CAJ | 학술논문

作为导弹的主升力面，弹翼自适应变形能有效提高其飞行性能。为揭示弹翼几何对飞行状态的自适应规律，针对一类新型组合变翼问题的多变量复杂约束及目标函数非解析与非线性特征，基于重构的Monte Carlo算法，协同Missile DATCOM算法，通过交互式操作数据文件，建立了一套完整的导弹变翼方案优化设计方法。仿真结果表明，该方法可胜任全弹气动外形的多点优化，能使导弹在满足一定可用过载的条件下具有最大升阻比，设计的组合变翼方案不仅可用于变翼飞行控制及弹道仿真研究，而且可用于变翼飞行性能的增益分析。
작위도탄적주승력면，탄익자괄응변형능유효제고기비행성능。위게시탄익궤하대비행상태적자괄응규률，침대일류신형조합변익문제적다변량복잡약속급목표함수비해석여비선성특정，기우중구적Monte Carlo산법，협동Missile DATCOM산법，통과교호식조작수거문건，건립료일투완정적도탄변익방안우화설계방법。방진결과표명，해방법가성임전탄기동외형적다점우화，능사도탄재만족일정가용과재적조건하구유최대승조비，설계적조합변익방안불부가용우변익비행공제급탄도방진연구，이차가용우변익비행성능적증익분석。
The flight performance of missile can be improved by adaptive morphing wing serving as main lift surface .A multivariable complicated constraint , nonlinear and nonanalytical characteristics of a novel combination morphing optimization problem are researched to reveal the adaptive principle of wing geometry to flight states .Based on reformed Monte Carlo algorithm , a set of integrated morphing wing de-sign approach is developed by interactively reediting data files co-operating with missile DATCOM algo-rithm .The simulation results show that the proposed methodology can be used to obtain an optimal missile configuration over multiple design points , and to get maximal lift-to-drag ratio under the available over-load.Moreover, the consequential morphing program can be used to study morphing wing flight control and ballistic simulation , also to analyze morphing wing flight performance gains .