Acceleration Control Patents (Class 244/191)
  • Patent number: 10974814
    Abstract: A wing, a method of controlling lift on a wing, and a system to produce lift on a wing are provided. The wing may include a fore-element, an aft-element, a pivotable linkage that operatively connects the aft-element leading edge to the fore-element trailing edge in a span-wise direction, and an actuator. The actuator may deflect the aft-element through a predetermined deflection angle about the pivotable linkage relative to the fore-element within less than or equal to two convective periods. The method may include deflecting a span-wise flap through the deflection angle in less than or equal to two convective periods to produce high lift. The system may include a sensor to detect an input and a controller to deflect the span-wise flap of the wing by the deflection angle in not more than two convective periods based on the received input signal.
    Type: Grant
    Filed: July 6, 2020
    Date of Patent: April 13, 2021
    Assignee: United States of America as represented by the Secretary of the Air Force
    Inventors: Michael V Ol, Alberto Medina
  • Patent number: 10919617
    Abstract: An aerial vehicle comprising an airframe, an aircraft flight controller to provide an output control signal, and a planar printed circuit board positioned on the airframe. The printed circuit board may include coupled thereto a processor, a rate gyroscope, and at least three accelerometers. The processor is configured to generate an actuation signal based at least in part on a feedback signal received from at least one of said rate gyroscope and the at least three accelerometers. The processor communicates the actuation signal to said aircraft flight controller, which is configured to adjust the output control signal based on said actuation signal.
    Type: Grant
    Filed: October 19, 2017
    Date of Patent: February 16, 2021
    Assignee: Aurora Flight Sciences Corporation
    Inventors: Riley Griffin, Edward Scott, Sean Humbert
  • Patent number: 10745107
    Abstract: A wing, a method of controlling lift on a wing, and a system to produce lift on a wing are provided. The wing may include a fore-element, an aft-element, a pivotable linkage that operatively connects the aft-element leading edge to the fore-element trailing edge in a span-wise direction, and an actuator. The actuator may deflect the aft-element through a predetermined deflection angle about the pivotable linkage relative to the fore-element within less than or equal to two convective periods. The method may include deflecting a span-wise flap through the deflection angle in less than or equal to two convective periods to produce high lift. The system may include a sensor to detect an input and a controller to deflect the span-wise flap of the wing by the deflection angle in not more than two convective periods based on the received input signal.
    Type: Grant
    Filed: January 3, 2018
    Date of Patent: August 18, 2020
    Inventors: Michael V. Ol, Alberto Medina
  • Patent number: 10487761
    Abstract: A vehicle control apparatus that makes it possible to attempt fuel consumption improvement and exhaust gas reduction effectively without causing a sense of incompatibility in the driver is provided. When traveling following the preceding vehicle, kinetic energy required for an own vehicle in future is predicted on the basis of kinetic energy of the own vehicle, a velocity of a preceding vehicle, and a distance between the own vehicle and the preceding vehicle. It is determined whether there is kinetic energy enough for the own vehicle to be able to follow the preceding vehicle with inertial traveling, on the basis of the predicted kinetic energy and current kinetic energy. When it is determined that the kinetic energy is sufficient and the driving and traveling state of the own vehicle satisfies other traveling idling reduction conditions, control of stopping the engine is exercised.
    Type: Grant
    Filed: March 14, 2014
    Date of Patent: November 26, 2019
    Assignee: Hitachi Automotive Systems, Ltd.
    Inventors: Takeo Shibata, Hiroshi Kuroda
  • Patent number: 9714056
    Abstract: A method of controlling a vehicle includes moving a lift generating device to generate lift when a vehicle speed is greater than a pre-defined speed, a steering angle of the vehicle is equal to or less than a minimum angle value, a lateral acceleration of the vehicle is equal to or less than a minimum lateral acceleration value, and a corner brake fluid pressure at any of the wheels is equal to or less than a minimum brake fluid pressure. A downforce generating device is moved to generate downforce when the vehicle speed is greater than the pre-defined speed, the steering angle is equal to or greater than a maximum angle value, the lateral acceleration is equal to or greater than a maximum lateral acceleration value, and the corner brake fluid pressure at any of the wheels is equal to or greater than a maximum brake fluid pressure.
    Type: Grant
    Filed: January 30, 2015
    Date of Patent: July 25, 2017
    Assignee: GM Global Technology Operations LLC
    Inventor: J. William Handzel, Jr.
  • Patent number: 9645580
    Abstract: A homeostatic flying hovercraft preferably utilizes at least two pairs of counter-rotating ducted fans to generate lift like a hovercraft and utilizes a homeostatic hover control system to create a flying craft that is easily controlled. The homeostatic hover control system provides true homeostasis of the craft with a true fly-by-wire flight control and control-by-wire system control.
    Type: Grant
    Filed: September 21, 2016
    Date of Patent: May 9, 2017
    Assignee: QFO Labs, Inc.
    Inventors: Brad Pedersen, Peter Spirov
  • Patent number: 9086427
    Abstract: An object of the invention is to provide an inertial sensor with small delay and high accuracy. An inertial sensor 1 includes an acceleration detecting element 2 that detects an acceleration of at least one axis of a vehicle; a first filter 6 that limits a detection signal of the acceleration to a first band; a second filter 7 that limits a detection signal of the acceleration to a second band; a vehicle control variable calculation section 8 that calculates a vehicle control variable Gxc on the basis of the detection signal of the acceleration limited to the second band; and a sensor signal output section 9 that outputs the detection signal of the acceleration limited to the first band and the vehicle control variable.
    Type: Grant
    Filed: January 11, 2012
    Date of Patent: July 21, 2015
    Assignee: Hitachi Automotive Systems, Ltd.
    Inventors: Daisuke Maeda, Heewon Jeong, Masahide Hayashi, Makoto Yamamoto
  • Patent number: 8498758
    Abstract: Present novel and non-trivial system, device, and method for generating altitude data and/or height data are disclosed. A processor receives navigation data from an external source such as a global positioning system (“GPS”); receives navigation data from multiple internal sources; receives object data representative of terrain or surface feature elevation; determines an instant measurement of aircraft altitude as a function of these inputs; and generates aircraft altitude data responsive to such determination. In an additional embodiment, the processor receives reference point data representative of the elevation of the stationary reference point (e.g., a landing threshold point); determines an instant measurement of aircraft height as a function of this input and the instant measurement of aircraft altitude; and generates aircraft height data responsive to such determination.
    Type: Grant
    Filed: November 26, 2012
    Date of Patent: July 30, 2013
    Assignee: Rockwell Collins, Inc.
    Inventors: Douglas A Bell, James H. Doty, Sarah Barber, Felix B. Turcios
  • Patent number: 8478456
    Abstract: Some embodiments relate to a method of controlling a flight of a flight vehicle according to a first mode of operation and changing the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation. Other embodiments relate to a flight-control system for a flight vehicle configured to control a flight of a flight vehicle according to a first mode of operation and to control the flight of the flight vehicle according to a second mode of operation to use less energy than the first mode of operation. Other embodiments relate to a control actuation system configured to control positions of aerodynamic elements in a flight vehicle in response to commands from a guidance system according to a first mode of operation and to change the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation.
    Type: Grant
    Filed: August 8, 2011
    Date of Patent: July 2, 2013
    Assignee: Raytheon Company
    Inventors: Jeffery P. Sowers, Karl F. Spiessbach, Donald E. Croft
  • Patent number: 8321074
    Abstract: Present novel and non-trivial system, device, and method for generating altitude data and/or height data are disclosed. A processor receives navigation data from an external source such as a global positioning system (“GPS”); receives navigation data from multiple internal sources; receives object data representative of terrain or surface feature elevation; determines an instant measurement of aircraft altitude as a function of these inputs; and generates aircraft altitude data responsive to such determination. In an additional embodiment, the processor receives reference point data representative of the elevation of the stationary reference point (e.g., a landing threshold point); determines an instant measurement of aircraft height as a function of this input and the instant measurement of aircraft altitude; and generates aircraft height data responsive to such determination.
    Type: Grant
    Filed: August 3, 2012
    Date of Patent: November 27, 2012
    Inventors: Douglas A. Bell, James H. Doty
  • Publication number: 20120146816
    Abstract: The device (1) comprises means (10) for determining, in the case of the loss of a speed information, control parameters which are used on at least one automatic pilot of the aircraft, instead of said speed information.
    Type: Application
    Filed: February 20, 2012
    Publication date: June 14, 2012
    Applicant: AIRBUS OPERATIONS (SAS)
    Inventors: Thierry Bourret, Pascale Louise, Jean Muller, Xavier Dal Santo
  • Patent number: 8185259
    Abstract: The fuzzy logic-based control method for helicopters carrying suspended loads utilizes a controller based on fuzzy logic membership distributions of sets of load swing angles. The anti-swing controller is fuzzy-based and has controller outputs that include additional displacements added to the helicopter trajectory in the longitudinal and lateral directions. This simple implementation requires only a small modification to the software of the helicopter position controller. The membership functions govern control parameters that are optimized using a particle swarm algorithm. The rules of the anti-swing controller are derived to mimic the performance of a time-delayed feedback controller. A tracking controller stabilizes the helicopter and tracks the trajectory generated by the anti-swing controller.
    Type: Grant
    Filed: August 23, 2010
    Date of Patent: May 22, 2012
    Assignee: King Fahd University of Petroleum & Minerals
    Inventor: Hanafy M. Omar
  • Patent number: 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
  • Publication number: 20080099628
    Abstract: A method and apparatus for aiding pilots in aerial refueling comprises a primary auto-throttling system (ATS) disposed in a primary aircraft and a secondary ATS disposed in a secondary aircraft. The primary ATS includes logic which generates and transmits an anticipatory signal to the secondary ATS. Based upon the received anticipatory signal, the secondary ATS automatically controls a throttle of the secondary aircraft so as to maintain an airspeed of the primary aircraft. The anticipatory signals include rate of change information including at least one of rate of change of airspeed of the primary aircraft, rate of change of pitch of the primary aircraft, and rate of change of weight of the primary aircraft.
    Type: Application
    Filed: September 28, 2006
    Publication date: May 1, 2008
    Inventor: Randall A. Greene
  • Patent number: 7146299
    Abstract: The present invention is a system and method for easily adjusting flight characteristics of a simulated aircraft. The system allows a user to adjust commanded pitch, roll or yaw values or steady state frequency response values that are associated with an atmospheric temperature value, an atmospheric dynamic pressure value, aileron position, rudder position, and elevator position.
    Type: Grant
    Filed: August 16, 2002
    Date of Patent: December 5, 2006
    Assignee: The Boeing Company
    Inventor: Steven W. Cooke
  • Publication number: 20040256521
    Abstract: A method of accelerating a destruction of a vortex formed at a rear of a wing of an aircraft by merging first and second co-rotating eddies. A periodic perturbation is generated adjacent an area of creation the first eddy. The periodic perturbation has a wavelength capable of exciting at least one instability mode of the first eddy.
    Type: Application
    Filed: November 21, 2003
    Publication date: December 23, 2004
    Inventors: Alexandre Corjon, Thomas Leweke, Florent LaPorte
  • Patent number: 6539290
    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: May 30, 2000
    Date of Patent: March 25, 2003
    Assignee: Dabulamanzi Holdings, LLC
    Inventor: David W. Vos
  • Patent number: 6459228
    Abstract: The present invention provides an active control system for coupling the movements of a pair of independently operated manual input devices such as dual flight control sticks operated by a pilot and co-pilot flying an aircraft. Each input device is configured to receive manual input data in the form of angular displacement of the device about one or more rotational axes. The active control system provides desired tactile feedback to an operator who displaces one of the manual input devices in the form of a restorative centering force. If an external system such as an auto-pilot system is engaged, the restorative force may be in a direction necessary to reconcile manual displacement of the input device with a position commanded by the external system, rather than directed toward the center position. The system also acts to reflect manual displacement of each input device as a force applied to the other.
    Type: Grant
    Filed: March 22, 2001
    Date of Patent: October 1, 2002
    Assignee: MPC Products Corporation
    Inventors: Zenon Szulyk, Brian Dyra, Alex Makhlin
  • Patent number: 6253481
    Abstract: The invention provides for a shotgun mountable shell holder which may be readily attached to the forearm of a shotgun. The present invention includes a first member having a forearm mounting region and a second member having a shell mounting region. The present invention is constructed so that when it is mounted to a shotgun it may hold an additional round of ammunition near the forehand of the shooter along the forearm or grip of the gun.
    Type: Grant
    Filed: May 6, 1999
    Date of Patent: July 3, 2001
    Inventor: George R. Melby
  • Patent number: 6189836
    Abstract: A feedback system for reducing the effects of destabilizing forces in a vehicle (e.g. helicopter) by utilizing acceleration feedback data sensed by an acceleration sensor located in the vehicle. This sensed acceleration signal is passed through a low-pass filter and combined with a command signal to produce an error signal. The error signal is multiplied by a predetermined gain to produce a corrective signal that is utilized by actuators to adjust an adjustable surface, such as a swashplate, on the vehicle.
    Type: Grant
    Filed: September 25, 1998
    Date of Patent: February 20, 2001
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Phillip Jeremy Gold, John Randall Mayo
  • 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
  • Patent number: 5815407
    Abstract: An apparatus (700) for inhibiting operation of an electronic device (702) during take-off and landing of an aircraft (802) has a sensor (704) that measures a lateral acceleration. A control circuit (706) is coupled to the sensor (704) and has an output (708) coupled to the electronic device (702).
    Type: Grant
    Filed: December 14, 1995
    Date of Patent: September 29, 1998
    Assignee: Motorola Inc.
    Inventors: James R. Huffman, Ronald D. Cruickshank, Shrirang Nikanth Jambhekar, Jeffrey Van Myers, Russell L. Collins
  • Patent number: 5722620
    Abstract: Disclosed is a pitch-axis stability and command augmentation system (19) in which a pilot column input (.delta..sub.C) is provided to a pitch command processor (26), the output of which is a C*U feedforward command (C*U.sub.FFC) that is supplied as an additive input to a combining unit (20). The combining unit (20) receives a second additive input of an augmented feedback command signal (AFB.sub.COM). The resulting output is filtered and generates an elevator command signal (.delta..sub.e,FILT). The command processor (26) additionally supplies a corrected column position signal (.delta..sub.C,COR) to a pitch command C*U processor (26) that converts the corrected column position signal (.delta..sub.C,COR) into a C*U pitch command (C*U.sub.PilotCmd), representative of the pilot's requested elevator pitch which is generated by movement of the control cola. A computed C*U processor (32) forms a computed C*U signal (C*U.sub.Computed) that is based on the current state of the aircraft.
    Type: Grant
    Filed: May 15, 1995
    Date of Patent: March 3, 1998
    Assignee: The Boeing Company
    Inventors: Kioumars Najmabadi, Monte R. Evans, Edward E. Coleman, Robert J. Bleeg, Richard S. Breuhaus, Dorr Marshall Anderson, Timothy A. Nelson
  • Patent number: 5641136
    Abstract: A flight control system that provides energy management for an aircraft. The flight control system includes an energy control system which generates a first error signal that is a function of an actual energy characteristic and a threshold energy characteristic. The energy characteristic may be the bleed rate of the aircraft. The error signal is converted into a control surface command signal which moves the control surface(s) of the aircraft, accordingly. The control system limits the movement of the control surface(s) so that the actual energy characteristic does not exceed the threshold energy characteristic. The energy control system can be coupled to a nominal control system which generates a second error signal that is a function of a pilot input command and a feedback signal which is indicative of the present state of the aircraft. The second error signal can also be converted to a control surface command signal which moves the control surface(s) of the aircraft.
    Type: Grant
    Filed: December 22, 1994
    Date of Patent: June 24, 1997
    Assignee: Eidetics Aircraft, Inc.
    Inventors: Andrew Skow, William M. Porada, William A. Clark
  • Patent number: 5589749
    Abstract: A feedback control system which uses estimated back electromotive force(EMF) from a controlled actuator to provide feedback into the control system and improve control of the actuator. Back EMF is estimated from current through the actuator and voltage across the actuator. The estimated back EMF signal is fed back into the control system where it serves as a rate term. In the preferred embodiment the back EMF signal is used in combination with an actuator position signal which is also feedback into the control system. A complementary filter conditions both the rate and position signals for improved performance. The invention is particularly suited for controlling linear actuators which do not provide conventional rate feedback signals.
    Type: Grant
    Filed: August 31, 1994
    Date of Patent: December 31, 1996
    Assignee: Honeywell Inc.
    Inventors: Dale D. Davidson, Hamid R. Sadeghpour
  • Patent number: 5248114
    Abstract: An autopilot system including parameter identification circuits wherein the function of the torque and the function of the translational force on a missile are unknown and varying (including approaching zero).
    Type: Grant
    Filed: June 20, 1974
    Date of Patent: September 28, 1993
    Inventor: Dewey P. Ankeney
  • Patent number: 5186416
    Abstract: A system for reducing the forces applied to the wings of an aircraft in flight includes an accelerometer for measuring the vertical acceleration of the aircraft and generators for generating signals to control the aerodynamic surfaces in the wings of the aircraft as a function of the acceleration measured by the accelerometer. The control signal generator is not activated except when the vertical acceleration exceeds a predetermined value.
    Type: Grant
    Filed: December 27, 1990
    Date of Patent: February 16, 1993
    Assignee: Societe Anonyme dite: Aerospatiale Societe Nationale Industrielle
    Inventors: Pierre Fabre, Xavier Le Tron, Philippe Lacoste
  • Patent number: 5128671
    Abstract: A hand-held joystick has spaced-apart groups of accelerometers and is free to move or rotate on multiple axes. Each group has, for example, three mutually perpendicular accelerometers, with each one producing an electrical signal responsive to linear acceleration along one axis. The signals are combined to derive a definition of acceleration of the joystick along the three mutually perpendicular linear axes and/or rotation about these axes. The combined signal is used by an electrical control system which provides input to a device being controlled. The signal to the device under control is responsive to the motion of the joystick.
    Type: Grant
    Filed: April 12, 1990
    Date of Patent: July 7, 1992
    Assignee: LTV Aerospace and Defense Company
    Inventor: William A. Thomas, Jr.
  • Patent number: 5058836
    Abstract: A control system for the reentry phase of a reentry type vehicle with the vehicle having aerodynamic control surfaces for controlling the attitude of the vehicle during reentry includes an estimating device, such as an extended Kalman filter, for estimating dynamic aerodynamic operational parameters of the vehicle in response to status parameters of the vehicle, a sensing device for supplying the status parameters, an autopilot device for generating a drive command signal in response to the dynamic aerodynamic operaational parameters and an actuator device, which may include an electric motor or smaller hydraulic one than prior systems, for controlling the aerodynamics control surfaces in response to the drive command signal. Computation necessary for estinmating is used to determine a more accurate drive command signal than is typically available from prior systems, thereby permitting a smaller, lighter weight actuator to be used.
    Type: Grant
    Filed: December 27, 1989
    Date of Patent: October 22, 1991
    Assignee: General Electric Company
    Inventor: Charles I. Nobel
  • Patent number: 5053767
    Abstract: The invention provides for the detection of both longitudinal and vertical windshears during the takeoff and landing phases of aircraft flight. Standard instrumentation available on many aircraft is used to calculate the aircraft's energy loss or gain by integrating the value of the longitudinal shear. When the energy loss or gain exceeds predetermined levels, appropriate annuciation is provided to the human pilot. The same standard instrumentation aforementioned is also used to calculate changes in the aircraft's specific energy rate, that is the aircraft's actual energy rate divided by the aircraft's weight, to determine the effect of vertical winds. Specific energy rate is calculated by integrating the difference between the aircraft's acceleration relative to the ground and its acceleration relative to the airmass in which it is flying.
    Type: Grant
    Filed: March 12, 1990
    Date of Patent: October 1, 1991
    Assignee: Honeywell Inc.
    Inventors: Terry L. Zweifel, Khosrow H. Youssefi
  • Patent number: 4905934
    Abstract: The gust alleviation system was designed to be an add-on to any existing g-command flight control system. The system assumes that there already exists, a stability augmentation system which will hold the aircraft's attitude. This system minimizes the interaction of the gust alleviation system with the existing flight control system. The gust alleviation system picks off the stick displacement signal and the aircraft normal acceleration sensor signal and processes this information. The outputs of the gust alleviation system are added back respectively to the existing flap command signal and the aircraft's original stability augmentation loop.
    Type: Grant
    Filed: July 5, 1988
    Date of Patent: March 6, 1990
    Assignee: Grumman Aerospace Corporation
    Inventor: Jimmie Chin
  • Patent number: 4857922
    Abstract: An improved windshear warning apparatus for aircraft, responsive to both the magnitude of the wind shear and the allowable time the windshear can be tolerated at a given magnitude. The sensed magnitude is used to compute the allowable time before providing a windshear alarm. For large windshear rates, the allowable time is short; conversely for small windshear rates which exceed a threshold level, a longer time period is computed before an alarm occurs. Since a windshear rate must persist for the computed allowable time before activating the alarm, windshear rates that are above the threshold level for elapsed time less than the computed allowable time will not result in an enunciation, while high magnitude windshear rates of short duration will not cause false alarms since they do not exceed the computed allowable time.
    Type: Grant
    Filed: February 28, 1986
    Date of Patent: August 15, 1989
    Assignee: Honeywell Inc.
    Inventors: Harry Miller, Terry Zweifel
  • Patent number: 4821981
    Abstract: This invention provides a system for enhancing the performance of an aircraft during flight. The aircraft, which includes at least two control surfaces, such as stabilon and trailing edge flaps, includes devices for: generating a signal representative of the optimum normal acceleration from signals representative of the aircraft's flight status, generating a signal representative of the aircraft's actual normal acceleration, comparing the optimum signal to the actual signal, and generating a command to alter the position of either one or both of the aircraft's control surfaces to reduce any differences between the optimum and actual normal acceleration signals.
    Type: Grant
    Filed: January 25, 1988
    Date of Patent: April 18, 1989
    Assignee: The Boeing Company
    Inventors: Dagfinn Gangsaas, Daniel C. Norman
  • Patent number: 4697768
    Abstract: Strake, flap and canard control surfaces of an aircraft are driven by an error signal which is comprised of a pilot stick command signal and feedback components including measured vertical acceleration and pitch rate of the aircraft and a third feedback component derived from a complementary filter. The filter has a high-pass filter section which operates upon canard position data and a low-pass filter section which operates upon pitch rate. A summation of the signals passing both filtering sections is summed with the vertical acceleration and pitch rate feedback signals to form a combined feedback signal.
    Type: Grant
    Filed: November 12, 1985
    Date of Patent: October 6, 1987
    Assignee: Grumman Aerospace Corporation
    Inventor: Robert W. Klein
  • Patent number: 4651958
    Abstract: In order to achieve fine control of the velocity of an aircraft flying a predetermined flight path at a predetermined nominal speed in the presence of such perturbations as wind gusts, a low inertia, fast acting device is extended or deployed into the aircraft dragstream and is rapidly position-modulated in response to sensed acceleration/deceleration to instantaneously slightly alter the total system drag to an amount which causes the aircraft to maintain the predetermined velocity. Among the exemplary alternative low inertia devices disclosed are: fuselage and wing mounted flaps which are rapidly more or less extended, a trailing cable which is rapidly reeled in or out, and a trailing inflatable member whose degree of inflation is rapidly changed, all in response to sensed acceleration/deceleration from an on-board system.
    Type: Grant
    Filed: September 17, 1984
    Date of Patent: March 24, 1987
    Assignee: Atlantic Richfield Company
    Inventor: Joseph E. Zupanick
  • Patent number: 4645144
    Abstract: In order to achieve fine control of the velocity of an aircraft flying a predetermined flight path at a predetermined nominal speed in the presence of such perturbations as wind gusts, a low inertia, fast acting device is extended or deployed into the aircraft dragstream and is rapidly position-modulated in response to sensed acceleration/deceleration to instanteneously slightly alter the total system drag to an amount which causes the aircraft to maintain the predetermined velocity. Among the exemplary alternative low inertia devices disclosed are: fuselage and wing mounted flaps which are rapidly more or less extended, a trailing cable which is rapidly reeled in or out, and a trailing inflatable member whose degree of inflation is rapidly changed, all in response to sensed acceleration/deceleration from an on-board system.
    Type: Grant
    Filed: December 13, 1985
    Date of Patent: February 24, 1987
    Assignee: Atlantic Richfield Company
    Inventor: Joseph E. Zupanick
  • Patent number: 4593285
    Abstract: A windshear warning apparatus which separately compares a plurality of signals derived from horizontal and vertical inertial acceleration and air mass acceleration components to indicate incipient windshear. The compared signals are substantially equal under normal wind conditions but are significantly different under windshear conditions. A signal proportional to the product of the magnitude and rate of change of the total or resultant inertial acceleration of the aircraft is used to provide a warning of a significant windshear condition.
    Type: Grant
    Filed: May 6, 1983
    Date of Patent: June 3, 1986
    Assignee: Sperry Corporation
    Inventors: Harry Miller, Terry L. Zweifel
  • Patent number: 4562546
    Abstract: A stability augmentation system for a forward swept wing aircraft is disclosed that corrects a dynamic instability phenomenon which occurs when the whole vehicle (rigid body) motion couples with the wing structural motion. The sensors are positioned and their output signals combined such that wing structural motion is isolated. Specifically positioned wing control surfaces are operated to suppress such motion with minimal resulting rigid body pitch motion inducing inputs.
    Type: Grant
    Filed: January 13, 1983
    Date of Patent: December 31, 1985
    Assignee: Rockwell International Corporation
    Inventors: John H. Wykes, Gerald D. Miller
  • Patent number: 4229725
    Abstract: A system to warn an aircraft pilot of a hazardous wind shear condition in which the rate of change of airspeed is compared to the ability of the aircraft to respond thereto. Any difference therebetween that exceeds a predetermined threshold is used to activate a suitable alarm or compensation device. Additional refinements include correcting the inertial speed inputs for vertical components and autopilot induced throttle changes, and correcting the air speed inputs for short term fluctuations.
    Type: Grant
    Filed: May 12, 1978
    Date of Patent: October 21, 1980
    Inventor: Richard J. Reilly
  • Patent number: 4127249
    Abstract: A rate of change of energy computer utilizing signal processing of the inner vectorial product of inertial acceleration and inertial velocity wherein such parameters are derived utilizing outputs from the aircraft INS (inertial navigation system) and from body mounted accelerometers.
    Type: Grant
    Filed: February 7, 1977
    Date of Patent: November 28, 1978
    Assignee: The Boeing Company
    Inventor: Antonius A. Lambregts
  • Patent number: 4095271
    Abstract: In order to provide a more accurate representation of aircraft pitch attitude for use in aircraft head up display devices, a circuit for generating a computed pitch signal responds to a longitudinal accelerometer and a vertical gyroscope within the aircraft wherein the computed pitch signal is generated by adding to the gyro pitch signal a correction factor computed by subtracting the value of the computed pitch signal from an inertial pitch signal derived from the longitudinal accelerometer. In order to compensate for the effects of aircraft acceleration on the longitudinal accelerometer signal, a computed acceleration signal derived from the difference between the longitudinal accelerometer signal and the gyro pitch signal is subtracted from the longitudinal accelerometer to generate the inertial pitch signal.
    Type: Grant
    Filed: April 20, 1977
    Date of Patent: June 13, 1978
    Assignee: Sundstrand Data Control, Inc.
    Inventor: Hans Rudolf Muller
  • Patent number: 4079905
    Abstract: The output of a transducer providing a signal representing the instantaneous airspeed of an aircraft is differentiated and fed to a summing device. Also fed to the summing device are a signal representing the horizontal acceleration of the aircraft which is subtracted from the instantaneous airspeed signal, and a signal in accordance with the downdraft drift angle of the aircraft which is added to the instantaneous airspeed signal. The output of the summing device represents the magnitude of the wind shear condition (rate of change of wind velocity) as modified by a downdraft drift angle signal. This output signal is fed to appropriate indicator apparatus which may comprise an appropriate display, a peak magnitude storage device, a warning device including a dangerous wind condition and/or a telemetering device providing a reading to a ground station for use in advising other aircraft.
    Type: Grant
    Filed: February 7, 1977
    Date of Patent: March 21, 1978
    Assignee: Safe Flight Instrument Corporation
    Inventor: Leonard M. Greene
  • 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: 4012713
    Abstract: The output of a transducer providing a signal in accordance with the instantaneous air speed of an aircraft is differentiated and fed to a summing device which subtracts therefrom a signal in accordance with the horizontal acceleration of the aircraft, this signal being derived from the output of an inertial instrument such as an accelerometer. The output of the summing device represents the magnitude of the wind shear condition (rate of change of wind velocity with changes in altitude). This signal is fed to appropriate indicator means which may comprise an appropriate display, a peak magnitude storage device, a warning device indicating a dangerous wind shear condition, or a telemetering device providing a wind shear reading to a ground station for use in advising other aircraft.
    Type: Grant
    Filed: November 5, 1975
    Date of Patent: March 15, 1977
    Assignee: Safe Flight Instrument Corporation
    Inventors: Leonard M. Greene, Ramon Bloch
  • Patent number: 3998411
    Abstract: A system for compensating for certain speed overshoot problems encountered in large instrument-controlled aircraft during long-term deceleration from high speeds, such as may be encountered in preparation for descent to landing approach from cruise conditions. During such long-term deceleration, the aircraft vertical gyro miss-erects due to an effect of the deceleration upon the gyro positioning control circuitry. The present system compensates for the gyro signal error, used for developing the aircraft speed command following deceleration, by the use of a threshold detector and filter to develop a compensation signal having a delay and amplitude related to the input control signals involved.
    Type: Grant
    Filed: February 17, 1976
    Date of Patent: December 21, 1976
    Assignee: McDonnell Douglas Corporation
    Inventor: Frederick C. Blechen
  • Patent number: 3979090
    Abstract: An improved second order gyroscopic attitude and heading reference system including separate variable time constant accelerometer integrators for independently controlling the velocity error signals associated with respective east and north acceleration signals to provide velocity damped output signals so that a high acceleration input signal of dubious accuracy will have minimal precessional authority while a lower acceleration input signal of greater accuracy will retain nominal control.
    Type: Grant
    Filed: March 17, 1975
    Date of Patent: September 7, 1976
    Assignee: Sperry Rand Corporation
    Inventors: David R. Brickner, James S. Johnson