A ballistic optimization method for quasi equilibrium flight segment of high mach number aircrafts

DOI:	10.11809/bqzbgcxb2023.09.029
Keywords:	high mach number aircrafts; quasi equilibrium flight segment; ballistic optimization; improved direct shooting method; adaptive genetic algorithm; the fourth order Ronge Kutta method; multi no fly zone
Abstract:	A hybrid optimization solution based on improved direct shooting method and adaptive genetic algorithm is proposed for the class HTV aircraft quasi equilibrium flight segment ballistic optimization. Firstly, the control variable data set is constructed within the control constraint range, and the initial and terminal moments of the control variable value and the terminal time are incorporated into the optimal design variables. Then, the improved direct shooting method is used to make the dynamic optimal control that satisfies the control constraint, process constraints (dynamic pressure, overload, heat flow rate, no fly zone, and others) and terminal constraint with the longest range as the objective function. The problem is parameterized as a nonlinear programming problem. On this basis, the global optimization of the control parameters is performed by an adaptive genetic algorithm, and the control variable time history is smoothed by three sample interpolation, and the fourth order Ronge Kutta method is used for numerical integration to obtain the ideal ballistic path. The proposed ballistic optimization algorithm is verified that it has faster convergence speed and better performance than the original algorithm (direct shooting method genetic algorithm). Moreover, the proposed algorithm reduces sensitivity to initial valuations, and certain robustness, which can avoid multiple no fly zones and achieve the ideal trajectory that satisfies the constraints and guarantees the longest range.
Issue:	Vol. 44 No. 9 (2023)
Published:	2023-09-28
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