形状记忆合金自复位减振装置研制与验证
2024,46(3):105-115
麻越垠
国防科技大学 空天科学学院, 湖南 长沙 410073;
空天任务智能规划与仿真湖南省重点实验室, 湖南 长沙 410073;
中国空气动力研究与发展中心 设备设计及测试技术研究所, 四川 绵阳 621000，mayueyin@cardc.cn
李道奎
国防科技大学 空天科学学院, 湖南 长沙 410073;
空天任务智能规划与仿真湖南省重点实验室, 湖南 长沙 410073
聂旭涛
中国空气动力研究与发展中心 设备设计及测试技术研究所, 四川 绵阳 621000
张伟
国防科技大学 空天科学学院, 湖南 长沙 410073;
中国空气动力研究与发展中心 设备设计及测试技术研究所, 四川 绵阳 621000
高鑫宇
中国空气动力研究与发展中心 设备设计及测试技术研究所, 四川 绵阳 621000
陈万华
中国空气动力研究与发展中心 设备设计及测试技术研究所, 四川 绵阳 621000
陈振华
中国空气动力研究与发展中心 设备设计及测试技术研究所, 四川 绵阳 621000
国防科技大学 空天科学学院, 湖南 长沙 410073;
空天任务智能规划与仿真湖南省重点实验室, 湖南 长沙 410073;
中国空气动力研究与发展中心 设备设计及测试技术研究所, 四川 绵阳 621000，mayueyin@cardc.cn
李道奎
国防科技大学 空天科学学院, 湖南 长沙 410073;
空天任务智能规划与仿真湖南省重点实验室, 湖南 长沙 410073
聂旭涛
中国空气动力研究与发展中心 设备设计及测试技术研究所, 四川 绵阳 621000
张伟
国防科技大学 空天科学学院, 湖南 长沙 410073;
中国空气动力研究与发展中心 设备设计及测试技术研究所, 四川 绵阳 621000
高鑫宇
中国空气动力研究与发展中心 设备设计及测试技术研究所, 四川 绵阳 621000
陈万华
中国空气动力研究与发展中心 设备设计及测试技术研究所, 四川 绵阳 621000
陈振华
中国空气动力研究与发展中心 设备设计及测试技术研究所, 四川 绵阳 621000
摘要：
为改善第二喉道中的可调中心体机构(简称中心体)在工作状态下的流致振动,根据形状记忆合金(shape memory alloy, SMA)偏置双程驱动原理,设计制作一种能够满足中心体有限安装空间要求的SMA自复位减振装置；采用UMAT接口编制的SMA本构关系子程序实现减振装置最大压紧力的数值分析,数值分析与静态调试试验结果误差约为2.58%；搭建地面减振试验平台,测试SMA自复位减振装置分离和闭合状态下的中心体零部件振动响应。减振试验结果显示:SMA自复位减振装置闭合后,中心体振动响应明显降低,在0～100 Hz频带内,均有明显的减振效果,低频至55 Hz范围内,减振率均大于50%。
为改善第二喉道中的可调中心体机构(简称中心体)在工作状态下的流致振动,根据形状记忆合金(shape memory alloy, SMA)偏置双程驱动原理,设计制作一种能够满足中心体有限安装空间要求的SMA自复位减振装置；采用UMAT接口编制的SMA本构关系子程序实现减振装置最大压紧力的数值分析,数值分析与静态调试试验结果误差约为2.58%；搭建地面减振试验平台,测试SMA自复位减振装置分离和闭合状态下的中心体零部件振动响应。减振试验结果显示:SMA自复位减振装置闭合后,中心体振动响应明显降低,在0～100 Hz频带内,均有明显的减振效果,低频至55 Hz范围内,减振率均大于50%。
基金项目：
中国空气动力研究与发展中心基础与前沿技术研究基金资助项目(PJD20200224)
中国空气动力研究与发展中心基础与前沿技术研究基金资助项目(PJD20200224)
Development and verification of shape memory alloy self-resetting vibration damping device
MA Yueyin
College of Aerospace Science and Engineering, National University Defense Technology, Changsha 410073, China;
Hunan Key Laboratory of Intelligent Planning and Simulation for Aerospace Missions, Changsha 410073, China;
Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China,mayueyin@cardc.cn
LI Daokui
College of Aerospace Science and Engineering, National University Defense Technology, Changsha 410073, China;
Hunan Key Laboratory of Intelligent Planning and Simulation for Aerospace Missions, Changsha 410073, China
NIE Xutao
Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
ZHANG Wei
College of Aerospace Science and Engineering, National University Defense Technology, Changsha 410073, China;
Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
GAO Xinyu
Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
CHEN Wanhua
Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
CHEN Zhenhua
Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
College of Aerospace Science and Engineering, National University Defense Technology, Changsha 410073, China;
Hunan Key Laboratory of Intelligent Planning and Simulation for Aerospace Missions, Changsha 410073, China;
Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China,mayueyin@cardc.cn
LI Daokui
College of Aerospace Science and Engineering, National University Defense Technology, Changsha 410073, China;
Hunan Key Laboratory of Intelligent Planning and Simulation for Aerospace Missions, Changsha 410073, China
NIE Xutao
Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
ZHANG Wei
College of Aerospace Science and Engineering, National University Defense Technology, Changsha 410073, China;
Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
GAO Xinyu
Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
CHEN Wanhua
Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
CHEN Zhenhua
Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China
Abstract：
In order to improve the flow induced vibration of the adjustable central flap mechanism deployed in the second throat in the working state, a SMA (shape memory alloy) self-resetting vibration damping device which could meet the limited installation space of the central flap mechanism was designed and manufactured according to the biasing two-way driving principle of SMA. The SMA constitutive relation subroutine compiled by UMAT interface was used to realize the numerical analysis of the maximum pressing force of the damping device, and the error between the numerical analysis and the static test results is about 2.58%. A ground vibration reduction test platform was built to test the vibration reduction effect of SMA self-resetting vibration damping device in the separated and closed states. The vibration reduction test results show that the vibration response of the central flap mechanism is significantly reduced with SMA self-resetting damping device activated. An obvious damping effect appear in the frequency band of 0～100 Hz, especially, the damping rate in the range of low frequency to 55 Hz is greater than 50%.
In order to improve the flow induced vibration of the adjustable central flap mechanism deployed in the second throat in the working state, a SMA (shape memory alloy) self-resetting vibration damping device which could meet the limited installation space of the central flap mechanism was designed and manufactured according to the biasing two-way driving principle of SMA. The SMA constitutive relation subroutine compiled by UMAT interface was used to realize the numerical analysis of the maximum pressing force of the damping device, and the error between the numerical analysis and the static test results is about 2.58%. A ground vibration reduction test platform was built to test the vibration reduction effect of SMA self-resetting vibration damping device in the separated and closed states. The vibration reduction test results show that the vibration response of the central flap mechanism is significantly reduced with SMA self-resetting damping device activated. An obvious damping effect appear in the frequency band of 0～100 Hz, especially, the damping rate in the range of low frequency to 55 Hz is greater than 50%.
收稿日期：
2022-03-03
2022-03-03
