Abstract: In this research, the emergency rendezvous guidance strategy in manned Mars exploration mission is analyzed and designed, and the rapid rendezvous method between Mars landing module and spacecraft when the mission is terminated during landing is mainly discussed. Firstly, the orbit transformation process of Mars landing phase is simplified. When the mission is terminated, according to the initial phase of the landing module and the spacecraft, the height of the far point of the Mars phase-modulated orbit is determined by the special point orbit change strategy. After the phase-modulation of the landing mudole is completed, it enters the circular orbit around the Mars. Then the terminal aiming point of far-range rendezvous is designed based on CW equation. The final far-range rendezvous is realized based on the guidance strategy of the near-circular deviation equation. Finally, the proposed emergency rendezvous strategy is verified by simulation. The simulation results show that the designed emergency rendezvous guidance strategy can effectively complete the rapid rendezvous and docking between the Mars landing module and the spacecraft during the emergency rendezvous of Hohmann descent and power descent.