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建立了无人机折叠尾翼展开机构的动力学模型,计算得到折叠尾翼展开的运动规律。根据折叠尾翼展开机构的设计要求及扭簧的设计准则,建立驱动扭簧参数的优化模型。采用模拟退火算法,用Visual Basic语言编制计算程序求解得到扭簧的优化参数。建立了折叠尾翼的有限元模型,针对优化前后的扭簧参数分别进行了数值模拟计算,结果表明:优化后的参数能够让折叠尾翼在满足设计要求的时间内展开到位,而冲击载荷只有原方案的23.2%。
The dynamics model of the unfolding mechanism of the folded tail of the UAV is established, and the law of the movement of the folded tail is calculated. According to the design requirements of the folding tail expansion mechanism and the design criteria of the torsion spring, the optimal model of the torsion spring parameters is established. Using simulated annealing algorithm, using Visual Basic language programming to solve the torsion spring optimization parameters obtained. The finite element model of the folded tail is established. The torsional spring parameters before and after optimization are respectively numerically simulated. The results show that the optimized parameters can make the tail of the folded tail to meet the design requirements, while the impact load is only the original program Of the 23.2%.