An active control technique utilizing piezoelectric actuators to alleviate gust-response loads of a large-aspect-ratio flexible wing is investigated. Piezoelectric materials have been extensively used for active vibra...An active control technique utilizing piezoelectric actuators to alleviate gust-response loads of a large-aspect-ratio flexible wing is investigated. Piezoelectric materials have been extensively used for active vibration control of engineering structures. In this paper, piezoelectric materials further attempt to suppress the vibration of the aeroelastic wing caused by gust. The motion equation of the flexible wing with piezoelectric patches is obtained by Hamilton＇s principle with the modal approach, and then numerical gust responses are analyzed, based on which a gust load alleviation（GLA） control system is proposed. The gust load alleviation system employs classic propor tional-integral-derivative（PID） controllers which treat piezoelectric patches as control actuators and acceleration as the feedback signal. By a numerical method, the control mechanism that piezoelectric actuators can be used to alleviate gust-response loads is also analyzed qualitatively. Furthermore, through low-speed wind tunnel tests, the effectiveness of the gust load alleviation active control technology is validated. The test results agree well with the numerical results. Test results show that at a certain frequency range, the control scheme can effectively alleviate the z and x wingtip accelerations and the root bending moment of the wing to a certain extent. The control system gives satisfying gust load alleviation efficacy with the reduction rate being generally over 20%.展开更多
Owing to the advantages of wire-driven parallel manipulator, a new wire-driven parallel suspension system for airplane model in low-speed wind tunnel is constructed, and the methods to measure and calculate the aerody...Owing to the advantages of wire-driven parallel manipulator, a new wire-driven parallel suspension system for airplane model in low-speed wind tunnel is constructed, and the methods to measure and calculate the aerodynamic parameters of the airplane model are studied. In detail, a static model of the wire-driven parallel suspension is analyzed, a mathematical model for describ- ing the aerodynamic loads exerted on the scale model is constructed and a calculation method for obtaining the aerodynamic parameters of the model by measuring the tension of wires is presented. Moreover, the measurement system for wire tension and its corresponding data acquisition system are designed and built. Thereafter, the wire-driven parallel suspension system is placed in an open return circuit low-speed wind tunnel for wind tunnel tests to acquire data of each wire tension when the airplane model is at different attitudes and different wind speeds. A group of curves about the parameters for aerodynamic load exerted on the airplane model are obtained at different wind speeds after the acquired data are analyzed. The research results validate the feasibility of using a wire-driven parallel manipulator as the suspension system for low-speed wind ttmnel tests.展开更多
近年来,国际上不同国家和地区有关风荷载计算的规范均有不同程度的更新迭代,为了研究规范中风荷载及风致加速度计算参数的差异影响,以联邦航空咨询委员会(Commonwealth Advisory Aeronautical Research Council,CAARC)提出的简单标准模...近年来,国际上不同国家和地区有关风荷载计算的规范均有不同程度的更新迭代,为了研究规范中风荷载及风致加速度计算参数的差异影响,以联邦航空咨询委员会(Commonwealth Advisory Aeronautical Research Council,CAARC)提出的简单标准模型试验为例,对不同国家和地区的矩形高层建筑顺风向风荷载及风致加速度进行对比研究。首先,对不同规范给定的风场特性及风场参数进行了详细分析;随后,将不同规范中的风荷载和风致加速度计算公式归一化处理;最后,结合风洞试验结果,详细讨论参考风速、湍流强度、湍流积分尺度、峰值因子、背景响应因子、共振响应因子、阵风响应因子的差异及其对风荷载及风致加速度的影响。结果表明:风场参数的差异是造成高层建筑顺风向风荷载和风致加速度不同的决定性因素。展开更多
以带运动抑制结构的圆筒型浮式生产储卸油装置(Cylindrical Floating Production Storage and Offloading,CFPSO)为研究对象,在低速风洞中对CFPSO流载荷进行测量。为获得均匀流并减少边界层的影响,采用距离地面一定高度的小地板。热线...以带运动抑制结构的圆筒型浮式生产储卸油装置(Cylindrical Floating Production Storage and Offloading,CFPSO)为研究对象,在低速风洞中对CFPSO流载荷进行测量。为获得均匀流并减少边界层的影响,采用距离地面一定高度的小地板。热线测量结果表明,采用小地板能够获得更均匀的流剖面。通过风洞试验对4种不同型式的运动抑制结构流载荷进行测量,进一步采用数值模拟方法对不同型式运动抑制结构的尾流场进行分析。结果表明:运动抑制结构通过对尾涡的限制,减少能量损耗,实现减阻效果。研究结果可为运动抑制结构的设计提供一定的参考。展开更多
基金supported by the National Key Research and Development Program (2016YFB 0200703)
文摘An active control technique utilizing piezoelectric actuators to alleviate gust-response loads of a large-aspect-ratio flexible wing is investigated. Piezoelectric materials have been extensively used for active vibration control of engineering structures. In this paper, piezoelectric materials further attempt to suppress the vibration of the aeroelastic wing caused by gust. The motion equation of the flexible wing with piezoelectric patches is obtained by Hamilton＇s principle with the modal approach, and then numerical gust responses are analyzed, based on which a gust load alleviation（GLA） control system is proposed. The gust load alleviation system employs classic propor tional-integral-derivative（PID） controllers which treat piezoelectric patches as control actuators and acceleration as the feedback signal. By a numerical method, the control mechanism that piezoelectric actuators can be used to alleviate gust-response loads is also analyzed qualitatively. Furthermore, through low-speed wind tunnel tests, the effectiveness of the gust load alleviation active control technology is validated. The test results agree well with the numerical results. Test results show that at a certain frequency range, the control scheme can effectively alleviate the z and x wingtip accelerations and the root bending moment of the wing to a certain extent. The control system gives satisfying gust load alleviation efficacy with the reduction rate being generally over 20%.
基金National Natural Science Foundation of China (50475099)
文摘Owing to the advantages of wire-driven parallel manipulator, a new wire-driven parallel suspension system for airplane model in low-speed wind tunnel is constructed, and the methods to measure and calculate the aerodynamic parameters of the airplane model are studied. In detail, a static model of the wire-driven parallel suspension is analyzed, a mathematical model for describ- ing the aerodynamic loads exerted on the scale model is constructed and a calculation method for obtaining the aerodynamic parameters of the model by measuring the tension of wires is presented. Moreover, the measurement system for wire tension and its corresponding data acquisition system are designed and built. Thereafter, the wire-driven parallel suspension system is placed in an open return circuit low-speed wind tunnel for wind tunnel tests to acquire data of each wire tension when the airplane model is at different attitudes and different wind speeds. A group of curves about the parameters for aerodynamic load exerted on the airplane model are obtained at different wind speeds after the acquired data are analyzed. The research results validate the feasibility of using a wire-driven parallel manipulator as the suspension system for low-speed wind ttmnel tests.
文摘近年来,国际上不同国家和地区有关风荷载计算的规范均有不同程度的更新迭代,为了研究规范中风荷载及风致加速度计算参数的差异影响,以联邦航空咨询委员会(Commonwealth Advisory Aeronautical Research Council,CAARC)提出的简单标准模型试验为例,对不同国家和地区的矩形高层建筑顺风向风荷载及风致加速度进行对比研究。首先,对不同规范给定的风场特性及风场参数进行了详细分析;随后,将不同规范中的风荷载和风致加速度计算公式归一化处理;最后,结合风洞试验结果,详细讨论参考风速、湍流强度、湍流积分尺度、峰值因子、背景响应因子、共振响应因子、阵风响应因子的差异及其对风荷载及风致加速度的影响。结果表明:风场参数的差异是造成高层建筑顺风向风荷载和风致加速度不同的决定性因素。
文摘以带运动抑制结构的圆筒型浮式生产储卸油装置(Cylindrical Floating Production Storage and Offloading,CFPSO)为研究对象,在低速风洞中对CFPSO流载荷进行测量。为获得均匀流并减少边界层的影响,采用距离地面一定高度的小地板。热线测量结果表明,采用小地板能够获得更均匀的流剖面。通过风洞试验对4种不同型式的运动抑制结构流载荷进行测量,进一步采用数值模拟方法对不同型式运动抑制结构的尾流场进行分析。结果表明:运动抑制结构通过对尾涡的限制,减少能量损耗,实现减阻效果。研究结果可为运动抑制结构的设计提供一定的参考。
