Design and development of simulation software for two-body separation calculation considering complicated factors

A method was proposed for the design and realization of two-body simulation software which could calculate and analyze a variety of space launch vehicle separation movement of the two-body types. The outer loads were added according to the user's choice. It has the characteristics of wide range of applications and strong flexibility. According to the motion states of the combination of input, the mass characteristics of the separation bodies and outer load changes, using integral calculation, a trajectory curves was obtained. The software also has the function of inferring the outer load changes based on the movement curves. The function can demonstrate the correctness of the software. The simulation time, the integration step, output step size and separation of specific points can be set. The fourth-order Runge-Kutta method was used for integration computing. This separation process of the monomer fairing and the stages were simulated and analyzed, considering the aerodynamic, the separation rocket thrust, the main stage rocket thrust and other factors. The movement regularity of the fairing and the rocket was obtained after being calculated.