| 摘要 |
PURPOSE: To reduce the propagation of vibration to an airframe by constituting this device for mounting an engine to the airfram of aircraft by installing a strut extending between the engine and the air frame and a clamper lying between this strut and the airframe. CONSTITUTION: When a non-ducted fan engine 4 for an aircraft, having a first set 8 of a propeller blade being radialy rotated, and a second likewise set 10 rotating in the opposite direction are mounted at both sides of an tail-unit empennage section 2 of a fuselage 6, a mounting strut 22 consisting of a plurality of mounting beams 12, 14, 16, both inboard and outboard closing ribs 18, 20, and both upper and lower outer panels 21, is installed therein. Then a thrust damping element 26 for the inboard closing ribs 18 to a fuselage outer plate 28 is installed in this rib 18. In addition, the front beam 12 is mounted to a fuselage frame member 36 by two viscous damping elements 38, 40 and elastomer clampers 39 and 41, while the rear beam 16 is mounted to a fuselage frame member 46 by two viscous damping elements 48, 50 and elastomer dampers 49 and 51 as well.
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