公开(公告)号：BR8402038A

公开(公告)日：1984-12-11

申请号：BR8402038

申请日：1984-05-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FISCHER WILLIAM CHRISTIAN ,  WRIGHT STUART C ,  VERZELLA DAVID JOHN

IPC: G05B23/02 ,  B64C13/00 ,  B64C13/24 ,  G05B9/03 ,  G05D1/00

Abstract: In a dual actuator system, runaways are identified by comparing the position and rate of one actuator to another. When there is a threshold position discrepancy and a sustained rate discrepancy, a fault is indicated. The faster actuator is identified as the runaway.

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.

公开(公告)号：AU657001B2

公开(公告)日：1995-02-23

申请号：AU2506392

申请日：1992-08-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WRIGHT STUART C ,  DRYFOOS JAMES B

IPC: B64C13/18 ,  B64C13/50 ,  G05D1/08 ,  G05D17/02

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.

公开(公告)号：CA2116566A1

公开(公告)日：1993-03-18

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 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.

公开(公告)号：CA2113730A1

公开(公告)日：1993-03-18

申请号：CA2113730

申请日：1992-07-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WRIGHT STUART C ,  ADAMS DON L ,  GOLD PHILLIP J

IPC: B64C13/50 ,  G05D1/00 ,  G05D1/08

公开(公告)号：AU596939B2

公开(公告)日：1990-05-17

申请号：AU2211088

申请日：1988-09-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： NOVIS ARI M ,  WRIGHT STUART C ,  ADAMS DON L

IPC: H02P7/06 ,  H02P7/00 ,  H02P7/288 ,  H02P7/282

Abstract: A method of and an arrangement for controlling the operation of a reversible D.C. electric motor including a winding having two ends each of which is connected to both the positive and negative terminals of an electric current source through respective control switches that can be selectively closed and opened in response to command signals to apply voltage differentials across the winding with attendant electric current flow through the winding in one or the opposite direction for operating the electric motor in one or the other of its senses of rotation with intervening rotation sense reversals utilize the original command signals for determining when the sense of rotation reversal would result in an excessive electric current flow through the winding. In such a case, the original command signals are temporarily replaced by substitute command signals of such a character that both of the winding ends are connected through the respective control switches to only one of the electric current source terminals with attendant dynamic braking of the electric motor.

公开(公告)号：IT1173944B

公开(公告)日：1987-06-24

申请号：IT2076284

申请日：1984-05-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FISCHER WILLIAM C ,  ADAMS DON LUIS ,  WRIGHT STUART C ,  VERZELLA DAVID J

IPC: B64C13/00 ,  B64C13/08 ,  B64C13/18 ,  B64C13/44 ,  B64C27/56 ,  B64C27/57 ,  G05B9/03 ,  G05D1/08 ,  B64C

Abstract: The directions of travel of an inner and an outer loop actuator are monitored for movement in opposite directions within selected ranges and the outer loop actuator is disabled under selected conditions. These conditions may include movement of both the inner and outer loop actuators in opposite directions, any one of which has been detected moving at a rate greater than a selected rate or to a position outside a selected range. The invention is particularly suited for an aircraft trim actuator shutdown monitor system.

公开(公告)号：GB2140174A

公开(公告)日：1984-11-21

申请号：GB8410987

申请日：1984-04-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FISCHER WILLIAM C ,  WRIGHT STUART C ,  VERZELLA DAVID JOHN ,  ADAMS DON LUIS

IPC: B64C13/00 ,  B64C13/08 ,  B64C13/18 ,  B64C13/44 ,  B64C27/56 ,  B64C27/57 ,  G05B9/03 ,  G05D1/08

Abstract: The directions of travel of an inner and an outer loop actuator are monitored for movement in opposite directions within selected ranges and the outer loop actuator is disabled under selected conditions. These conditions may include movement of both the inner and outer loop actuators in opposite directions, any one of which has been detected moving at a rate greater than a selected rate or to a position outside a selected range. The invention is particularly suited for an aircraft trim actuator shutdown monitor system.

公开(公告)号：GB2140172A

公开(公告)日：1984-11-21

申请号：GB8410985

申请日：1984-04-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FISCHER WILLIAM C ,  WRIGHT STUART C ,  VERZELLA DAVID JOHN

IPC: B64C13/00 ,  G05B9/03 ,  G05D1/00

公开(公告)号：ES2089550T3

公开(公告)日：1996-10-01

申请号：ES92917949

申请日：1992-07-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GOLD PHILLIP J ,  LAPPOS NICHOLAS D ,  ADAMS DON L ,  WRIGHT STUART C

IPC: G05D1/08

Abstract: A helicopter flight control system includes an automatic turn coordination system which provides a coordinating yaw command signal to the tail rotor of the helicopter. The system stores on command a trim attitude (e.g., signals indicative of bank angle, lateral ground speed, and lateral acceleration) about which automatic turn coordination is provided, thus providing the pilot with automatic turn coordination about attitudes other than wings level.