This paper establishes a rotor/fuselage coupling dynamic model for the inverted configuration of the blade tip. Based on the full-size BO-105 rotor blade, the changes in the heading, lateral, and vertical vibration loads of the hub and the vibration characteristics of the fuselage within the range of 0–20 ° of the inverted blade tip were analyzed. The research shows that the inverted blade tip changes the total pitch, periodic pitch, and fuselage pitch angle. The inverted blade tip at a small angle does not significantly affect the hub vibration load and fuselage vibration, while the inverted blade tip at a larger angle will increase the high-order harmonic vibration loads of the hub heading, lateral, and vertical, thereby causing an increase in fuselage vibration.