Title:
ACTUATOR MECHANISM FOR CONTROLLING RUDDER FACE WITH VARIABLE TRANSMISSION RATIO
Document Type and Number:
Japanese Patent JPH01229798
Kind Code:
A
Abstract:
PURPOSE:To miniaturize and lighten while improve the durability of a servo actuator by providing the linking position variable means of an output rod to a link and making the operating angle ratio of a rudder face to a brake horse power variable. CONSTITUTION:As a servo actuator 12 is operated, a link 16 is tilted by means of an output shaft 12' and a controlling rudder face 10 is rotated centering around a hinge shaft 21 via a slotted hole 18, a slide pin 17, and a rod 19 to vary an operating steering angle. As a flying speed gets higher, the rod 19 of a motor-driven actuator 20 is tilted to the position of the imaginary line making the operating angle of the controlling rudder face 10 with respect to a brake horse power smaller. On the contrary, as the flying speed gets lower, the rod 19 is rotated to the position of the solid line, making the operating angle of the rudder face larger. In general, since aircraft has a large steering angle and small operating force at the time of low speed while having a small steering angle and large operating force at the time of high speed, the output of the servo actuator 12, particularly with respect to the maximum load at the time of the maximum speed, can be greatly reduced by such a structure.
Inventors:
OKADA TOYOHISA
TAKEUCHI YASURO
TAKEUCHI YASURO
Application Number:
JP5368588A
Publication Date:
September 13, 1989
Filing Date:
March 09, 1988
Export Citation:
Assignee:
SHIN MEIWA IND CO LTD
International Classes:
B64C13/24; (IPC1-7): B64C13/24
Attorney, Agent or Firm:
Yohei Kinoshita (1 person outside)
Previous Patent: SWITCH FOR CONTROLLING DRIVE UNIT OF SHIP ENGINE
Next Patent: METHOD OF MOUNTING DUCTED FAN GAS TURBINE ENGINE ON AIRCRAFT
Next Patent: METHOD OF MOUNTING DUCTED FAN GAS TURBINE ENGINE ON AIRCRAFT