By Change In Speed Patents (Class 244/182)
  • Patent number: 10295349
    Abstract: A flight management system for an aircraft and method of securing open world data using such a system. The flight management system includes at least two flight management computers including one computer termed active forming part of an active guidance subsystem configured to supply data for guiding the aircraft. Another computer is termed inactive at the current time. The flight management system includes a validation subsystem that includes the inactive flight management computer and a validation unit connected to the flight management computers. The validation subsystem is independent of the active guidance subsystem and configured to validate open world data and to transmit at least to the active flight management computer data that is validated during the validation.
    Type: Grant
    Filed: May 23, 2017
    Date of Patent: May 21, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventor: Jean-Claude Mere
  • Patent number: 10273021
    Abstract: A flight-time variable associated with an aircraft is determined including by determining the flight-time variable while the aircraft is flying. It is determined whether the aircraft is airworthy based at least in part on the flight-time variable. In response to determining that the aircraft is not airworthy, the aircraft is automatically landed.
    Type: Grant
    Filed: June 22, 2018
    Date of Patent: April 30, 2019
    Assignee: Kitty Hawk Corporation
    Inventors: Alexander David Selwa, Mark Johnson Cutler
  • Patent number: 10227933
    Abstract: A method of controlling thrust for a gas turbine engine of an aircraft is provided. The method includes determining a fan speed required for minimum thrust to achieve an aircraft operation. The method also includes determining an excess amount of thrust generated by the gas turbine engine. The method also includes reducing the amount of thrust generated by the gas turbine engine.
    Type: Grant
    Filed: February 12, 2015
    Date of Patent: March 12, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Kurt J. Sobanski, Richard P. Meisner, Robert J. Bengtson
  • Patent number: 10219067
    Abstract: A sound system is provided with a headphone that includes a transducer and at least one microphone. The sound system also includes an equalization filter and a loop filter circuit. The equalization filter is adapted to equalize an audio input signal based on at least one predetermined coefficient. The loop filter circuit includes a leaky integrator circuit that is adapted to generate a filtered audio signal based on the equalized audio input signal and a feedback signal indicative of sound received by the at least one microphone, and to provide the filtered audio signal to the transducer.
    Type: Grant
    Filed: August 29, 2014
    Date of Patent: February 26, 2019
    Assignee: Harman International Industries, Incorporated
    Inventor: Ulrich Horbach
  • Patent number: 10196154
    Abstract: In some embodiments, a system is provided that includes a portable electronic device; and an application executable on the portable electronic device, the application including computer program code that (a) monitors acceleration data during a flight of an airplane; and (b) displays a representation of the acceleration data in relation to a threshold acceleration of the airplane. Numerous other aspects are provided.
    Type: Grant
    Filed: July 18, 2017
    Date of Patent: February 5, 2019
    Inventor: Brian M. Dugan
  • Patent number: 10184348
    Abstract: A system and method are provided for controlling turbine blade tip-to-static structure clearance in a gas turbine engine installed on an aircraft. Mode control data are processed to determine that a fuel-saving mode is enabled, and aircraft data are processed to determine that the aircraft gas turbine engine is generating a substantially constant thrust. The turbine blade tip-to-static structure clearance in the aircraft gas turbine engine is minimized upon determining that both the aircraft gas turbine engine is generating a substantially constant thrust and the fuel-saving mode is enabled. The turbine blade tip-to-static structure clearance in the aircraft gas turbine engine is then selectively increased to a predetermined clearance, and a change in aircraft gas turbine engine thrust is prevented until the predetermined clearance is achieved.
    Type: Grant
    Filed: December 5, 2013
    Date of Patent: January 22, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Gregory C. Carlucci, Glenn Alexander Knight, Jim Rumbo, Dennis D Loots, Roger Peckham, Marko Bacic, James Kenneth Haberstock
  • Patent number: 10173676
    Abstract: Provided are a travel assist device capable of producing, in a preferred manner, warning vibrations notifying deviation of a vehicle with respect to a travel path, and a method of controlling the same. A travel assist device includes a travel assist control device that notifies a driver about an anti-deviation direction or a deviation direction by making a steering angular acceleration in the deviation direction and the steering angular acceleration in the anti-deviation direction different from each other when producing warning vibrations, wherein a time-derivative value of a steering angle of a steering wheel is defined as a steering angular velocity, and a time-derivative value of the steering angular velocity is defined as the steering angular acceleration.
    Type: Grant
    Filed: April 9, 2015
    Date of Patent: January 8, 2019
    Assignee: Honda Motor Co., Ltd.
    Inventors: Daisuke Hanzawa, Shinnosuke Ishida, Kentaro Yamada, Hiroyasu Kubota, Makoto Ito
  • Patent number: 10134289
    Abstract: Methods and systems are provided for guiding or otherwise assisting operation of a vehicle to intersect a stabilized approach to a destination. One exemplary method of assisting an aircraft for landing at an airport involves obtaining, from a system onboard the aircraft, a current position of the aircraft and a current velocity of the aircraft, determining a descent strategy for the aircraft from the current position to an initialization point for a stable approach to the airport based at least in part on the current position and the current velocity, and providing indication of the descent strategy on a display device. The descent strategy is determined based on one or more validation criteria associated with the initialization point so that one or more predicted values for one or more characteristics of the aircraft satisfy the one or more validation criteria at the initialization point.
    Type: Grant
    Filed: February 18, 2016
    Date of Patent: November 20, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Zdenek Moravek, Robert Sosovicka, Filip Magula, David Kunes, Katerina Sprinarova, Ivan Lacko
  • Patent number: 10101749
    Abstract: A rotorcraft includes airspeed sensors, inertial sensors, and a flight control computer (FCC) operable to provide a longitudinal control for the rotorcraft. The FCC receives a first indication of longitudinal airspeed from the airspeed sensors and receives a first indication of longitudinal acceleration from the inertial sensors. The FCC generates a filtered indication of longitudinal airspeed from the first indication of longitudinal airspeed and generates a scaled and filtered indication of longitudinal acceleration from the first indication of longitudinal acceleration. The FCC combines the filtered indication of longitudinal airspeed with the scaled and filtered indication of longitudinal acceleration to generate a determined longitudinal airspeed. The FCC generates a flight control signal to control operation of the rotorcraft, the flight control signal based on the determined longitudinal airspeed.
    Type: Grant
    Filed: March 21, 2017
    Date of Patent: October 16, 2018
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Luke Dafydd Gillett, Robert Earl Worsham, II
  • Patent number: 10040542
    Abstract: In accordance with an embodiment of the present invention, a method of operating a rotorcraft includes operating the rotorcraft in a speed control mode, where a speed of the rotorcraft is proportional to a pilot control command; detecting a high longitudinal acceleration condition; upon detection of the high longitudinal acceleration condition, temporarily disabling the speed control mode and stabilizing the rotorcraft while the speed control mode is disabled; and reestablishing the speed control mode when a measured longitudinal acceleration of the rotorcraft falls below a first threshold.
    Type: Grant
    Filed: February 7, 2017
    Date of Patent: August 7, 2018
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Luke Gillett, Sung K. Kim
  • Patent number: 10036348
    Abstract: A method for controlling a position of a variable nozzle of an aircraft includes the following steps: setting the variable nozzle in a position P(t0) at a time t0 as a preliminary step; step A in which at each instant ti with 1<i<N, an optimal position P(ti) of the variable nozzle is determined according to magnitudes distinctive of the flight of the aircraft; step B measuring a time interval ?ti defined as a difference between ti and t0; and step C by which a displacement of the variable nozzle in a position corresponding to the optimal position P(ti) is authorized when the time interval ?ti is higher than a predetermined minimum threshold.
    Type: Grant
    Filed: December 29, 2014
    Date of Patent: July 31, 2018
    Assignee: AIRCELLE
    Inventors: Pierre Caruel, Hervé Hurlin, Olivier Kerbler
  • Patent number: 9815569
    Abstract: A computer apparatus and method to determine aircraft fuel mileage performance. The computer apparatus including a memory and a processor disposed in communication with the memory and configured to issue a plurality of instructions stored in the memory. The instructions issue signals to receive real-time aircraft data during aircraft flight and process the real-time data to determine real-time aircraft mass data. A calculation is performed to determine the real-time fuel mileage performance for the aircraft based upon determined real-time aircraft mass data.
    Type: Grant
    Filed: August 11, 2016
    Date of Patent: November 14, 2017
    Assignee: Rosemount Aerospace Inc.
    Inventors: Thomas J. Horsager, Michael Haukom, William Baumgarten, Matthew J. Hansen, Kenneth J. Freeman
  • Patent number: 9696724
    Abstract: A system, device, and method for a takeoff (T/O) of an aircraft are disclosed. The T/O automating system may include an autothrottle system configured with a plurality of thrust modes, an autopilot system configured with a plurality of vertical guidance modes; and a flight management computer (FMC). The FMC may be configured to perform the method of receiving of input data representative of inputs of a T/O profile selection, a first profile altitude, a second profile altitude, and/or a third altitude; generating output data representative of outputs which includes a command engaging a thrust mode and a command engaging a vertical guidance mode to provide pitch attitude guidance commensurate to a speed and/or vertical speed; and providing the output data to the autothrottle system and the autopilot system. In some embodiments, the T/O profile could be a profile designed for one or more noise abatement departure profiles.
    Type: Grant
    Filed: April 22, 2016
    Date of Patent: July 4, 2017
    Assignee: Rockwell Collins, Inc.
    Inventors: Norm W. Arons, Kirk A. Kolek, Brannen M. Clark, Mark Wayne Volner
  • Patent number: 9646114
    Abstract: A method and apparatus for establishing a validated stable design for a stable electrical power system. An initial design for an electrical power system is established. The initial design for the electrical power system satisfies design requirements. The initial design for the electrical power system is simulated for a plurality of simulated operating conditions for the electrical power system to generate simulation data. Stability parameter requirements for a stable design for the electrical power system are established from the simulation data. A hardware implementation of the stable design for the electrical power system is tested to generate hardware testing data. The stable design for the electrical power system is validated using the hardware testing data to establish a validated stable design for the electrical power system.
    Type: Grant
    Filed: July 10, 2013
    Date of Patent: May 9, 2017
    Assignee: The Boeing Company
    Inventors: Kamiar J. Karimi, Eugene V. Solodovnik, Zachary R. Lewis, Jeffrey Joseph White
  • Patent number: 9567097
    Abstract: A computer apparatus and method to determine aircraft fuel mileage performance. The computer apparatus including a memory and a processor disposed in communication with the memory and configured to issue a plurality of instructions stored in the memory. The instructions issue signals to receive real-time aircraft data during aircraft flight and process the real-time data to determine real-time aircraft mass data. A calculation is performed to determine the real-time fuel mileage performance for the aircraft based upon determined real-time aircraft mass data.
    Type: Grant
    Filed: January 29, 2013
    Date of Patent: February 14, 2017
    Assignee: Rosemount Aerospace Inc.
    Inventors: Thomas Horsager, Michael Haukom, William Baumgarten, Matthew Hansen, Kenneth Freeman
  • Patent number: 9342988
    Abstract: A device comprising a computation unit for computing, for each of a plurality of different distances relative to a threshold of a landing runway along a lateral approach trajectory, a geometric altitude, using a measured and stored barometric altitude, a computation unit for computing a terrain height, by subtracting, from the computed geometric altitude, a measured and stored height, and a computation unit for determining a terrain profile from the set of terrain heights computed for the set of different distances.
    Type: Grant
    Filed: December 30, 2014
    Date of Patent: May 17, 2016
    Assignee: AIRBUS OPERATIONS (S.A.S.)
    Inventors: Thierry Bourret, Kenji Ahualle Horimoto
  • Patent number: 9324193
    Abstract: A method for reporting aircraft data is described that includes receiving, at a processing device, data relating to a condition experienced during operation of the aircraft, determining a cost relevance for the data, comparing, with the processing device, the cost relevance for the data to a threshold, transmitting the data to an end user system if the cost relevance exceeds the threshold, and storing the data in a memory if the cost relevance does not exceed the threshold.
    Type: Grant
    Filed: September 8, 2011
    Date of Patent: April 26, 2016
    Assignee: The Boeing Company
    Inventors: Michael D. Sudolsky, Jeanne C. Maggiore
  • Patent number: 9224302
    Abstract: A four dimensional time controlled flight management system (4DFMS) and related method generate an initial descent profile for an aircraft in flight. The initial descent profile is planned in compliance with a 1) a published arrival procedure at an airport, 2) a fuel-efficient optimized profile descent (OPD), and a required time of arrival (RTA) constraint at a metering waypoint on the published arrival. The 4DFMS maintains awareness of the changing wind conditions during cruise mode and descent mode of operation and triggers a replan of the descent profile should compliance fall outside of a 95% confidence level at a six second compliance requirement in the descent mode. The system continuously generates a total time error at the metering waypoint by projecting estimated time of arrivals at active waypoints to determine accurate altitude, airspeed, and time compliance at the metering waypoint.
    Type: Grant
    Filed: May 29, 2015
    Date of Patent: December 29, 2015
    Assignee: Rockwell Collins, Inc.
    Inventors: Shih-Yih Young, Kristen M. Jerome
  • Patent number: 9213335
    Abstract: A method for controlling aircraft time of arrival at a flight trajectory waypoint decouples the various parts of the flight for flight plan, speed scheduling, and trajectory predictions. Adjustments to the speed during a first cruise phase of the flight reduce the deviations between the actual and estimated arrival times throughout the flight, and particularly reduce the amount of speed adjustments necessary during the later descent phase.
    Type: Grant
    Filed: February 3, 2015
    Date of Patent: December 15, 2015
    Assignee: The Boeing Company
    Inventor: David Garrido-Lopez
  • Patent number: 8676403
    Abstract: The present invention relates to methods of controlling the flight path of an aircraft to follow as closely as possible a predetermined four-dimensional flight path, such as when flying continuous descent approaches. A method of controlling an aircraft to follow a predetermined four-dimensional flight path is provided that comprises monitoring an actual along-track position and an actual vertical position of the aircraft relative to corresponding desired positions on the predetermined flight path. Throttle commands are generated based on deviations of the actual vertical position of the aircraft from the desired vertical position. Elevator commands are generated based on the deviation of the actual along-track position from the desired along-track position and on the deviation of the actual vertical position from the desired vertical position.
    Type: Grant
    Filed: April 15, 2010
    Date of Patent: March 18, 2014
    Assignee: The Boeing Company
    Inventors: David Garrido-Lopez, Ramon Gomez Ledesma
  • Patent number: 8606437
    Abstract: A longitudinal control law is designed to optimize the flying qualities when aircraft is set to approach configuration, i.e. when the flap lever is set to the landing position and landing gears are locked down. Under such circumstances, the effort of trimming the aircraft speed can be extremely reduced by the usage of a momentary on-off switch or other control in the sidestick, instead of or in addition to a conventional trim up-down switch, making easier the task of airspeed selection by the pilot. This control law provides excellent handling qualities during approach and landing, with the benefit of not needing or using radio altimeter information in safety-critical applications.
    Type: Grant
    Filed: November 28, 2011
    Date of Patent: December 10, 2013
    Assignee: Embraer S.A.
    Inventors: Fabricio Reis Caldeira, Marcos Vinicius Campos, Reneu Luiz Andrioli, Jr., Wagner de Oliveira Carvalho, Dagfinn Gangsaas, Eduardo Camelier, Daniel Siqueira, Lucas Rubiano
  • Patent number: 8600586
    Abstract: An improved stable approach monitor (SAM) system provides an audible advisory to a pilot when an aircraft is on a final landing approach. More specifically, the SAM system compares a measured airspeed of the aircraft to a predetermined flap placard speed. If the measured airspeed exceeds the predetermined flap placard speed then the improved SAM system provides an audible advisory indicating the airspeed of the aircraft is too fast. Advantageously, this audible advisory should prevent the pilot from attempting to deploy the flaps at an excessive airspeed and in turn focuses the pilot's attention on the problem at hand, which would be to reduce the airspeed of the aircraft. Once the airspeed is equal to or below the predetermined flap placard speed, the improved SAM system may provide another audible advisory informing the pilot to commence deployment of the flaps.
    Type: Grant
    Filed: February 4, 2009
    Date of Patent: December 3, 2013
    Assignee: Honeywell International Inc.
    Inventors: Yasuo Ishihara, Kevin J Conner, Steve Johnson
  • Patent number: 8457872
    Abstract: The invention relates to a method for managing the flight of an aircraft flying along a trajectory and being subject to an absolute time constraint (on a downstream point) or relative time constraint (spacing with respect to a downstream aircraft), the said aircraft comprising a flight management system calculating a temporal discrepancy to the said time constraint, wherein the said method includes the following steps: the calculation of a distance on the basis of the temporal discrepancy, the modification of the trajectory: if the temporal discrepancy to the time constraint corresponds to an advance, the lengthening of the trajectory by the distance; if the temporal discrepancy to the time constraint corresponds to a delay, the shortening of the trajectory by the distance.
    Type: Grant
    Filed: February 23, 2010
    Date of Patent: June 4, 2013
    Assignee: Thales
    Inventor: Guy Deker
  • Patent number: 8332080
    Abstract: The invention relates to a method and device to assist in navigation in an airport sector. The inventive method and device make it possible to automatically calculate the points of intersection between the path of the flight plan and the zones having speed limitations all around an airport and calculate a speed profile conforming to these limitations. The inventive method and device also make it possible to use an automatic guidance automatically defining flight instructions corresponding to the calculated speed profile. Furthermore, the invention calculates predictions concerning the flight parameters.
    Type: Grant
    Filed: June 6, 2008
    Date of Patent: December 11, 2012
    Assignee: Thales
    Inventors: Manuel Gutierrez-Castaneda, Stéphane Paris
  • Patent number: 8321071
    Abstract: A method and systems for controlling a speed of a vehicle are provided. The control system includes an input device configured to receive a required time of arrival (RTA) at a waypoint and a processor communicatively coupled to said input device, said processor programmed to automatically determine a dynamically adjustable range for an autothrottle control using an RTA error and a speed control tolerance, the RTA error representing a difference between an estimated time of arrival (ETA) and the RTA, the speed control tolerance representing a tolerance range about the vehicle speed profile. The control system also includes an output device communicatively coupled to said processor, said output device is configured to transmit at least one of a thrust control signal and a drag control signal to a speed control system of the vehicle.
    Type: Grant
    Filed: July 31, 2009
    Date of Patent: November 27, 2012
    Assignee: GE Aviation Systems, LLC
    Inventor: Joel Kenneth Klooster
  • Patent number: 8311687
    Abstract: A method and systems for controlling an aircraft during descent are provided. The control system includes an input device configured to receive a speed margin for the vehicle and a processor communicatively coupled to the input device wherein the processor is programmed to automatically determine a flight path of the vehicle that is shallower than an idle flight path for the vehicle and generate a flight control surface control signal configured to maintain the determined flight path using the received speed margin. The control system further includes an output device communicatively coupled to the processor. The output device is configured to transmit the flight control surface control signal to a flight control system of the vehicle.
    Type: Grant
    Filed: July 30, 2010
    Date of Patent: November 13, 2012
    Assignee: GE Aviation Systems LLC
    Inventor: Michael John Bakker
  • Patent number: 8214089
    Abstract: A flight control system moves elevators according to a pilot command summed with an automatic command. The flight control system monitors a set of flight parameters to determine if the flight vehicle is operating inside a permitted envelope. The flight controls system incorporates automatic protections thru the automatic elevator command if the flight vehicle is close to its envelope limits. The exemplary illustrative non-limiting implementation herein provides automatic protections in order to protect the flight vehicle from low speeds, high attitude, stalls and buffetings.
    Type: Grant
    Filed: November 9, 2010
    Date of Patent: July 3, 2012
    Assignee: EMBRAER - Empresa Brasileira de Aeronautica S.A.
    Inventors: Fabricio Reis Caldeira, Dagfinn Gangsaas, Alvaro Vito Polati de Souza, Eduardo da Silva Martins, Marco Tulio Sguerra Vita, Jose Marcio Vieira Dias Filho, Marcos Vinicius Campos, Emerson Freitas
  • 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: 8170727
    Abstract: The invention relates to a method for calculating an approach trajectory of an aircraft (200) to an airport The aircraft is slaveable in terms of trajectory, thrust and/or speed. The aircraft is able to advance at reduced engine revs. The airport has a runway The approach trajectory terminates in an impact point (205) on the runway and has a high-altitude descent segment (217) and an intermediate geometric segment (207), to which the aircraft is slaved in terms of trajectory and speed. A step of calculating a final approach segment (208) at reduced engine revs and a landing segment is performed with a greater thrust than the reduced revs so as to prepare a possible go-around (209), to which the aircraft is slaved in terms of thrust and speed.
    Type: Grant
    Filed: April 16, 2008
    Date of Patent: May 1, 2012
    Assignee: Thales
    Inventor: Guy Deker
  • Patent number: 8131410
    Abstract: In accordance with an embodiment, a method includes displaying information corresponding to automatically controlled engine thrust levels during a reduced engine thrust period of flight of an aircraft. The information corresponds to one or more parameters associated with a flight control computer of the aircraft. In an alternate aspect, the displayed information includes alphanumeric information formatted in accordance with a sequential order of the automatically controlled engine thrust levels. In a further aspect, the alphanumeric information corresponds to first, second and third engine thrust levels.
    Type: Grant
    Filed: June 15, 2007
    Date of Patent: March 6, 2012
    Assignee: The Boeing Company
    Inventors: Mark I. Nikolic, Barbara E. Holder
  • Publication number: 20120053760
    Abstract: Guiding an aircraft to follow a four-dimensional flight path during a descent with a nominal thrust setting corresponding to idle thrust or non-idle thrust includes monitoring actual along-track position and actual vertical position of the aircraft relative to corresponding desired positions on the flight path, generating control commands based on deviations of the actual vertical position of the aircraft from the desired vertical position, and generating elevator commands based on the deviation of the actual along-track position from the desired along-track position, wherein generating control commands includes, if the deviation of the actual vertical position from the desired vertical position indicates that the aircraft is too low, generating a throttle command to increase the thrust setting to above nominal thrust, and generating a speed brake command to deploy speed brakes when the deviation of the actual vertical position from the desired vertical position indicates that the aircraft is too high.
    Type: Application
    Filed: June 24, 2011
    Publication date: March 1, 2012
    Applicant: THE BOEING COMPANY
    Inventors: Kevin A. BURNSIDE, David GARRIDO-LOPEZ, Kevin R. ELMER, Ramon GOMEZ LEDESMA
  • Patent number: 8095300
    Abstract: A method and device for generating a speed profile for an aircraft rolling on the ground. The device (1) comprises means (8) for automatically determining a speed profile which is suited to successive elements of a ground rolling trajectory and which complies with maximum speeds and particular constraints.
    Type: Grant
    Filed: December 8, 2008
    Date of Patent: January 10, 2012
    Assignee: Airbus Operations SAS
    Inventors: Fabrice Villaume, Pierre Scacchi
  • Patent number: 8010267
    Abstract: Methods and a system for a vehicle control system using a reference time profile including an upper control bound and a lower control bound are provided. The system includes an input device configured to receive a required time of arrival at a waypoint and a processor communicatively coupled to said input device wherein the processor is programmed to generate a reference time profile using a first speed profile up to an intermediate control point and a second speed profile between the intermediate control point and an RTA waypoint. The system also includes an output device communicatively coupled to the processor wherein the output device is configured to transmit a speed control signal based on the reference time profile to a vehicle speed control system.
    Type: Grant
    Filed: October 31, 2008
    Date of Patent: August 30, 2011
    Assignee: General Electric Company
    Inventors: Joel Kenneth Klooster, Keith Douglas Wichman
  • Patent number: 7931238
    Abstract: A flight control system for an aircraft receives a selected value of a first parameter, which is either the airspeed or inertial velocity of the aircraft. A primary feedback loop generates a primary error signal that is proportional to the difference between the selected value and a measured value of the first parameter. A secondary feedback loop generates a secondary error signal that is proportional to the difference between the selected value of the first parameter and a measured value of a second flight parameter, which is the other of the airspeed and inertial velocity. The primary and secondary error signals are summed to produce a velocity error signal, and the velocity error signal and an integrated value of the primary error signal are summed to produce an actuator command signal. The actuator command signal is then used for operating aircraft devices to control the first parameter to minimize the primary error signal.
    Type: Grant
    Filed: September 12, 2005
    Date of Patent: April 26, 2011
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Kenneth E. Builta, Kynn J. Schulte
  • Patent number: 7626514
    Abstract: Systems and methods for controlling activation of a look-ahead function of a terrain alert and warning system. The system receives rate of climb and aircraft speed information, compares the rate of climb and aircraft speed information to a predefined threshold, and deactivates a look-ahead function based on the comparison.
    Type: Grant
    Filed: October 4, 2006
    Date of Patent: December 1, 2009
    Assignee: Honeywell International Inc.
    Inventors: Yasuo Ishihara, Charles D. Bateman
  • Patent number: 7571045
    Abstract: In a gas-turbine engine control system having a first control channel inputting the outputs of sensors to calculate and output a first command value indicative of a quantity of fuel to be supplied to the engine and a second control channel inputting the outputs of the sensors to calculate and output a second command value similarly indicative of the quantity of fuel, the second control channel calculates and outputs the second command value using the first command value so long as the instruction to switch the outputs is not generated, while calculates and outputs the second command value, without using the first command value, when the instruction to switch the outputs is generated. With this, immediately after switching to the second command value, the second command value is made substantially equal to and not greatly different from the preceding first command value.
    Type: Grant
    Filed: May 24, 2005
    Date of Patent: August 4, 2009
    Assignee: Honda Motor Co., Ltd.
    Inventors: Hironori Muramatsu, Yukinobu Sugitani
  • Patent number: 7512464
    Abstract: A system and method are disclosed for controlling the speed of an aircraft having a preprogrammed speed profile when transitioning from a manually set target speed to the preprogrammed speed profile. In operation, an input is received indicating that a user desires to transition from a manually set target speed to the preprogrammed speed profile. A determination is then made as to whether the manually set target speed satisfies one or more selected conditions for qualifying as a constraint speed of the preprogrammed speed profile. If the manually set target speed satisfies the one or more selected conditions, the preprogrammed speed profile is updated to include the manually set target speed as a constraint speed and the speed of the aircraft is controlled using the updated speed profile.
    Type: Grant
    Filed: December 22, 2005
    Date of Patent: March 31, 2009
    Assignee: The Boeing Company
    Inventors: Tom Tarleton, Jason Koszola, Peter D. Gunn
  • Publication number: 20080308681
    Abstract: Systems and methods for providing supplemental drag to an aircraft are disclosed. In one embodiment, a method includes detecting changes in at least one throttle resolver angle (TRA). Deflections are determined for one or more flight control surfaces based on the changes in TRA, and accordingly, the one or more flight control surfaces are deflected automatically to generate supplemental drag. The one or more flight control surfaces include at least one at least one of an aileron, a spoiler, and an elevator. Additionally, in one instance, the deflections of the one or more flight control surfaces is implemented as a rated limited time lag function of the changes in TRA.
    Type: Application
    Filed: June 15, 2007
    Publication date: December 18, 2008
    Applicant: THE BOEING COMPANY
    Inventors: Douglas L. Wilson, Julie R. Brightwell, Christopher P. Beamis
  • Publication number: 20080308682
    Abstract: A flight control system for an aircraft receives a selected value of a first parameter, which is either the airspeed or inertial velocity of the aircraft. A primary feedback loop generates a primary error signal that is proportional to the difference between the selected value and a measured value of the first parameter. A secondary feedback loop generates a secondary error signal that is proportional to the difference between the selected value of the first parameter and a measured value of a second flight parameter, which is the other of the airspeed and inertial velocity. The primary and secondary error signals are summed to produce a velocity error signal, and the velocity error signal and an integrated value of the primary error signal are summed to produce an actuator command signal. The actuator command signal is then used for operating aircraft devices to control the first parameter to minimize the primary error signal.
    Type: Application
    Filed: September 12, 2005
    Publication date: December 18, 2008
    Inventors: Kenneth E. Builta, Kynn J. Schulte
  • Patent number: 7463956
    Abstract: This invention relates to the concept of managing the rate of change of energy in a helicopter or other aeronautical vehicle. The invention uses energy management calculations to determine the maximum longitudinal and lateral inputs that can be made while still enabling the vehicle to maintain a desired vertical state. The results of the calculations can be cued to the pilot either tactilely, aurally, or visually, or used for internal software limiting.
    Type: Grant
    Filed: July 3, 2003
    Date of Patent: December 9, 2008
    Assignee: The Boeing Company
    Inventors: Pieter G. Einthoven, Channing S. Morse
  • Patent number: 7437237
    Abstract: A positioning control apparatus including feedback loops according to a plurality of control modes which control positioning of an object to be controlled is provided, in which the positioning control apparatus includes a part (121, 122, 123, 124) for reflecting a control process performed by a control mode before being switched in a control process performed by a control mode after being switched when a control mode is switched to another control mode. For example, an operation parameter on the control mode before being switched is dynamically reflected in the control mode after being switched.
    Type: Grant
    Filed: April 30, 2002
    Date of Patent: October 14, 2008
    Assignee: Fujitsu Limited
    Inventor: Kenichi Murakado
  • Patent number: 6989769
    Abstract: A method and system is utilized to produce an output corresponding to a safety level, particularly in relation to an activity on a moving body. The method involving producing an output corresponding to the ability to perform an operation within a safe limit on a moving vessel. The method comprising the steps of acquiring real time data from instrumentation on the vessel indicative of first and second elements of vessel motion relevant to the safety of the operation. Processing the data relating to each element of motion. Scaling the data relating to each element to a common scale to provide first and second values relating to the respective elements of vessel motion. Determining which value is of greatest significance and providing a output indicative of the greatest value.
    Type: Grant
    Filed: July 26, 2002
    Date of Patent: January 24, 2006
    Assignee: MacTaggart Scott (Holdings) Limited
    Inventor: Anthony James Gray
  • Patent number: 6886786
    Abstract: An engine thrust management system comprising an engine control device, an aircraft flight manual, a flight management device and a cockpit instrument device. The engine control device is operable to calculate a percent maximum available thrust parameter and a percent indicated thrust parameter. The aircraft flight manual is operable to calculate a required thrust parameter. The flight management device is operable to calculate a percent thrust setting target parameter and a percent commanded thrust parameter. The percent commanded thrust is the amount of thrust requested by an aircraft operator. The percent commanded thrust is varied by the operator according to the value of the percent thrust setting target parameter and the value of the percent indicated thrust parameter in order to produce optimal thrust.
    Type: Grant
    Filed: October 10, 2003
    Date of Patent: May 3, 2005
    Assignee: The Boeing Company
    Inventor: Kiet T. Huynh
  • Patent number: 6819266
    Abstract: An aircraft system for reducing the airspeed of an aircraft as it passes through a preselected altitude includes an automatic throttle system including a computer, a device for inputting a preselected altitude and a preselected airspeed into the computer. An altimeter provides the current altitude of the aircraft and an aircraft instrument provides the current air speed and the vertical speed of the aircraft. The computer in response to the current altitude and vertical speed of the aircraft generates a signal to retard the throttles when the current altitude, the current air speed of the aircraft is equal to 2 times the vertical speed plus a preselected altitude.
    Type: Grant
    Filed: October 7, 2002
    Date of Patent: November 16, 2004
    Assignee: Safe Flight Instrument Corporation
    Inventor: Randall A. Greene
  • Patent number: 6643568
    Abstract: A system for automatically controlling lift augmentation devices of an aircraft, during a phase of take-off by the aircraft, includes a controllable actuator that shifts the lift-augmentation devices, and a control unit for generating control demands to control the actuator to bring the lift-augmentation devices into a defined position. The control unit further includes a detector that detects actual take-off by the air craft and, if appropriate, signals such detection to the control unit. At start of the take-off phase, the lift-augmentation device are brought into a first position, in which they are deployed. The control unit generates, at least when the detector signals the actual take-off, a control demand making it possible to bring the lift-augmentation devices into a second position, in which the lift-augmentation devices are retracted by comparison with the first position.
    Type: Grant
    Filed: November 19, 2001
    Date of Patent: November 4, 2003
    Assignee: Airbus France
    Inventors: Dominique Chatrenet, Gérard Mathieu, Fernando Alonso, Martine Cart-Lamy
  • Patent number: 6571171
    Abstract: An apparatus and method for inserting a waypoint into a preexisting flight plan which includes selecting a waypoint on a graphical display of a portion of the flight plan and automatically generating a proposed changed flight plan based upon inserting the waypoint into the nearest leg of the flight plan.
    Type: Grant
    Filed: September 8, 1999
    Date of Patent: May 27, 2003
    Assignee: Rockwell Collins, Inc.
    Inventor: Martin Pauly
  • Patent number: 6507782
    Abstract: The instant invention provides a system and method for controlling the flight of an aircraft to meet an RTA. The system comprises a speed profile generator that communicates with a trajectory generator to produce a speed profile signal that enables the aircraft to reach a waypoint substantially at a predetermined time. In the system of the instant invention, the speed profile generator receives a nominal speed command signal, a time error signal and a sensitivity signal. Based on these inputs, the speed profile generator produces a speed profile signal. The trajectory generator receives the speed profile signal and a required time of arrival signal. Based on these signals, the trajectory generator produces a time error signal and a sensitivity signal. This sensitivity signal represents the sensitivity of the time error signal to changes in the speed profile signal.
    Type: Grant
    Filed: May 14, 2001
    Date of Patent: January 14, 2003
    Assignee: Honeywell International Inc.
    Inventors: Jim R. Rumbo, Michael R. Jackson, Brian E. O'Laughlin
  • Patent number: 6450456
    Abstract: An airborne power control system for automatically controlling the power of an aircraft during landing is disclssed. The system includes a computer and a minimum airspeed program as a function of altitude. A radio altimeter or the like senses the instantaneous altitude of the aircraft while a pitot tube or the like measures indicated airspeed. A computer and program compare programmed airspeed with actual airspeed for a given altitude. And, a servomotor is provided for decreasing engine thrust where the actual airspeed exceeds the programmed airspeed at any given altitude. An inhibitor inhibits the decrease in engine thrust if the airspeed drops below the programmed airspeed.
    Type: Grant
    Filed: December 20, 1999
    Date of Patent: September 17, 2002
    Assignee: Safe Flight Instrument Corporation
    Inventor: Leonared M. Greene
  • Patent number: 6324448
    Abstract: A method, an apparatus and a computer program product are provided for accurately determining the vertical speed of an aircraft in a manner independent of signals provided by an air data computer, an inertial reference system and an inertial navigation system. Initially, a first vertical velocity of the aircraft is determined based upon a pressure altitude value associated with the aircraft. A second vertical velocity of the aircraft is also obtained from a GPS receiver carried by the aircraft. The first and second vertical velocities are then combined to determine the vertical speed of the aircraft. In this regard, the first and second vertical velocities are combined by complimentarily filtering the first and second vertical velocities. More particularly, the first vertical velocity is typically low pass filtered to remove high frequency noise that is attributable to the relatively low resolution of the first vertical velocity value.
    Type: Grant
    Filed: May 12, 2000
    Date of Patent: November 27, 2001
    Assignee: Honeywell International, Inc
    Inventor: Steven C. Johnson
  • Patent number: 6062513
    Abstract: In a method of flight control in which a thrust command is computed based on the total aircraft energy error relative to flight path and speed control commands, and an elevator command is computed based on the energy distribution error relative to the same flight path and speed control commands, an improvement is provided including an elevator control command in response to a column control input by the pilot. In the short term, the computing establishes a change in flight path angle beyond the sustainable flight path angle at the trim speed for the prevailing thrust condition. In the long term, the computing establishes a change in speed relative to a set reference speed, the speed change being proportional to the column control input. In the long term, the computing establishes a flight path angle equal to a sustainable value for the prevailing thrust condition and the altered speed condition.
    Type: Grant
    Filed: September 14, 1998
    Date of Patent: May 16, 2000
    Assignee: The Boeing Company
    Inventor: Antonius A. Lambregts