Integrated controller applied to aircraft and aircraft

The embodiment of the invention provides an integrated controller applied to an aircraft and the aircraft, and the integrated controller comprises: a shell, wherein an air inlet is formed in the firstend face of the shell, an air outlet is formed in the second end face opposite to the first end face and a fan is arranged at the air outlet; a plurality of functional modules which are arranged in the shell, wherein the functional modules are arranged in the shell from outside to inside according to the sequence of the heating values from large to small, and the heating surface of the functionalmodule on the outermost side faces the shell; and a phase change heat dissipation module which is arranged on the shell and is tightly attached to the outer surface of the shell. According to the integrated controller applied to the aircraft and the aircraft provided by the embodiment of the invention, the heat dissipation rate can be improved. 本申请实施例提供一种应用于飞行器的集成化控制器及飞行器，其中，集成化控制器包括：壳体；所述壳体的第一端面设有入风口，与第一端面相对的第二端面设有出风口；所述