To approach close to the Sun, direct launch from the Earth costs a lot of energy, which can be effectively reduced by the gravity assist of the Venus. In this paper, interplanetary transfer trajectories with multiple resonant gravity assists of the Venus are designed for a solar approaching detection mission. And design models for the trajectories with continuous resonant gravity assists, as well as resonant and non-resonant gravity assists combined are built. A mission launched between 2025 and 2028 is studied. The study shows that, compared with trajectory with continuous resonant gravity assists, trajectory with resonant and non-resonant gravity assists combined is useful for reducing transfer time of solar approaching detection mission. And its impact on the energy cost is not universal, which is related to the resonance ratio in the trajectory.