The present invention relates to a non-co-axial multi-rotor aircraft, which comprises an aircraft body, a power system, a transmission system, a flying control system, and 2N rotor components, wherein N is more than or equal to 2, the power system drives the rotor component to rotate through the transmission system, the flying control system controls the power system to work, every rotor component comprises a rotor and a blade pitch driving mechanism for changing a rotor blade pitch, the flying control system is provided for controlling works of every blade pitch driving mechanism, the transmission system comprises N forward direction transmission mechanisms and N reverse direction transmission mechanisms, the forward direction transmission mechanisms and the reverse direction transmission mechanisms are sequentially and staggedly distributed, and the power system drives the rotors of the N rotor components to rotate along the same direction through the N forward direction transmission mechanisms. With the present invention, technical problems of single driving manner, low aircraft load, short flying time and the like due to application of rotor rotation speed changing to control an aircraft attitude by the existing multi-rotor aircraft are solved.