中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

12 records (took 0.026 seconds)

    IMPROVED MODEL FOLLOWING CONTROL SYSTEM
    2.
    发明专利
    IMPROVED MODEL FOLLOWING CONTROL SYSTEM 未知

    公开(公告)号：CA2116566C

    公开(公告)日：2000-06-06

    申请号：CA2116566

    申请日：1992-08-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： WRIGHT STUART C ,  DRYFOOS JAMES B

    IPC: B64C13/18 ,  B64C13/50 ,  G05D1/08

    Abstract: An aircraft flight control system including model following control laws includes improved logic and algorithms to limit the error between a desired parameter value from the output of a model and an actual parameter value. Such logic is operable to sense the amount of said parameter error and io limit the amount of the error if it exceeds a predetermined value. The difference between the predetermined limit and the actual error is fed back to the model such that the output of the model is adjusted so that the error between the desired and actual parameter values does not exceed the predetermined value.

    INERTIAL VELOCITY COMMAND SYSTEM
    3.
    发明专利
    INERTIAL VELOCITY COMMAND SYSTEM 未知

    公开(公告)号：CA2191861A1

    公开(公告)日：1995-12-14

    申请号：CA2191861

    申请日：1995-05-04

    Applicant: UNITED TECHNOLOGIES CORP SIKOR

    Inventor： GOLD PHILLIP J ,  FOGLER DONALD L JR ,  DRYFOOS JAMES B

    IPC: B64C13/00 ,  B64C13/18 ,  B64C27/57 ,  G05D1/08 ,  G05D1/10

    Abstract: A velocity command system is provided with a velocity stabilization mode wherein aircraft flight path referenced velocities are determined with respect to an inertial frame of reference, the flight path referenced velocities are held constant during pilot commanded yaw maneuvers so that the aircraft maintains a fixed inertial referenced flight path regardless of the pointing direction of the aircraft. Velocity control with respect to an inertial frame of reference is accomplished by controlling the aircraft flight path based on aircraft body referenced commanded lateral and longitudinal acceleration and based on aircraft body referenced lateral and longitudinal centrifugal acceleration. Operation in the velocity stabilization mode is provided in response to the manual activation of the velocity stabilization mode by the pilot, provided that the aircraft is already operating in the ground speed mode and the aircraft is not in a coordinated turn.

    4.
    发明专利
    未知

    公开(公告)号：ES2120206T3

    公开(公告)日：1998-10-16

    申请号：ES95919762

    申请日：1995-05-04

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GOLD PHILLIP J ,  FOGLER DONALD L JR ,  DRYFOOS JAMES B

    IPC: B64C13/00 ,  B64C13/18 ,  B64C27/57 ,  G05D1/08 ,  G05D1/10

    Abstract: A velocity command system is provided with a velocity stabilization mode wherein aircraft flight path referenced velocities are determined with respect to an inertial frame of reference, the flight path referenced velocities are held constant during pilot commanded yaw maneuvers so that the aircraft maintains a fixed inertial referenced flight path regardless of the pointing direction of the aircraft. Velocity control with respect to an inertial frame of reference is accomplished by controlling the aircraft flight path based on aircraft body referenced commanded lateral and longitudinal acceleration and based on aircraft body referenced lateral and longitudinal centrifugal acceleration. Operation in the velocity stabilization mode is provided in response to the manual activation of the velocity stabilization mode by the pilot, provided that the aircraft is already operating in the ground speed mode and the aircraft is not in a coordinated turn.

    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING AZIMUTH AND PITCH CONTROL
    6.
    发明专利
    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING AZIMUTH AND PITCH CONTROL 未知

    公开(公告)号：CA2118024A1

    公开(公告)日：1993-11-25

    申请号：CA2118024

    申请日：1993-05-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LAPPOS NICHOLAS D ,  DRYFOOS JAMES B ,  KELLER JAMES F ,  FOWLER DONALD W

    IPC: B64C13/18 ,  B64C27/04 ,  F41G3/22 ,  G05D1/08

    Abstract: 2118024 9323715 PCTABScor01 A fire control system (55) azimuth command and elevation command provides a flight control system attitude reference in response to operation of the flight control system in a coupled aiming mode. The coupled aiming mode is engaged in response to the continuous operation of a pilot switch (920), the azimuth command and elevation command being below respective threshold magnitudes (940, 941), and the operation of the fire control system (55). During operation in the coupled aiming mode, the azimuth command and elevation command replace the yaw attitude feedback error signal and pitch attitude error signal, respectively, as the aircraft attitude reference. During integration of the fire control system and the flight control system, the flight control system is made less sensitive to small pilot command stick inputs below a stick input threshold magnitude, so that small or inadvertent pilot commanded yaw and pitch maneuvers will not affect the yaw and pitch attitude reference commanded by the fire control system azimuth and elevation commands. However, intended pilot commanded yaw and pitch maneuvers (70) maintain full authority at all times.

    8.
    发明专利
    未知

    公开(公告)号：ES2083185T3

    公开(公告)日：1996-04-01

    申请号：ES92919085

    申请日：1992-08-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： WRIGHT STUART C ,  DRYFOOS JAMES B

    IPC: B64C13/18 ,  B64C13/50 ,  G05D1/08

    Abstract: An aircraft flight control system including model following control laws includes improved logic and algorithms to limit the error between a desired parameter value from the output of a model and an actual parameter value. Such logic is operable to sense the amount of said parameter error and to limit the amount of the error if it exceeds a predetermined value. The difference between the predetermined limit and the actual error is fed back to the model such that the output of the model is adjusted so that the error between the desired and actual parameter values does not exceed the predetermined value.

    9.
    发明专利
    未知

    公开(公告)号：ES2080512T3

    公开(公告)日：1996-02-01

    申请号：ES92917911

    申请日：1992-07-31

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SKONIECZNY JOSEPH P ,  FOGLER DONALD L JR ,  GOLD PHILIPP J ,  KELLER JAMES F ,  DRYFOOS JAMES B

    IPC: G05D1/08 ,  B64C13/18

    Abstract: A helicopter flight control system (21) includes a model following control system architecture which automatically provides a coordinating yaw command signal to the helicopter tail rotor to coordinate helicopter flight during a banked turn. The control system processes information from a variety of helicopter sensors (31) in order to provide the coordinating yaw command signal on an output line (72) to the tail rotor (20) of the helicopter.

Patent Agency Ranking