Override Of Automatic Control By Human Pilot Patents (Class 244/196)
  • Patent number: 8910909
    Abstract: A helicopter includes a rotor system having a rotor with an adjustable pitch that is controlled at least in part by a pilot using a collective control and which helicopter generates a Low RPM signal that is indicative of a threshold low rotational speed of the rotor. An actuator arrangement can move the collective control by exerting a force on the collective control such that the pilot is able to overcome the actuator force but which otherwise can move the collective control from a current operational position toward a minimum pitch position. A clutch can co-rotate with a motor to serve in transferring the actuation force to reduce the adjustable pitch and can slip relative to the actuator shaft assembly responsive to an application of a counterforce applied by the pilot to the collective control such that the counterforce overcomes the actuation force.
    Type: Grant
    Filed: January 23, 2014
    Date of Patent: December 16, 2014
    Assignee: Merlin Technology, Inc.
    Inventors: John E. Mercer, Mark H. Marvin
  • Patent number: 8907536
    Abstract: An actuator device for actuating equipment has an electric motor arranged to be connected to an autopilot device and connected by a drivetrain to an outlet shaft, itself designed to be connected to a control instrument, the drivetrain incorporating stepdown gearing dividing the drivetrain into a high-speed segment beside the motor and a low-speed segment beside the outlet shaft. The high-speed segment comprising a deactivator member for deactivating the autopilot device. The deactivator member having a first element secured to a first portion of the high-speed segment; a second element secured to a second portion of the high-speed segment and connected to the first element to allow the first element to be angularly offset relative to the second element when a torque for transmission reaches a predetermined threshold; and a detector member for detecting the angular offset.
    Type: Grant
    Filed: January 24, 2012
    Date of Patent: December 9, 2014
    Assignee: Sagem Defense Securite
    Inventor: Benoit Cremiere
  • Publication number: 20140332633
    Abstract: A helicopter includes a rotor system having a rotor with an adjustable pitch that is controlled at least in part by a pilot using a collective control and which helicopter generates a Low RPM signal that is indicative of a threshold low rotational speed of the rotor. An actuator arrangement can move the collective control by exerting a force on the collective control such that the pilot is able to overcome the actuator force but which otherwise can move the collective control from a current operational position toward a minimum pitch position. A clutch can co-rotate with a motor to serve in transferring the actuation force to reduce the adjustable pitch and can slip relative to the actuator shaft assembly responsive to an application of a counterforce applied by the pilot to the collective control such that the counterforce overcomes the actuation force.
    Type: Application
    Filed: January 23, 2014
    Publication date: November 13, 2014
    Applicant: Merlin Technology Inc.
    Inventors: John E. Mercer, Mark H. Marvin
  • Patent number: 8838299
    Abstract: The present invention relates to a method of decoupling the mode of automatic following of the lateral profile and the mode of automatic following of the vertical profile of an automatic guidance system of an aircraft (A) flying on a reference trajectory (T). The mode of automatic following of the vertical profile is not disengaged immediately on disengaging the mode of automatic following of the lateral profile. After disengaging the mode of automatic following of the lateral profile, the mode of automatic following of the vertical profile is disengaged automatically only if at least one criterion of lateral separation between the current or short-term position of the aircraft and the lateral profile corresponding to the reference trajectory is satisfied, having regard to the position error.
    Type: Grant
    Filed: December 4, 2008
    Date of Patent: September 16, 2014
    Assignee: Thales
    Inventors: Guy Deker, Manuel Gutierrez-Castaneda
  • Patent number: 8684314
    Abstract: For emergency piloting of a manual flight control system (7) of an aircraft (1), in the event of flexible connection means (26) breaking, an upstream control device (8) takes authority over the electronic control unit (29) of series actuator (21). An output pivoting quadrant (25) is subjected by a centering rod (22) to a blocking and centering action. In the event of the system breaking, the output pivoting quadrant (25) forms a bearing point for the series actuator (21), so that an emergency control actuate a airfoil surface (11).
    Type: Grant
    Filed: March 12, 2012
    Date of Patent: April 1, 2014
    Assignees: Airbus Helicopters, Airbus Helicopter Deutschland GmbH
    Inventors: Bruno Chaduc, Patrick Hellio, Bernard Gemmati, Karsten Krok
  • Patent number: 8651425
    Abstract: A helicopter includes a rotor system having a rotor with an adjustable pitch that is controlled at least in part by a pilot using a collective control and which helicopter generates a Low RPM signal that is indicative of a threshold low rotational speed of the rotor. An actuator arrangement can move the collective control by exerting a force on the collective control such that the pilot is able to overcome the actuator force but which otherwise can move the collective control from a current operational position toward a minimum pitch position. A clutch can co-rotate with a motor to serve in transferring the actuation force to reduce the adjustable pitch and can slip relative to the actuator shaft assembly responsive to an application of a counterforce applied by the pilot to the collective control such that the counterforce overcomes the actuation force.
    Type: Grant
    Filed: May 23, 2012
    Date of Patent: February 18, 2014
    Assignee: Merlin Technology Inc.
    Inventors: John E. Mercer, Mark H. Marvin
  • Patent number: 8594864
    Abstract: A torque based power limit cueing system is provided and includes an engine computer to compile data relating to torque and additional information of each of one or more engines, an active stick by which tactile cueing are provided to a pilot and by which the pilot inputs control commands, a multi-function display (MFD) by which visible cues are provided to the pilot and a flight control computer (FCC) operably coupled to the engine computer, the active stick and the multi-function display, the FCC being configured to receive the data from the engine computer and to output tactile cue commands and visible commands in accordance with the torque and the additional information of each of the one or more engines to the active stick and the MFD, respectively.
    Type: Grant
    Filed: August 24, 2011
    Date of Patent: November 26, 2013
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Aaron L. Greenfield, Alex Faynberg, Vineet Sahasrabudhe, John Rucci, Glen Knaust
  • Publication number: 20130075535
    Abstract: The rudder control system (1) comprises means (10) for determining a compensation order for an actuator (6) of the aircraft rudder (7).
    Type: Application
    Filed: September 14, 2012
    Publication date: March 28, 2013
    Applicant: AIRBUS OPERATIONS (SAS)
    Inventors: Patrice BROT, Pierre Fabre
  • Patent number: 8360369
    Abstract: A helicopter includes a rotor system having a rotor with an adjustable pitch that is controlled at least in part by a pilot using a collective control and which helicopter generates a Low RPM signal that is indicative of a threshold low rotational speed of the rotor. An actuator arrangement configured to move the collective control by exerting a force on the collective control such that the pilot is able to overcome the force but which otherwise moves the collective control from a current operational position toward a minimum pitch position. A control arrangement is configured for receiving the Low RPM signal and for responding to the Low RPM signal by activating the actuator arrangement for at least a predetermined period of time to apply the force to move the collective control from the current operational position to the minimum pitch position.
    Type: Grant
    Filed: November 23, 2010
    Date of Patent: January 29, 2013
    Assignee: Merlin Technology, Inc.
    Inventors: John E. Mercer, Mark H. Marvin
  • Publication number: 20120241563
    Abstract: For emergency piloting of a manual flight control system (7) of an aircraft (1), in the event of flexible connection means (26) breaking, an upstream control device (8) takes authority over the electronic control unit (29) of series actuator (21). An output pivoting quadrant (25) is subjected by a centering rod (22) to a blocking and centering action. In the event of the system breaking, the output pivoting quadrant (25) forms a bearing point for the series actuator (21), so that an emergency control actuate a airfoil surface (11).
    Type: Application
    Filed: March 12, 2012
    Publication date: September 27, 2012
    Applicants: EUROCOPTER DEUTSCHLAND GMBH, EUROCOPTER
    Inventors: Bruno Chaduc, Patrick Hellio, Bernard Gemmati, Karsten Krok
  • Patent number: 8235328
    Abstract: Embodiments of the invention relate to a flight control system for controlling an aircraft during flight. The flight control system may include a primary controller configured to receive an input from a pilot and to output a primary control signal and a primary transmission path connected to the primary controller and configured to relay the primary control signal. The flight control system may also include a backup controller configured to receive the input from the pilot and to output a backup control signal and a backup transmission path connected to the backup controller and configured to relay the backup control signal. Additionally, the flight control system may include an actuator having a remote electronics unit configured to receive the primary control signal and the backup control signal and to determine if the primary control signal is available and valid.
    Type: Grant
    Filed: June 23, 2011
    Date of Patent: August 7, 2012
    Assignee: Gulfstream Aerospace Corporation
    Inventor: Jukka Matti Hirvonen
  • Patent number: 8200379
    Abstract: This invention relates to an intelligence system on board an aircraft that detects an emergency, assesses the situation, and then acts on the situation in a pre-determined manner.
    Type: Grant
    Filed: February 10, 2009
    Date of Patent: June 12, 2012
    Inventors: Dario P. Manfredi, Robert La France
  • Patent number: 8121747
    Abstract: Embodiments of a process and a program product are provided suitable for implantation by a flight management system (FMS), which is deployed onboard an aircraft and including a display device and a user interface. The FMS operable in a plurality of non-precision approach modes. In one embodiment, the process includes the steps of: (i) receiving data via the user interface designating an approach in a flight plan; (ii) enabling the pilot to utilize the user interface to select a non-precision approach mode from the plurality of non-precision approach modes if the designated approach is a non-precision approach; and (iii) placing the FMS in the selected non-precision approach mode during the designated approach.
    Type: Grant
    Filed: August 5, 2009
    Date of Patent: February 21, 2012
    Assignee: Honeywell International Inc.
    Inventors: Dennis David Loots, Erwan Paricaud, Yannick Thebault
  • Patent number: 7984878
    Abstract: Embodiments of the invention relate to a flight control system for controlling an aircraft during flight. The flight control system may include a primary controller configured to receive an input from a pilot and to output a primary control signal and a primary transmission path connected to the primary controller and configured to relay the primary control signal. The flight control system may also include a backup controller configured to receive the input from the pilot and to output a backup control signal and a backup transmission path connected to the backup controller and configured to relay the backup control signal. Additionally, the flight control system may include an actuator having a remote electronics unit configured to receive the primary control signal and the backup control signal and to determine if the primary control signal is available and valid.
    Type: Grant
    Filed: January 17, 2007
    Date of Patent: July 26, 2011
    Assignee: Gulfstream Aerospace Corporation
    Inventor: Jukka Matti Hirvonen
  • Publication number: 20100258678
    Abstract: A stall protection system for use with an aircraft may have at least one sensor configured to provide an indication of a pressure differential associated with airflow across an airfoil, and a controller in communication with the at least one sensor. The controller may be configured to compare the pressure differential to a pressure differential threshold associated with a stall condition of the airfoil, and to selectively generate a recovery response signal based on the comparison.
    Type: Application
    Filed: June 19, 2009
    Publication date: October 14, 2010
    Inventor: NICHOLAS JONATHAN FERMOR
  • Patent number: 6859689
    Abstract: A method and apparatus are provided for controlling a dynamic device having multi-inputs and operating in an environment having multiple operating parameters. A method of designing flight control laws using multi-input, multi-output feedback LTI'zation is also provided. The method includes steps of: (i) determining coordinates for flight vehicle equations of motion; (ii) transforming the coordinates for the flight vehicle equations of motion into a multi-input linear time invariant system; (iii) establishing control laws yielding the transformed equations of motion LTI; (iv) adjusting the control laws to obtain a desired closed loop behavior for the controlled system; and (v) converting the transformed coordinates control laws to physical coordinates.
    Type: Grant
    Filed: January 27, 2003
    Date of Patent: February 22, 2005
    Assignee: Athena Technologies, Inc.
    Inventor: David W. Vos
  • Patent number: 6691956
    Abstract: An airplane security system, particularly for a commercial airliner, includes an on-board device for allowing a person not on-board the airplane to override an on-board piloting system for the airplane. This on-board device is used together with an off-board device for allowing the person not on-board the airplane to contact the on-board device for overriding the on-board piloting system. The person off-board the airplane can then utilize a device for directing a flight path for the airplane that would differ from the flight path originally intended by those on-board and piloting the airplane, including providing for the safe landing of the airplane.
    Type: Grant
    Filed: July 3, 2002
    Date of Patent: February 17, 2004
    Inventor: Serville A. Waterman
  • Patent number: 6561463
    Abstract: A flight control module with integrated actuator spoiler control electronics, where the flight control functions have been integrated into the integrated modular avionics through the use of a flight control module (“FCM”), the FCM being configured to contain spoiler actuator control electronics (“ACE”). The spoiler ACE is used to control the roll functions of the spoiler. The spoiler ACE is configured to be separate from the FCM, even though it is located within the same modules and receives its power independent of the power supply for the FCM. In the event of a failure of the primary flight control surfaces of an airplane, the spoilers can be used to control the roll of the aircraft because the spoiler ACE is independent of the ACE used to control the primary flight control surfaces. The spoiler ACE can also be used in the event of a failure of the FCM because the spoiler ACE is independent of the FCM.
    Type: Grant
    Filed: July 14, 2000
    Date of Patent: May 13, 2003
    Assignee: Honeywell International Inc.
    Inventors: Larry Yount, John Todd
  • Patent number: 6527225
    Abstract: A method for automating a takeoff maneuver for an aircraft, comprising the steps of generating a takeoff profile comprising a takeoff point, a flight path, and a takeoff decision point (TDP), engaging an automated takeoff system to access the takeoff profile, receiving periodic position data of the aircraft, comparing the position data to the takeoff profile to compute a plurality of deviations each time the position data is received, outputting the plurality of deviations to a display, converting the plurality of deviations into a plurality of control commands, and maneuvering the aircraft in response to the control commands along the flight path.
    Type: Grant
    Filed: April 30, 2002
    Date of Patent: March 4, 2003
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Stephen H. Silder, Jr., Charles W. Evans, Christopher A. Thornberg
  • Patent number: 6460810
    Abstract: A device for programming industry standard autopilots by unskilled pilots. The effect of the invention is such that when the invention is employed in a flying body comprising an industry standard autopilot with a digital flight control system, the invention provides for the safe operation of any aircraft by an unskilled pilot. The device additionally affords skilled pilots a more rapid and simplified means of programming autopilots while in flight thus reducing a skilled pilot's cockpit workload for all aircraft flight and directional steering, way points, and aircraft flight functions reducing the possibility of pilot error so as to effect safer flight operations of an aircraft by affording a skilled pilot to direct aircraft steering and function while under continuous autopilot control.
    Type: Grant
    Filed: January 22, 2001
    Date of Patent: October 8, 2002
    Inventor: Terry Jack James
  • Patent number: 6443399
    Abstract: In an aircraft using fly-by-wire technology, the flight control functions have been integrated into the integrated modular avionics (“IMA”). The new flight control module (“FCM”) resides on the same data bus as the other modules in the IMA and receives power from the same power supply. In addition, the FCM is also connected to a separate power supply to add redundancy to the system. Several benefits arise from this configuration of an FCM. There is no longer a separate chassis needed for the flight control functions, thus resulting in a reduction in weight. In addition, the FCM now has access to all of the data on the IMA bus, instead of a limited amount of data over an ARINC 629 bus. The FCM provides augmentation signals to the actuator control electronics (“ACE”) to aid in the flying of the aircraft. In the event of a failure of the FCM, the ACE still provides enough control to fly the airplane.
    Type: Grant
    Filed: July 14, 2000
    Date of Patent: September 3, 2002
    Assignee: Honeywell International Inc.
    Inventors: Larry Yount, John Todd
  • Patent number: 6366837
    Abstract: A method augmenting a pilot's command lane signal by transmitting the pilot's input command to a first summer and the surface actuator control circuitry. The first summer output signal is transmitted to a second summer circuit to add (or subtract) the first summer output signal with a flight control signal resulting in a second summer output signal. The second summer output signal is transmitted to the first summer to add, subtract or otherwise modify the second summer output signal with the pilot command input signal. Thus, the pilot command input signal is augmented or coupled with the second summer output signal to provide better control of the aircraft while not allowing the flight control computer/avionics control electronic circuitry to directly augment the pilot command input signal.
    Type: Grant
    Filed: July 14, 2000
    Date of Patent: April 2, 2002
    Assignee: Honeywell International Inc.
    Inventors: Larry Yount, John Todd
  • Patent number: 6021980
    Abstract: A stabilization system is disclosed in which stabilization pitch and roll signals effective for stabilizing the aircraft are combined with respective pilot provided elevator and aileron position demand signals in accordance with a function which reduces the effects of the stabilizing signals in dependence on increasing values of the respective elevator and aileron position demand signals.
    Type: Grant
    Filed: October 28, 1996
    Date of Patent: February 8, 2000
    Inventors: Elliot Wright, Igor E. Tsibizov
  • Patent number: 5806806
    Abstract: A robust mechanical reversion system which provides the ability to fly and land in the absence of any fly-by-wire controls and which is transparent to the pilot during normal operation. The described invention provides a mechanism which includes redundant linear variable differential transmitters (LVDT) which generates a transmitted signal in proportion to the displacement of the control apparatus in the cockpit. The signal is fed to the flight control computer which determines the magnitude of the change represented by the signal and in turn, commands both the control surface servo actuators as well as an electrical mechanical servo actuator (EMA) located in close proximity to the flight compartment and coupled to the mechanical system to move in proportion to the change.
    Type: Grant
    Filed: March 4, 1996
    Date of Patent: September 15, 1998
    Assignee: McDonnell Douglas Corporation
    Inventors: Wilfred E. Boehringer, Teunes Verhoeven
  • Patent number: 5738310
    Abstract: A rudder bar system for a helicopter controlled in yaw by acting on the tail rotor or an equivalent device has a capability, as a function of the parameters representative of the current flight status of the helicopter, of either automatically continuously recentering the forces on the rudder bar, which cancels out the residual static forces and gives the pilot a tactile sensation close to that given by a friction-type rudder bar, or allowing the pilot fully to feel the countering action of an elastic return device such as a spring.
    Type: Grant
    Filed: December 22, 1995
    Date of Patent: April 14, 1998
    Assignee: Eurocopter France
    Inventors: Philippe Alain Jean Rollet, Jacques Serge Louis Bellera
  • Patent number: 5445346
    Abstract: Spoilers on the forward top and bottom elevator tail surface of large aircraft offer an independent backup for pitch control. The placement of spoilers in a line along the forward portion of an aircraft pitch-control structure offers direct upward or downward "lift" from a spoiler-induced unbalance of Bernoulli forces on a near-symmetrical airfoil. Combined with a temporary bypass valve and channels between the "up" and "down" hydraulic actuators, a spoiler's forward-mounted torsion force on the elevator surfaces can also rotate the elevators in a controlled fashion. Preparation for hi-risk aircraft missions would install gate-spoiler surfaces into spoiler-actuating subsystems as a temporary safety-of-flight hedge against the loss of hydraulic elevator control.
    Type: Grant
    Filed: August 26, 1992
    Date of Patent: August 29, 1995
    Inventor: Raymond D. Gilbert
  • Patent number: 5255880
    Abstract: An improved fly by wire or fly by light system which provides for a smooth manual override of the autopilot function by allowing the pilot to modify the autopilot command to the control surfaces by physically manipulating the yoke to a position different than that commanded by the autopilot.
    Type: Grant
    Filed: July 13, 1992
    Date of Patent: October 26, 1993
    Assignee: Rockwell International Corporation
    Inventors: Woon Lyloc, David C. Pattison
  • Patent number: 5170163
    Abstract: An aircraft performance monitor 1 receives signals representative of the height h, rate of change of height h and vertical acceleration .theta. of the aircraft. The monitor 1 determines when (h-A(.sub.n.sbsb.1.sup.n.sbsp.2 +K.sub.1 h+K.sub.2 .theta. goes beyond a predetermined limit and generates a warning signal and disables the autopilot. The signal representative of vertical acceleration may be derived from the rate of change of pitch attitude of the aircraft, from the elevator angle or from an accelerometer.
    Type: Grant
    Filed: February 8, 1991
    Date of Patent: December 8, 1992
    Assignee: Smiths Industries Public Limited Company
    Inventors: Philip H. Collins, Robin D. T. Mosedale
  • Patent number: 5031562
    Abstract: A combined manual and automatic steering for a watercraft wherein there is provided an automatic steering control and a manual steering control that is operative to override the automatic control upon manual operator actuation.
    Type: Grant
    Filed: December 4, 1987
    Date of Patent: July 16, 1991
    Assignee: Sanshin Kogyo Kabushiki Kaisha
    Inventors: Ryoichi Nakase, Masayoshi Nanami
  • Patent number: 5012423
    Abstract: A device and method of back-up fly by wire control, especially useful in fly by wire systems when a failure mode is encountered. The problem of back-up system controllability with the type of compliant sidestick which has minimal displacement and returns to zero upon release of the control force is solved by reducing the authority of the sidestick to a fraction of full authority actuator position capability, to provide good control sensitivity. Full authority actuator position control is provided by automatically activating a trim integrator when the sidestick reaches its displacement stops.
    Type: Grant
    Filed: April 17, 1989
    Date of Patent: April 30, 1991
    Assignee: McDonnell Douglas Corporation
    Inventor: Stephen S. Osder
  • Patent number: 4964599
    Abstract: System for controlling roll and yaw of an aircraft. The system includes a device capable of elaborating, from electric signals respectively representative of the position of a first voluntary actuation member, the rolling speed, the attitude, the yaw speed, the sideslip and of the position of a second voluntary actuation member, a single electrical order for roll control formed by a linear combination of the electric signals. There is a device capable of elaborating, from the same electric signals, an electrical order for yaw control formed by a linear combination of the electric signals. There is also a device which makes it possible to combine the electrical order for yaw control and a mechanical order coming directly from the second voluntary actuation member.
    Type: Grant
    Filed: January 9, 1989
    Date of Patent: October 23, 1990
    Assignee: Aerospatiale Societe Nationale Industrielle
    Inventor: Jacques Farineau
  • Patent number: 4527242
    Abstract: Automatic flight control apparatus, preferably for use in a helicopter, comprises a parallel connected servosystem which allows the apparatus to discern manual input forces and to respond naturally to them. The manual forces are sensed internal the parallel servosystem by monitoring the corrective error drive signal to the parallel servomotor. A signal indicative of excess manual force is used to develop other signals, one of which aids in temporarily defeating the command signal generated by the autopilot in trying to do its job, and another of which temporarily contributes positive feedback within the parallel servosystem so as to cause the servomotor to aid the pilot's manual input force. Another preferred embodiment includes a series connected servosystem.
    Type: Grant
    Filed: June 28, 1982
    Date of Patent: July 2, 1985
    Assignee: Rockwell International Corporation
    Inventors: Kenneth W. McElreath, Gordon R. Fabian
  • Patent number: 4373184
    Abstract: Disclosed is a vertical flight path angle steering system for aircraft, utilizing a digital flight control computer which processes pilot control inputs and aircraft response parameters into suitable elevator commands and control information for display to the pilot on a cathode ray tube. The system yields desirable airplane control handling qualities and responses as well as improvements in pilot workload and safety during airplane operation in the terminal area and under windshear conditions.
    Type: Grant
    Filed: December 26, 1979
    Date of Patent: February 8, 1983
    Assignee: The Boeing Company
    Inventor: Antonius A. Lambregts
  • Patent number: 4236685
    Abstract: The present steering mechanism, especially for an aircraft includes a manly operable steering member and an automatic steering system. A difference signal formed from a pilot input and trim signal and from a gyro feedback signal is supplied to a force control and damping circuit twice, once directly and once through an authority limit circuit. The output of the authority limit circuit is also supplied to the motors forming part of the automatic steering system. The force control and damping circuit also receives further input signal or signals representing steering information. The output of the force control and damping circuit is connected to the feel unit of the steering system, whereby an immediate manual control by the pilot is effective, however limited against an excessive control or so-called manual over control.
    Type: Grant
    Filed: February 21, 1979
    Date of Patent: December 2, 1980
    Assignee: Messerschmitt-Boelkow-Blohm Gesellschaft mit beschraenkter Haftung
    Inventor: Gerhard K. Kissel
  • Patent number: 4206891
    Abstract: The yaw channel of a helicopter, which includes a yaw servo having a yaw trim valve operable to automatically hold heading, and at cruise speeds alternatively operable to provide controlled yaw for coordinated turns, which is normally disengaged by switches located on the pedals, is selectively allowed to remain engaged at cruise speeds so that if the pilot induces commands in yaw by means of the pedals, the pedal linkage must be forced against the position of the trim piston established by the heading hold or coordinated turn input commands to the yaw trim valve, thereby giving the pilot pedal force feel as a consequence of the resilient connection to the trim piston, which provides an indication to the pilot of the amount of side slip he is creating, thereby to avoid destructive overloading of the tail rotor.
    Type: Grant
    Filed: October 26, 1978
    Date of Patent: June 10, 1980
    Assignee: United Technologies Corporation
    Inventors: Ricardo L. Perez, Ronald E. Barnum, Franklin A. Tefft
  • Patent number: 4168045
    Abstract: 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.
    Type: Grant
    Filed: February 28, 1978
    Date of Patent: September 18, 1979
    Assignee: United Technologies Corporation
    Inventors: Gregory P. Wright, Don L. Adams
  • Patent number: 4109886
    Abstract: A flight control system utilizing a limited authority stability augmentation system having a long term attitude and/or path control input to enhance the automatic flight capability of the stability augmentation system. A position sensor coupled with the limited authority stability augmentation actuator provides an indication to the human pilot via a suitable indicator when the actuator is near or at the limit of its authority thereby permitting the human pilot to effect manual trim, thus recentering the actuator.
    Type: Grant
    Filed: January 12, 1976
    Date of Patent: August 29, 1978
    Assignee: Sperry Rand Corporation
    Inventors: Everett R. Tribken, Ronald J. Miller, Carl D. Griffith
  • Patent number: 4003532
    Abstract: The automatic heading retention mode of operation of an automatic flight control system for a rotary wing aircraft is discontinued and reestablished through the use of a logic circuitry responsive to the yaw rate, bank angle and airspeed of the aircraft and to the force applied to the cyclic pitch control member by the pilot. The logic circuitry provides for the isolation of information commensurate with left and right turns and summation of the yaw rate and bank angle in each direction to determine if automatic disengagement of the heading hold is warranted.
    Type: Grant
    Filed: March 15, 1976
    Date of Patent: January 18, 1977
    Assignee: United Technologies Corporation
    Inventors: Don L. Adams, Sr., Raymond G. Johnson, Jr.
  • Patent number: H2206
    Abstract: Side-slip of an aircraft during flight is detected through a pair of pressure sensors fixedly mounted on opposite lateral sides of the aircraft fuselage. Pressure measurement signals at said sensors are fed to electronic circuitry within the aircraft for generating magnitude and frequency signals reflective of the side-slip that are applied to a pair of vibrators respectively mounted on the undersides of a pair of pilot foot pedals located within the cockpit. The foot pedals are connected by linkage to the tail rudder on the aircraft fuselage. The varying magnitude and frequency of vibrations applied to the rudder foot pedals by the vibrators enables the pilot to immediately sense side-slip through the feet on the pedals. In response to such side-slip sensing, one of the pedals may be timely depressed for side-slip corrective angular displacement of the rudder.
    Type: Grant
    Filed: October 28, 2004
    Date of Patent: December 4, 2007
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventor: Judah H. Milgram