Abstract
The design of mini-missiles(MMs)presents several novel challenges.The stringent mission requirement to reach a target with a certain precision imposes a high guidance preci-sion.The miniaturization of the size of MMs makes the design of the guidance,navigation,and control(GNC)have a larger-than-before impact on the main-body design(shape,motor,and lay-out design)and its design objective,i.e.,flight performance.Pur-suing a trade-off between flight performance and guidance pre-cision,all the relevant interactions have to be accounted for in the design of the main body and the GNC system.Herein,a multi-objective and multidisciplinary design optimization(MDO)is proposed.Disciplines pertinent to motor,aerodynamics,lay-out,trajectory,flight dynamics,control,and guidance are included in the proposed MDO framework.The optimization problem seeks to maximize the range and minimize the gui-dance error.The problem is solved by using the nondominated sorting genetic algorithm Ⅱ.An optimum design that balances a longer range with a smaller guidance error is obtained.Finally,lessons learned about the design of the MM and insights into the trade-off between flight performance and guidance precision are given by comparing the optimum design to a design provided by the traditional approach.
NETL
NSTL
维普
万方数据