Patent ID: 7618007

Claim:
In combination with a pressure vessel which houses a combustion engine, an engine mounting system for mounting the pressure vessel to an aircraft structure, said engine mounting system comprising: a primary mounting system of vibration isolators that are mechanically connected between the pressure vessel and the aircraft structure to cushion and neutralize vibrations therebetween; a secondary mounting system including a pneumatic force balancing actuator which is mounted between the pressure vessel and aircraft structure to balance pressure differences therebetween, wherein said pneumatic force balancing actuator includes a cylinder which is mounted to the aircraft structure, and which has a hollow interior pneumatically connected to the exterior of an aircraft such that the cylinder maintains an internal pressure that equals an ambient pressure outside the aircraft; and a piston which is mounted within the cylinder and connected to the pressure vessel, said piston describing a cavity that is pneumatically connected to the aircraft's interior such that the aircraft's cabin pressure is a driving force on the piston such that the driving force of the piston and internal pressure of the cylinder cushions the pressure vessel with a differential pressure between the cabin pressure and the ambient pressure.