Abstract: For a environment propellant group,the simulation model,mass model and orbit model of adjacent space aircraft were established.By setting combustion chamber pressure,ample oxygen coefficient and nozzle exit pressure as variables,the performance of adjacent space aircraft was analyzed.The results show that it will be better with higher combustion chamber pressure under specific task for improving adjacent space aircraft performance.The best ample oxygen coefficient can be achieved at 0.99.If permitted,the nozzle area expansion ratio deployed should be as big as possible,since it is limited by rocket outer diameter and technology level,etc.The correlation study could provide a guidance for the system project study of other similar adjacent space aircrafts.