Flight Parameters Design of Launch Vehicle Based on Differential Genetic Combinatorial Optimization Method

To achieve a fast scheme selection for the launch vehicle, the flight parameters design method is investigated in this paper. To address the coexistence of continuous and discrete variables in the optimization of the flight parameters of the launch vehicle, a differential genetic combinatorial optimization method is proposed to optimize the flight design parameters. In the method, an adaptive crossover probability calculation based on a differential genetic algorithm is developed for multimodal features, and a suitable differentiation procedure for discrete variables is proposed in the optimization of the flight parameters of the launch vehicle. Nine benchmark functions from IEEE CEC2017 are used to validate the applicability of the proposed method, demonstrating the superiority of the proposed method on multimodal problems. Finally, the minimum take-off mass objective problem is formulated and solved to validate the effectiveness of the proposed method in the design of the flight parameters of the launch vehicle. The work of this paper has reference significance for the scheme selection and conceptual design of launch vehicle.