Abstract: To launch a lunar probe is a multi-celestial body problem, and also a strict orbit rendezvous problem. Many launch trajectory plans can be obtained theoretically, but selctions are strictly limited for enginnering applications with many constarints, such as launch capacity, launch site, telemetry and control conditions etc. The most conventional method is to transfer from the parking orbit with finite thrust. This paper takes a typical launch vehicle as an example, the Earth-lunar transfer scheme with constraints are analyzed and studied.