Design and optimization of booster gliding model guided rocket scheme

Abstract

In order to meet the needs of rocket innovation practice learning that takes into account both low-cost and high-level engineering practical training, the design of flight mission of the model guided rocket is proposed and the technical index analysis is carried out in the present study. The design of the rocket thrust system is completed using two paralleled YSR-32 motor, whose total engine impulse is 296.14\U0001d475 ∙ \U0001d494; The mathematical model of the integrated aerodynamic / ballistic design optimization problem of rocket is constructed, adopting the aerodynamic configuration of side strip wing and x-shaped tail rudder and using Boost-Glide trajectory. Take the farthest range as the objective function, the influence of 8 variables on it is analyzed; By using Astrolab, a rapid overall design optimization platform of the rocket, the integrated simulation process of the aerodynamic / ballistic performance of the rocket is established; The maximum range of the optimization results is 1.29 \U0001d48c\U0001d48e, the takeoff mass is 2.8 \U0001d48c\U0001d488, the speed at the shutdown point is 93.6 \U0001d48e/\U0001d494, and the maximum flight time is 28.4s; The single use cost of the guided rocket is not exceed 1300 yuan.