Design of Launch Vehicle Flight-Program-Adaptability Evaluation System Architecture

To solve the adaptability problem with multielement constrains in the early stages of launch vehicle plan argumentation, an architecture of launch vehicle flight-program-adaptability evaluation system based on multi-specialty cosimulation is proposed. Refinement simulation aiming at specific flight mission can be carried out on this simulation system which is integrated with simulation models of trajectory simulation model, engine simulation model, environment simulation model, aerodynamics simulation model, control system simulation model and other simulation models. Users can change the deviation values and flight mission with parameter configuration, and carry out simulations with Monte Carlo method. Based on evaluation rules and simulation results, the flight-program-adaptability can be evaluated in several ways such as control ability, flight load, thermal environment and carrying capacity, which provides data support for flight program optimization.