Title:
INDIVIDUAL BLADE CONTROL SYSTEM FOR HELICOPTERS
Document Type and Number:
WIPO Patent Application WO1990008063
Kind Code:
A3
Abstract:
A control system for providing individual blade control inputs to a four-bladed helicopter rotor. Limited authority series actuators located in a non-rotating portion of the helicopter are driven by a computer which receives inputs from individual blade sensors and aircraft stabilization sensors, summed with cockpit control inputs, and the resultant motions transmitted to the rotor blades through a conventional swashplate which drives four blades of the rotor and a translatable differential sleeve and summing linkage which drives only two blades. The differential sleeve is adapted for axially raising or lowering the swashplate. The combined motion of swashplate and differential sleeve is shown mathematically to result in individual blade control in pitch. Computer individual blade commands are converted from the rotating reference frame to cyclic, collective and differential blade pitch commands in the fixed reference frame through a coordinate transformation matrix.
Inventors:
GRIFFITH CARL D (US)
Application Number:
PCT/US1989/005807
Publication Date:
October 18, 1990
Filing Date:
December 22, 1989
Export Citation:
Assignee:
HONEYWELL INC (US)
International Classes:
B64C27/605; B64C27/72; (IPC1-7): B64C/
Foreign References:
| US4227856A | 1980-10-14 | |||
| US3144908A | 1964-08-18 | |||
| US3102597A | 1963-09-03 | |||
| DE2736409A1 | 1979-02-22 |
Download PDF: