Patent ID: 9663235
Date: 2017-05-30
CPC Classifications: B64C,B64D,B64F,F16F,Y10T

Claim:
1. A helicopter engine mounting system for mounting an engine to an aircraft body supported in flight by a rotary wing system rotating with an operational rotating frequency (P) with a plurality of (N) rotating blades, said aircraft body having a persistent in flight operational rotating frequency vibration from said rotating blades, said engine mounting system including a top fluid chamber fluid engine mount and a bottom fluid chamber fluid engine mount, said top fluid chamber fluid engine mount having a bottom end for grounding to said aircraft body, and said bottom fluid chamber fluid engine mount having a bottom end for grounding to said aircraft body, said top fluid chamber fluid engine mount having a top fluid chamber distal from said top fluid chamber fluid engine mount bottom end, said bottom fluid chamber fluid engine mount having a bottom fluid chamber proximate said bottom fluid chamber fluid engine mount bottom end, an intermediate cradle with a lateral link, said lateral link having a first end for grounding to said aircraft body and a second distal end, said second distal end distal from said first end, said second distal end linked to said intermediate cradle, said top fluid chamber fluid engine mount bottom end grounded to said aircraft body, said bottom fluid chamber fluid engine mount bottom end grounded to said aircraft body, with said intermediate cradle disposed between said top fluid chamber fluid engine mount and said bottom fluid chamber fluid engine mount and said engine, with a fluid conduit connecting said top fluid chamber fluid engine mount top fluid chamber with said bottom fluid chamber fluid engine mount bottom fluid chamber wherein a transfer of said persistent in flight operational rotating frequency vibration from said aircraft body to said engine is inhibited.