| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a steering device for an aircraft, capable of attaining size reduction and stable operation of a steering angle ratio variable mechanism. <P>SOLUTION: The steering device 1 for an aircraft includes an input crank 6 connected with a control stick through a first connecting mechanism and an output crank 7 connected with an elevator through a second connecting mechanism. Both the cranks 6, 7 are rotatably disposed around the identical crank center C1. The steering angle ratio variable mechanism 25 includes a cylindrical input shaft 28 rotatable integrally with the input crank 6; an output shaft 29 rotatable integrally with the output crank 7; and a wave gear mechanism 30 connected so as to differentially rotate both the shafts 28, 29. In such a state where the center lines of the input shaft 28 and the output shaft 29 coincide with the crank center C1, the output shaft 29 is inserted into the input shaft 28. <P>COPYRIGHT: (C)2012,JPO&INPIT |
