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作 者:于航 关永亮 侯燚红 陈善搏 YU Hang;GUNA Yong-liang;HOU Yi-hong;CHEN Shan-bo(Chang Guang Satellite Technology Co.,Ltd,Changchun Jilin 130052,China)
机构地区:[1]长光卫星技术股份有限公司,吉林长春130052
出 处:《计算机仿真》2025年第1期36-41,154,共7页Computer Simulation
基 金:吉林省科技发展计划项目(20210508038RQ)。
摘 要:为获取航天器碰撞结构的非线性模态特性,对碰撞结构的非线性模态特性分析方法进行研究。首先,根据Jankowski阻尼系数、非线性Hertz刚度与Jankowski冲击理论建立碰撞结构的非线性动力学模型。接着,采用无阻尼自治系统方法对非线性模态方程进行转换,依据改进的Newton打靶法非线性模态的求解方程。然后,分析航天器碰撞结构在动力学载荷下出现的两种分离-碰撞情况,将碰撞结构进行有限元离散,并计算非线性模态。最后,采用扫频试验验证分析计算结果的准确性。将非线性模态分析结果、线性模态分析结果与扫频试验结果进行对比,非线性模态分析前三阶模态误差分别为2.10%,1.43%,3.18%。对比结果说明非线性模态建模求解方法具有足够的准确性,能够满足航天器碰撞结构的分析要求。In order to obtain the nonlinear modal characteristics of the spacecraft crash structure,the analysis method of the nonlinear modal characteristics of the crash structure was studied.Firstly,the nonlinear dynamic model of the crash structure was established according to Jankowski damping coefficient,Hertz nonlinear stiffness and Jankowski impact theory.Secondly,the nonlinear modal equations were transformed by the undamped autonomous system method,and the nonlinear equations were solved according to the improved Newton shooting method.Then,two separation-impact situations of the spacecraft crash structure under dynamic loads were analyzed.The crash structure was subjected to finite element discretization,and the nonlinear modes were calculated.Finally,the swept-frequency test was used to verify the accuracy of the analysis method and results.Comparing the nonlinear modal analysis results and linear modal analysis result with the swept-frequency test results,the first three-order modal errors of nonlinear modal analysis result were 2.10%,1.43%,and 3.18%,respectively.The results show nonlinear modal analysis method has sufficient accuracy to meet the analysis requirements of spacecraft crash structures.
分 类 号:V414.1[航空宇航科学与技术—航空宇航推进理论与工程] V416.2
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