Performance Analysis on the Small-Scale Reusable Launch Vehicle

According to the symmetrical characteristics of a new type Reusable Launch Vehicle (RLV) in recovery phase, we studied basic aerodynamic model data Starship and with rudder deflection, causes its coefficients are expounded. At same time, analyzed stability maneuverability. flying quality requirements, lateral-directional return phase at high angle attack is analyzed. Finally, lateral heading control deviation by using criterion nonlinear open-loop simulations. The results show that has pitching rolling stability, but it only some ranges attack, there no conventional large attack. after modal analysis comparison flight quality, can be seen longitudinal long-period starship degenerates into real root stable convergent. roll mode level 2 helical 1 Dutch diverges, which needs stabilized controlled later.