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：CA1081830A

公开(公告)日：1980-07-15

申请号：CA271669

申请日：1977-02-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MURPHY RICHARD D ,  COTTON LOU S

IPC: B64C27/57 ,  G05D1/10 ,  G05D1/00

Abstract: In a helicopter having an automatic pilot system for controlling the main rotor collective pitch, main rotor longitudinal and lateral cyclic pitch, and tail rotor collective pitch, in response to inputs provided from normal sensors, navigational instruments and controls,(which include a among others is known, doppler radar, a pilot panel, an air speed indicator, a radar altimeter. a barometric altimeter and a longitudinal accelerometer). commands to control automatic approach to a desired hover position are provided to the autopilot system in response to signals normally supplied by a TACNAV unit as well as the sensors, navigational units and controls; controls are provided for altitude and rate of descent, so as to terminate in hover at a desired altitude, as well as for turns, courses, and speed so as to approach the desired point of hover upwind and to decelerate in a controlled fashion to hover.

公开(公告)号：CA1085368A

公开(公告)日：1980-09-09

申请号：CA300455

申请日：1978-04-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TEFFT FRANKLIN A ,  ADAMS DON L ,  COTTON LOU S

IPC: B64C27/58 ,  B64C27/54 ,  B64C27/56 ,  G05D1/08 ,  B64C11/34

Abstract: HELICOPTER PITCH RATE FEEDBACK BIAS FOR PITCH AXIS MANEUVERING STABILITY AND LOAD FEEL The longitudinal cyclic pitch channel of a helicopter has a negative pitch rate feedback bias added thereto when flying at higher speeds, thereby to stabilize the pitch axis against aft-load maneuvering instability and/or to induce a requirement for the pilot to provide a countermanding longitudinal cyclic pitch input through his cyclic pitch stick, the normal feel force of which provides an indication to him of the loading of the rotor as a consequence of undergoing pitch rate maneuvers.