman, Sridevi Nagaraja
  • Patent number: 9360868
    Abstract: A hand-held radio transmit controller for remotely controlling an aircraft, and a method for controlling a remote control aircraft offering ground vehicle-like control.
    Type: Grant
    Filed: October 28, 2014
    Date of Patent: June 7, 2016
    Assignee: TRAXXAS LP
    Inventors: Wesley Ronald Erhart, Scott Rollin Michael Schmitz, Tom Kawamura, Richard Douglas Hohnholt, Kent Poteet
  • Patent number: 9268336
    Abstract: A hand-held radio transmit controller for remotely controlling an aircraft, and a method for controlling a remote control aircraft offering ground vehicle-like control.
    Type: Grant
    Filed: August 28, 2015
    Date of Patent: February 23, 2016
    Assignee: TRAXXAS LP
    Inventors: Wesley Ronald Erhart, Scott Rollin Michael Schmitz, Thomas Michael Kawamura, Richard Douglas Hohnholt, Kent Poteet
  • Patent number: 9058040
    Abstract: A method, apparatus, and computer program product are present for operating an aircraft. Responsive to a command to hold an altitude of the aircraft, an adjustment to a pitch angle of the aircraft needed to substantially maintain the altitude of the aircraft is identified using a lift for the aircraft to form an identified adjustment to the pitch angle to reduce altitude deviations from at least one of a change in configuration of a number of flight surfaces and changes in wind. The pitch angle of the aircraft is adjusted using the identified adjustment during flight.
    Type: Grant
    Filed: February 27, 2009
    Date of Patent: June 16, 2015
    Assignee: THE BOEING COMPANY
    Inventor: Frederick Charles Henry Blechen
  • Patent number: 8989925
    Abstract: An improved Horizontal Situation Indicator (HSI) module for use with an aircraft, wherein the HSI module is adapted for accepting Bank Angle Commands or waypoint data from the GPS flight module and for using the same to determine a heading error. The HSI module is further adapted for outputting the heading error to the Flight Director module where it can be used to create a Roll Command for output to the Auto-Pilot, whereby the Auto-Pilot can be commanded to follow a turn using the HSI and the Flight Director without requiring an additional module be added to the aircraft to create the heading error for use by the Flight Director. The waypoint data can be of the “flyover” type or the “flyby” type.
    Type: Grant
    Filed: March 12, 2013
    Date of Patent: March 24, 2015
    Assignee: L-3 Communications Corporation
    Inventor: James Eugene Strickling
  • Patent number: 8874286
    Abstract: An alternative system for damping the dutch roll mode in an aircraft is provided using roll control surfaces. Classical yaw dampers for the dutch roll mode utilize the yaw control surfaces such as a rudder to dampen the dutch roll mode oscillations. An alternative damper is described that utilizes roll control surfaces such as spoilers or ailerons to dampen the dutch roll mode.
    Type: Grant
    Filed: November 20, 2013
    Date of Patent: October 28, 2014
    Assignee: Textron Innovations, Inc.
    Inventors: Steven G. Hagerott, Steven Klausmeyer, Gonzalo E. Mendoza
  • Patent number: 7693619
    Abstract: A control system of a spacecraft for controlling two or more sets of collinear control moment gyroscopes (CMGs) comprises an attitude control system. The attitude control system is configured to receive a command to adjust an orientation of the spacecraft, determine an offset for a momentum disk for each of the two or more sets of CMGs that maximizes torque, determine a momentum needed from the two or more sets of CMGs to adjust the orientation of the spacecraft, and calculate a total torque needed by taking the derivative of the momentum. The control system further comprises a momentum actuator control processor coupled to the attitude control system, the momentum actuator control processor configured to calculate a required gimbal movement for each of the CMGs in each of the two or more sets of collinear CMGs from total torque.
    Type: Grant
    Filed: November 30, 2005
    Date of Patent: April 6, 2010
    Assignee: Honeywell International Inc.
    Inventors: Michael R. Elgersma, Daniel P. Johnson, Mason A. Peck, Brian K. Underhill, Gunter Stein, Blaise G. Morton, Brian J. Hamilton
  • Patent number: 6169496
    Abstract: A flight warning system comprises an outside temperature probe for sensing outside temperature, a gyroscope for sensing aircraft bank angle, a static transducer for sensing static pressure, and a dynamic pressure sensor for receiving total pressure from a pitot tube. A computer is responsive to the gyroscope, static transducer, outside temperature probe and dynamic pressure sensor calculates whether the aircraft is entering a stall condition by comparing the aircraft's bank angle with the stall bank angle. The computer can also calculate whether sufficient altitude exists for the aircraft to safely return to a field after a power failure. An output device can also be provided for indicating the existence of said sufficient altitude, and a stall indicator can be provided for indicating whether the aircraft is entering a stall condition. A method for determining the existence of a stall condition with the aircraft is also disclosed.
    Type: Grant
    Filed: December 9, 1998
    Date of Patent: January 2, 2001
    Assignee: Exigent International, Inc.
    Inventors: Mack L. Martin, Mark G. Baciak, Louis W. Seiler
  • Patent number: 6073065
    Abstract: A method for detecting a bank angle experienced by a motor vehicle (10) is disclosed. Three estimates of the vehicle bank angle, .gamma..sub.a, .gamma..omega. and .gamma..sub..nu. are determined from separate data and are then used to determine an estimate of the bank angle BIAS. The bank angle BIAS is then combined with one of the three bank angle estimates to determine a final bank angle estimate, .gamma..sub.final, to be used to modify the vehicle's yaw control calculations in accordance therewith.
    Type: Grant
    Filed: September 4, 1998
    Date of Patent: June 6, 2000
    Assignee: Ford Global Technologies, Inc.
    Inventors: Todd Allen Brown, Hongtei Eric Tseng
  • Patent number: 5222691
    Abstract: A helicopter flight control system includes an automatic turn coordination system which provides a coordinating yaw command signal to the tail rotor of the helicopter. The system stores on command a trim attitude (e.g., signals indicative of bank angle, lateral ground speed, and lateral acceleration) about which automatic turn coordination is provided, thus providing the pilot with automatic turn coordination about attitudes other than wings level.
    Type: Grant
    Filed: August 28, 1991
    Date of Patent: June 29, 1993
    Assignee: United Technologies Corporation
    Inventors: Phillip J. Gold, Nicholas D. Lappos, Don L. Adams, Stuart C. Wright
  • 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: 5170969
    Abstract: An aircraft rudder command system for allowing a pilot to directly input a sideslip command for yaw-axis control through use of the rudder pedals is disclosed. The aircraft rudder command system includes a pedal input device for receiving a pedal input signal indicative of pilot rudder pedal input, a signal-receiving device for receiving feedback signals indicative of the current state of aircraft operation, a command generator system responsive to the pedal input signal and at least one of the feedback signals for generating a sideslip angle command, command limiting means for generating a limited sideslip angle command, and a feedback control system for transmitting a sideslip control rudder command to a rudder actuation system. The rudder actuation system causes the rudder to move in such a manner so as to produce an actual aircraft sideslip angle which follows the limited sideslip angle command. The aircraft rudder command system may also include a sideslip estimator.
    Type: Grant
    Filed: November 23, 1988
    Date of Patent: December 15, 1992
    Assignee: The Boeing Company
    Inventor: Ching-Fang Lin
  • Patent number: 5096146
    Abstract: A controller for generating a bank angle limit for an aircraft during takeoff with an nonoperational engine. The controller operates so that there are minimum and maximum bank angle limits. Between these minimum and maximums, there is a linear relationship between aircraft airspeed and bank angle limit. However, before there is a change in aircraft airspeed from an increasing mode to a decreasing mode or vice versa, the bank angle limit remains constant until the change in aircraft airspeed is greater than or equal to a predetermined airspeed differential.
    Type: Grant
    Filed: August 17, 1990
    Date of Patent: March 17, 1992
    Assignee: The Boeing Company
    Inventors: Munir Orgun, Dung D. Nguyen
  • Patent number: 5095746
    Abstract: An aircraft banking angle indicator which includes a banking angle sensing arrangement for generating an actual banking angle signal, a maximum banking angle input device for manually entering a selected maximum banking angle, a signal processing arrangement having respective inputs connected to the banking angle sensing arrangement and to the maximum banking angle input devices for generating an excessive banking output signal indicative of a banking angle exceeding the maximum banking angle, and an indicating arrangement having a signal input connected to the banking angle output signal for indicating the excessive banking angle.
    Type: Grant
    Filed: January 29, 1991
    Date of Patent: March 17, 1992
    Inventor: John W. Stanis
  • Patent number: 5050086
    Abstract: An aircraft's horizontal flight path and sideslip angle is controlled in a system having a roll control loop and a yaw control loop. An incremental aileron position command signal is generated in the roll control loop as a function of the sum of a yaw rate error and a sideslip error. An incremental rudder position command signal is generated in the yaw control loop as the function of the difference between these errors. The yaw rate error is determined as a function of a heading error. The manner in which the heading error is computed varies with the control mode in which the system is operating. In the simplest heading mode, the heading error is the difference between a heading command a sensed heading of the aircraft. In the inner loop of the roll control channel, a roll attitude command signal is generated as a function of heading error plus sideslip error. In the inner loop of the yaw control channel, a yaw rate command signal is generated as a function of heading error minus sideslip error.
    Type: Grant
    Filed: April 30, 1990
    Date of Patent: September 17, 1991
    Assignee: The Boeing Company
    Inventor: Antonius A. Lambregts
  • Patent number: 5023796
    Abstract: A flight path control apparatus for controlling an aircraft to execute a capture maneuver of a predetermined heading or track and provide a roll correction signal for controlling the path of said aircraft along an exponential transition curve. The corrective heading or track signal .DELTA..psi. is generated in accordance with ##EQU1## where .DELTA..psi. is the magnitude of the corrective heading or track command signal,g is a constant corresponding to the acceleration of gravity,V.sub.t is the true airspeed of the aircraft,.tau. is a predetermined constant of aircraft roll rate,.phi..sub.i is the roll angle of the aircraft at the initiation of the capture maneuver,.phi..sub.i is the time rate of change of the roll angle of the aircraft at initiation of the capture maneuver, and.phi..sub.M is a predetermined maximum time rate of change of roll rate of the aircraft during the capture maneuver.
    Type: Grant
    Filed: October 3, 1989
    Date of Patent: June 11, 1991
    Assignee: Honeywell, Inc.
    Inventor: Jeffrey A. Kahler
  • Patent number: 4964598
    Abstract: A remotely-controlled aircraft comprises a sensor for sensing the actual rate-of-turn of the aircraft and for generating a rate-of-turn signal proportional thereto, which signal, inherently also proportional to the actual bank-angle of the aircraft, is applied to the aileron drive as a negative feedback signal with the bank-angle command signal to thereby stabilize the bank-angle of the aircraft. The aircraft includes a further sensor for sensing the actual rate-of-climb of the aircraft and for generating a rate-of-climb signal proportional thereto, which latter signal, inherently also proportional to the actual pitch-angle of the aircfaft, is applied to the elevator drive as a negative feedback signal with the pitch-angle command signal to thereby stabilize the pitch-angle of the aircraft.
    Type: Grant
    Filed: December 19, 1988
    Date of Patent: October 23, 1990
    Assignee: B.T.A. Automatic Piloting Systems Ltd.
    Inventors: Zacharia Berejik, Allon Wallach
  • Patent number: 4553210
    Abstract: A system and technique is disclosed which provides a complemented roll attitude signal for use in the control system of an aircraft. The complemented roll attitude is produced by combining a yaw rate and true airspeed signal with a conventional roll attitude signal to produce a complemented signal which may be combined with a roll command signal to produce a roll steering signal for controlling aircraft response under non-zero roll attitude conditions of aircraft flight. The complemented roll attitude signal provides improved response to aircraft roll commands under non-zero roll attitude conditions, particularly in helicopter systems.
    Type: Grant
    Filed: August 17, 1982
    Date of Patent: November 12, 1985
    Assignee: Rockwell International Corporation
    Inventor: John P. Centala
  • Patent number: 4490668
    Abstract: A space-oriented apparatus for converting solar energy to microwave energy. The microwave energy is used to generate an RF beam for propagation to the earth. The apparatus is formed into an extended planar sandwich-like structure carrying solar cells on one surface facing the sun and microwave devices on the other face for generating the RF beam. The microwave devices are energized by the solar cells, and function to generate the RF energy. The apparatus is useful for converting solar energy to microwave power, and to operate communication satellites and satellites having radar functions.
    Type: Grant
    Filed: July 12, 1979
    Date of Patent: December 25, 1984
    Assignee: RCA Corporation
    Inventor: Fred Sterzer
  • Patent number: 4371939
    Abstract: The engagement (83) of a flight director (82) that provides automatic steering by roll angle of an aircraft which includes an automatic yaw trim system (FIG. 2) that will automatically coordinate turns induced by the flight director establishes (155, 157, 138) a heading hold disengagement mode which is maintained even if the flight director becomes disengaged (160) until the aircraft roll attitude is indicated as being nearly level (163). Exemplary roll channel (FIG. 1) and yaw channel (FIG. 2 ) of an automatic flight control system which may incorporate the invention are disclosed.
    Type: Grant
    Filed: March 30, 1981
    Date of Patent: February 1, 1983
    Assignee: United Technologies Corporation
    Inventors: Don L. Adams, William C. Fischer, Stuart C. Wright, David J. Verzella
  • Patent number: 4330829
    Abstract: Oscillations in helicopter attitude sustained by the aerodynamic response of the helicopter to an automatic flight control system which is responsive to an attitude sensor, are eliminated by band reject (notch) filtering of a control system stability command to the aircraft, derived from rate of changes of such attitude at a frequency related to the aircraft attitude oscillations induced by the rate-controlled stability compensation.
    Type: Grant
    Filed: July 7, 1980
    Date of Patent: May 18, 1982
    Assignee: United Technologies Corporation
    Inventors: William C. Fischer, Don L. Adams
  • Patent number: 4312039
    Abstract: An aircraft automatic yaw stabilization system with heading hold and manual command override capability provides circuit means responsive to the manual commands for suppressing heading transients in commmanding a heading change and in the ultimate capture of a desired heading.
    Type: Grant
    Filed: January 24, 1980
    Date of Patent: January 19, 1982
    Assignee: Sperry Corporation
    Inventor: Edmund R. Skutecki
  • Patent number: 4127245
    Abstract: The longitudinal cyclic pitch channel of a helicopter has a negative pitch rate feedback bias added thereto when flying at higher speeds, thereby to stabilize the pitch axis against aft-load maneuvering instability and/or to induce a requirement for the pilot to provide a countermanding longitudinal cyclic pitch input through his cyclic pitch stick, the normal feed force of which provides an indication to him of the loading of the rotor as a consequence of undergoing pitch rate maneuvers.
    Type: Grant
    Filed: April 27, 1977
    Date of Patent: November 28, 1978
    Assignee: United Technologies Corporation
    Inventors: Franklin A. Tefft, Don L. Adams, Lou S. Cotton
  • 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.
  • Patent number: 4046341
    Abstract: The instant invention relates to a system for estimating aircraft angle of attack .alpha. and sideslip angle .beta. from measured quantities such as angular body rate and linear acceleration. The estimated angle of attack and sideslip signals are generated by means of a Kalman filter configuration which simulates a model of the aircraft angle of attack and sideslip angle dynamics, and may be used either in an aircraft flight control network or for display purposes.
    Type: Grant
    Filed: March 30, 1976
    Date of Patent: September 6, 1977
    Assignee: General Electric Company
    Inventor: Richard Paul Quinlivan
  • Patent number: 3958522
    Abstract: A control system for hydrofoil craft is one in which control surfaces are moved automatically in response to signals derived from the motion of the craft to stabilize and control the craft. In such systems, a potentially dangerous condition can occur in case of a failure or malfunction in the roll control system. In order to prevent such conditions, two roll sensing devices are provided which normally generate identical signals to actuate the control surfaces to stabilize the rolling motion. In case a failure or malfunction, the signals provided by the two sensing devices become different and apparatus is provided to compare these signals and to respond to a difference in the signals to initiate landing of the craft rapidly and safely.
    Type: Grant
    Filed: March 16, 1973
    Date of Patent: May 25, 1976
    Assignee: The Boeing Company
    Inventors: Arlyn Orlando Harang, John Hunt Scott, Irving Alfred Hirsch