Title:
【発明の名称】ロータクラフトのピッチ軸制御飽和に対する補償装置
Document Type and Number:
Japanese Patent JP2001526997
Kind Code:
A
Abstract:
A control system for small unmanned rotorcraft compensates for vehicle pitch control saturation caused by the need for sudden vehicle pitch attitude correction, in turn often caused by wind gusts. The rotorcraft has a pitch-variable rotor system responsive to a vehicle pitch servo command for cyclically controlling rotor pitch and responsive to a collective servo command for collectively controlling rotor pitch. A compensating signal derived from the unlimited vehicle pitch servo command signal is cross-connected to the unlimited collective servo command signal to compensate for pitch control saturation, typically by reducing the magnitude of the resulting collective servo command signal. The compensating signal is derived by passing the unlimited vehicle pitch servo command signal through a dead band which responds as the signal approaches saturation and by preferably also then providing high and low frequency shaping to that signal.
Inventors:
Gold, Philip Jay.
Doris Cole, Joseph Tea.
Doris Cole, Joseph Tea.
Application Number:
JP2000525799A
Publication Date:
December 25, 2001
Filing Date:
December 04, 1998
Export Citation:
Assignee:
Sikorsky Aircraft Corporation
International Classes:
B64C27/20; B64C13/16; B64C13/20; B64C39/02; G05D1/00; G05D1/06; G05D1/08; (IPC1-7): B64C27/20; B64C13/16; B64C13/20; B64C39/02
Attorney, Agent or Firm:
Fujiya Shiga (2 outside)