United Trajectory Design Method for Return to Launch Site of Suborbital Reusable Launch Vehicle

摘要

A kind of suborbital reusable launch vehicle requiring return to launch site is in research recently. This paper mainly studies the return scheme and proposed a united trajectory design method for this kind of winged vehicle. The trajectory contains a trajectory rotation phase using forward integral and a re-entry phase using backward integral. The former phase begins at the staging point and ends at the highest point of the trajectory. From this point to the landing site is the latter phase. The flight direction is reversed to launch site along with the attitude and the velocity adjustment in the first phase using continuous thrust, then a special re-entry trajectory without thrust is presented. This paper presents a detailed description of the proposed method and the backward integral is analyzed through mathematics deduction. A comparative analysis quantifies the correctness and advantages of this integral method. As concluding remarks, this trajectory design method is simple and reliable enough to conduct a return to launch site recovery.