Optimization of the Conceptual Design of a Multistage Rocket Launcher

Abstract

The design of a vehicle launch comprises many factors, including the optimization of the climb path and the distribution of the mass in stages. The optimization process has been addressed historically from different points of view, using proprietary software solutions to obtain an ideal mass distribution among stages. In this research, we propose software for the separate optimization of the trajectory of a launch rocket, maximizing the payload weight and the global design, while varying the power plant selection. The launch is mathematically modeled considering its propulsive, gravitational, and aerodynamical aspects. The ascent trajectory is optimized by discretizing the trajectory using structural and physical constraints, and the design accounts for the mass and power plant of each stage. The optimization algorithm is checked against various real rockets and other modeling algorithms, obtaining differences of up to 9%.

Comparison of Optimization Techniques and Objective Functions Using Gas Generator and Staged Combustion LPRE Cycles

“…A fuzzy Multi-Objective GA (MOGA) technique has been applied to a GG cycle [17] as well as on a hybrid rocket [18] with the objectives of maximizing altitude and minimizing Gross Lift-Off Weight (GLOW). Orgeira-Crespo et al [19] compiled a database of existing LPREs and examined conceptual multistage LVs based on those existing engines. A GA technique was used on these conceptual LVs to optimize the GLOW based on different trajectories.…”

“…When determining GLOW for an LV, according to the best of our investigations, researchers, apart from [19], used mass models based on MERs to provide estimates for the masses. While minimizing GLOW and maximizing payload have been used as Objective Functions (OFs), to the best of our knowledge, other OFs such as maximizing I sp or Thrustto-Weight ratio (T/W) have not been investigated.…”