Distant retrograde orbits (DROs) have gained significant attention in recent years due to their unique orbital characteristics and stability. Resonant orbits also offer considerable value for space situational awareness and navigation missions in the cislunar space. However, researches on transfer orbits between these two types of orbits remain relatively insufficient. To address this issue, this paper proposes a design method for transfers between DRO and resonant orbits with arbitrary resonance ratios in the Earth-Moon circular restricted three-body problem (CRTBP). The proposed method is validated by designing transfer orbits for a range of resonant orbits with selected resonance ratios, and the effectiveness of the method is demonstrated through numerical computation. The method is applicable for the design of transfer orbits for different resonant orbits, and a transfer orbit database is established, providing theoretical and data support for the rapid design of transfer orbits in the future. Finally, we investigate the characteristics of transfer orbits, including fuel consumption and flight time. The results of this research contribute to the effective development of the Earth-Moon system.