公开(公告)号：KR820001684B1

公开(公告)日：1982-09-17

申请号：KR780000600

申请日：1978-03-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： JOHNSON RAYMOND G ,  COTTON LOU S ,  VERZELLA DAVID J

IPC: B64C13/16

Abstract: The helicopter stabilator(22), combining the functions of tail stabilizer and aircraft elevator, has its angle of incidence with respect to the helicopter controlled by a pair of reversibie actuators(30, 31) acting in series and controlled by a slosed-loop. The controls are disconnected when the actuators fail to track within a threshold disparity of either position or rate of change of position of each other. A test switch introduces an imbalance to test the fault circutry. The stabilator is biased to assume a miximum incidence position at low speeds, including hover.

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：CA2113648A1

公开(公告)日：1993-02-04

申请号：CA2113648

申请日：1992-07-09

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ADAMS DON L SR ,  WRIGHT STUART C ,  VERZELLA DAVID J ,  LAMONTAGNE TROY J

IPC: B64C27/57 ,  G05B5/01 ,  G05B13/02 ,  G05D1/00 ,  G05D1/08

Abstract: A control system, having an input command signal and driving a prime mover, is provided with variable magnitude and/or rate input signal limiting that is adjusted by maps 68,70,72,74 which set the limits for a variable magnitude limiter 14 and a variable rate limiter 22 as a function of the prime mover rate. The limiting is adjusted dynamically as the prime mover rate changes. When the prime mover enters an undesirable operating condition, the maps only limit the command signal in the direction of such condition. The adjustable limiting is enabled or disabled based on the position, rate, and/or acceleration of the prime mover.

公开(公告)号：AU657157B2

公开(公告)日：1995-03-02

申请号：AU2323592

申请日：1992-07-09

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ADAMS DONALD L JR ,  WRIGHT STUART C ,  VERZELLA DAVID J ,  LAMONTAGNE TROY J

IPC: B64C27/57 ,  G05B5/01 ,  G05B13/02 ,  G05D1/00

Abstract: A control system, having an input command signal and driving a prime mover, is provided with variable magnitude and/or rate input signal limiting that is adjusted by maps 68,70,72,74 which set the limits for a variable magnitude limiter 14 and a variable rate limiter 22 as a function of the prime mover rate. The limiting is adjusted dynamically as the prime mover rate changes. When the prime mover enters an undesirable operating condition, the maps only limit the command signal in the direction of such condition. The adjustable limiting is enabled or disabled based on the position, rate, and/or acceleration of the prime mover.

公开(公告)号：IT8420762D0

公开(公告)日：1984-05-02

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：ES2083752T3

公开(公告)日：1996-04-16

申请号：ES92915770

申请日：1992-07-09

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ADAMS DONALD L JR ,  WRIGHT STUART C ,  VERZELLA DAVID J ,  LAMONTAGNE TROY J

IPC: G05B5/01 ,  B64C27/57 ,  G05B13/02 ,  G05D1/00

Abstract: A control system, having an input command signal and driving a prime mover, is provided with variable magnitude and/or rate input signal limiting that is adjusted by maps 68,70,72,74 which set the limits for a variable magnitude limiter 14 and a variable rate limiter 22 as a function of the prime mover rate. The limiting is adjusted dynamically as the prime mover rate changes. When the prime mover enters an undesirable operating condition, the maps only limit the command signal in the direction of such condition. The adjustable limiting is enabled or disabled based on the position, rate, and/or acceleration of the prime mover.

公开(公告)号：CA1091213A

公开(公告)日：1980-12-09

申请号：CA297067

申请日：1978-02-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： JOHNSON RAYMOND G JR ,  COTTON LOUIS S ,  VERZELLA DAVID J

IPC: B64C27/06 ,  G05D1/08 ,  B64C11/44

Abstract: VARIABLE INCIDENCE HELICOPTER STABILATOR AND FAIL SAFE ACTUATOR A helicopter stabilator, combining the functions of tail stabilizer and aircraft elevator, has its angle of incidence with respect to the helicopter controlled by means of a pair of reversible electric jack-screw type actuators acting in series, each being controlled in a closed-loop fashion by separate electronic hardware, the position of each as well as the rate of change thereof being compared with the other, the controls being disconnected when the actuators fail to track within a threshold disparity of either position or rate of change of position of each other, whereby catastrophic aerodynamic changes, which could otherwise occur from electronic or actuator failure, are avoided, but dynamic loads do not cause unnecessary failure indications. A test switch introduces an imbalance to test the fault circuitry. The stabilator is biased to assume a maximum incidence position so as to be insensitive to the substantially vertical component of main rotor downwash, at low speeds, including hover; and inputs from airspeed and collective pitch position cause it to assume a substantially level position at higher, cruise speeds, for maximum forward flight stability. A pitch rate gyro input controls the stabilator for stable flight against pitch-inducing flight commands and external effects, such as gusts. In one embodiment, the electronic controls are related to a canted tail rotor which not only provides directional stability, but also provides tail lift; to overcome tail-up and tail-down effects of the downward component of the tail rotor due to more or less thrust and real or apparent lateral accelerations, a lateral accelerometer is used. To avoid main rotor downwash against the stabilator at hover, the lateral accelerometer and collective pitch inputs are washedout at low speeds. The bias allows final adjustment for high speed flight. The invention disclosed herein was made under or in the course of a contract with the Department of the Army.