Abstract: A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation. An outer nacelle surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle is formed with camber so as to be curved in a first plane away from the axis of rotation in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction. An aircraft is also disclosed.

Abstract: A vehicle controllable and smooth ride system with sprung weight comparable to or less than the unsprung weight is provided by a cantilevered connection between the front and rear unsprung weight and near horizontal arrangement of suspension devices in the sprung weight of the vehicle so verticle motion of the front and rear unsprung weight is transmitted to the sprung weight while the entire sprung weight is applied to each front and rear unsprung weight motions.