Abstract: Shocked-flow-field inverse design technology plays an important role in the design of hypersonic waverider vehicles. A novel design method based on the theory of three-dimensional characteristic lines is developed to overcome the defects of the conventional osculating method in designing three-dimensional shocked flow fields. In this method, a basic cell including four Mach lines and one streamline is constructed, then the corresponding front advancing and parallelization methods are developed. A new set of governing equations are obtained by decomposing the differential operators of the Euler equations, and the Tikhonov-Lagrange curve fitting method is proposed to obtain the corresponding stable solution. Four examples are used to test the numerical stability and accuracy of the method, including the conical shocked flow field, the elliptical shocked flow field, the conical shocked flow field with a small angle of attack, and the shocked flow field with a general shock shape described by the Bezier surface. The results show that the present method has a good performance in predicting the three-dimensional flow effects induced by the transverse pressure gradient and the angle of attack. Compared to the numerical simulation results, the errors of the wall pressure and Mach number distributions are less than 0.3% and 1.7%, respectively, and a high parallelization efficiency is also achieved. The proposed method extends the application of the theory of characteristic lines in the design of three-dimensional shocked flow fields, and has an important development prospect in the design of hypersonic waverider vehicles.