Analysis of vertical landing technique in reusable launch vehicle

Based on the vertical ascent and descent technique tests by the SpaceX corporation, the application value of two types of descent methods for launch vehicles is compared and analyzed. To this end, the first stage dynamics model of the launch vehicle is formulated for return trajectory. Then, a H-V profile based sectional return trajectory design method is proposed, and considering the propellant coupling effect of the ascent phase and the descent phase, an integrated trajectory optimization design strategy is synthesized for two vertical return ways including return to the launch site (RTLS) and not return to the launch site (NRTLS). Finally, numerical simulation is given to compare the launch capacity of two descent methods, and it is concluded that the NRTLS method costs less launch capacity and shows better practicability.