Forward engine mount with converging links

An aircraft comprising:

• a fuselage;
• a wing attached to the fuselage;
• a pylon having a rigid structure attached to an underside of the wing;
• and
• a propulsion assembly attached to the rigid structure, the propulsion assembly comprising:
• an engine having a propeller with a center of thrust, a fan casing, and a core casing aft of the fan casing;
• a forward engine mount coupled to the rigid structure and the engine, the forward engine mount having a longitudinal axis that intersects with the center of thrust of the engine, the forward engine mount further including at least two two-point shackles coupled to a frontal wall of the rigid structure;
• an intermediate engine mount including at least two thrust links coupled to the rigid structure aft of the forward engine mount and coupled to the engine aft of the forward engine mount at a rear portion of the fan casing, the intermediate engine mount having a longitudinal axis that intersects with the center of thrust, wherein the longitudinal axis of the forward engine mount and the longitudinal axis of the intermediate engine mount intersect at the center of thrust;
• and
• a rear engine mount coupled to the rigid structure and the engine aft of the intermediate engine mount;
• wherein the forward engine mount, the intermediate engine mount, and the rear engine mount are separated from each other by at least a portion of the rigid structure in a longitudinal direction of the rigid structure;
• wherein an orientation of the at least two two-point shackles of the forward engine mount in relation to the rigid structure and the engine is selected from a list consisting of:
• a first orientation where the at least two two-point shackles of the forward engine mount are arranged to direct a load distribution through a center point of the rigid structure;
• a second orientation where the at least two two-point shackles of the forward engine mount are arranged to direct the load distribution through an upper-most point of the engine;
• a third orientation where the at least two two-point shackles of the forward engine mount are arranged to direct the load distribution through an intermediate point of the engine in between an upper-most point of the engine and a centerline of the engine;
• or
• a fourth orientation where the at least two two-point shackles of the forward engine mount are arranged to direct the load distribution through the centerline of the engine;
• wherein the at least two thrust links of the intermediate engine mount are coupled to the rigid structure via an intermediate fastener, the intermediate fastener coupled to the underside wall of the rigid structure;
• wherein the rear engine mount includes a two-point shackle and a three-point shackle oriented on opposite sides of the centerline of the engine and coupled to the underside wall of the rigid structure aft of the intermediate engine mount;
• and
• wherein the engine mounting system is configured to provide a six degrees-of-freedom pylon interface, two degrees-of-freedom attributable to the forward engine mount in Y-Z directions, one degree-of-freedom attributable to the at least two thrust links in an X direction, and three degrees-of-freedom attributable to the rear engine mount in Mx-My-Mz directions.