Abstract: The special space exploration rocket is launched to rendezvous with the celestial body flying around earth, the absolute velocity of rocket should be zero at rendezvous time in order to satisfy the observe requirement. The ideal rendezvous orbit was designed before launch based on the orbit of the celestial body and launch site. The orbit parameters were loaded to onboard computer of rocket. After launch, the inertial navigation system was used to measure the rocket position and velocity, the thruster fire direction was adjusted try to eliminate the flight orbit errors. The several coordinated was defined and rocket orbit dynamical equation was created. The ideal rendezvous time, launch time and rendezvous point in space were studied. The trajectory control logic given during the thruster force is available. The error signal is decomposed into time error, altitude error, north-south error and east-west error in local horizontal frame. Position and velocity shift can be set to reduce the orbit drift caused by perturbation. The feasibility of control logic is verified by computer numerical simulation.