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.