新型着陆器单腿动力学仿真模型碰撞参数修正  

Collision parameters updating for single-leg dynamic simulation model of a novel lander

作　　者：吴宏宇[1] 王春洁[1,2] 丁建中 王巨涛[1] 满剑锋[3] 罗敏[3] WU Hongyu;WANG Chunjie;DING Jianzhong;WANG Jutao;MAN Jianfeng;LUO Min(School of Mechanical Engineering and Automation, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;State Key Lab of Virtual Reality and Systems, Beijing 100191, China;Beijing Institute of Spacecraft System Engineering, Beijing 100094, China)

机构地区：[1]北京航空航天大学机械工程及自动化学院,北京100191 [2]虚拟现实技术与系统国家重点实验室,北京100191 [3]北京空间飞行器总体设计部,北京100094

出　　处：《振动与冲击》2018年第5期50-55,64,共7页Journal of Vibration and Shock

摘　　要：建立新型着陆器的单腿动力学仿真模型,着陆器与着陆面的碰撞采用非线性阻尼弹簧模型模拟。出于提高仿真模型计算结果准确性的目的,参照装有单套着陆缓冲机构的着陆器物理样机的冲击试验结果,对非线性阻尼弹簧碰撞模型中的刚度系数、阻尼系数和非线性指数进行修正。为了提高模型修正的计算效率,构造出能准确反映仿真结果相对于试验结果误差值的Kriging代理模型,并应用第二代非劣排序遗传算法(NSGA-Ⅱ),以最小化Kriging代理模型计算出的误差值作为目标,实现非线性阻尼弹簧碰撞模型的参数修正。将修正后的参数代入仿真模型进行验证,相比于冲击试验结果,新模型计算出的着陆器主体下降距离与投放高度之差误差由修正前的29.4%降低到5.9%,辅助支柱最大缓冲行程误差由修正前的24.7%降低到8.4%。Single-leg dynamic simulation model of a novel lander was established,and the collision between lander and landing surface was simulated with a nonlinear spring-damper model.In order to improve the simulation accuracy of the model,its stiffness coefficient,damping coefficient and nonlinear exponent were taken as collision parameters and updated based on impact test results of the physical prototype of a lander with a single set of landing buffer.For improving the calculating efficiency,Kriging surrogate model was established to correctly describe the error between simulation results and test results.Then collision parameters were updated using the non-dominated sorting genetic algorithm II and taking minimizing the error calculated with Kriging model as an objective.The modified parameters were substituted into the simulation model to do a new simulation.Comparing calculation results of the simulation model before and after parametric updating,it was shown that compared with the impact test results,the lander’s main body falling distance error is reduced from19.2%before parametric updating to5.9%after that,the lander’s jury strut maximum buffering stroke error is reduced from24.7%before parametric updating to8.4%after that.

关 键 词：腿式着陆器 动力学分析 模型修正 Kriging代理模型 多目标优化 

分 类 号：H113[语言文字—汉语]