基于数值延拓算法的倾转旋翼机配平及稳定性分析
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摘要
考虑旋翼尾流对机翼、平尾和垂尾的气动干扰,建立了倾转旋翼机非线性飞行动力模型。以XV-15为例,通过简化悬停模型,计算得到悬停的配平解,在此基础上,分别以前飞速度和短舱转角为延拓参数,数值延拓完成直升机模式、过渡模式和飞机模式在不同飞行速度下的配平。并在此基础上对倾转旋翼机进行稳定性分析。计算结果表明:应用数值延拓算法进行配平可以不受初值限制计算得到真实解;数值延拓算法具有全面性,可计算全短舱转角-速度包线内的平衡值。
The nonlinear flight dynamics model of tilt-rotor aircraft was developed by considering the influence of rotor wake on wing,horizontal stabilizer and vertical stabilizer.Taking the tilt-rotor XV-15 for an instance,by simplifying the hovering model,trim result of hovering was easily calculated.Then,based on the hovering solution,using forward velocity and nacelle conversion angle as continuation parameters,trim calculations of helicopter mode,conversion mode and airplane mode were accomplished by numerical continuation method.Stability was also analyzed based on the trim results.Calculated results showed that,numerical continuation method can calculate the trim solution without being limited by the initial value;the continuation method can calculate the trim solution in the whole conversion envelope and provide a global analysis.
The nonlinear flight dynamics model of tilt-rotor aircraft was developed by considering the influence of rotor wake on wing,horizontal stabilizer and vertical stabilizer.Taking the tilt-rotor XV-15 for an instance,by simplifying the hovering model,trim result of hovering was easily calculated.Then,based on the hovering solution,using forward velocity and nacelle conversion angle as continuation parameters,trim calculations of helicopter mode,conversion mode and airplane mode were accomplished by numerical continuation method.Stability was also analyzed based on the trim results.Calculated results showed that,numerical continuation method can calculate the trim solution without being limited by the initial value;the continuation method can calculate the trim solution in the whole conversion envelope and provide a global analysis.
引文
[1]FERGUSON S W.A mathematical model for real time flight simulation of a generic tilt-rotor aircraft[R].NASA CR-166536,1988.
[2]FERGUSON S W.Development and validation of a simulation for a generic tilt-rotor aircraft[R].NASA CR-166537,1989.
[3]JHEMI A A,CARLSON E B,ZHAO Y J,et al.Optimization of rotorcraft flight following engine failure[J].Journal of the American Helicopter Society,2004,49(2):117-126.
[4]HARENDRA P B,JOGLEKAR M J,GAFFEY T M,et al.V/STOL tilt rotor study:Volume 5a mathematical model for real time flight simulation of the Bell model 301tilt rotor research aircraft[R].NASA-CR-114614,1973.
[5]PASHILKAR A A,PRADEEP S.Computation of flight mechanics parameters using continuation techniques[J].Journal of Guidance,Control,and Dynamics,2001,24(2):324-329.
[6]ANANTHKRISHNAN N,SINHA N K,Level flight trim and stability analysis using extended bifurcation and continuation procedure[J].Journal of Guidance,Control,and Dynamics,2001,24(6):1225-1228.
[7]万绍峰,曹龙,黄俊森,等.数值延拓算法应用于直升机配平计算[J].直升机技术,2015(2):11-15.WANG Shaofeng,CAO Long,HUANG Junsen,et al.Helicopter trim calculation by numerical continuation method[J].Helicopter Technique,2015(2):11-15.(in Chinese)
[8]CAO Yihua,CAO Long,WAN Shaofeng.Trim calculation of the CH-53 helicopter using numerical continuation method[J].Journal of Guidance,Control and Dynamics,2014,37(4):1343-1349.
[9]曹龙.直升机外吊挂动力学建模与飞行性能分析[D].北京:北京航空航天大学,2014.CAO long.Dynamics modeling and flying performance analysis of helicopter with slung-load[D].Beijng:Beijing University of Aeronautics and Astronautics,2014.(in Chinese)
[10]MCVICAR J S G,BRADLEYT R.Robust and efficient trimming algorithm for application to advanced mathematical models of rotorcraft[J].Journal of Aircraft,1995,32(2):439-442.
[11]BERND K,HINKE M O,JORGE G.Numerical continuation methods for dynamical systems[M].Berlin:Springer,2007.
[12]高正,陈仁良.直升机飞行动力学[M].北京:科学出版社,2003.
[13]曹芸芸,陈仁良.倾转旋翼飞行器旋翼对机翼向下载荷计算模型[J].航空动力学报,2011,26(2):468-474.CAO Yunyun,CHEN Renliang.Mathematical model for calculating wing download of tiltrotor aircraft[J].Journal of Aerospace Power,2011,26(2):468-474.(in Chinese)
[14]夏青元,徐锦法,金开保.倾转旋翼飞行器的建模和操纵分配策略[J].航空动力学报,2013,28(9):2016-2028.XIA Qingyuan,XU Jinfa,JIN Kaibao.Tilt-rotor aircraft modeling and its manipulation assignment strategy[J].Journal of Aerospace Power,2013,28(9):2016-2028.(in Chinese)
[15]KLEINHESSELINK K.Stability and control modeling of tiltrotor aircraft[D].College Park:University of Maryland,2007.
[16]沙虹伟,陈仁良.倾转旋翼机飞行力学特性[J].航空动力学报,2012,27(4):749-754.SHA Hongwei,CHEN Renliang.Flight dynamics characteristic of tilt rotor aircraft[J].Journal of Aerospace Power,2012,27(4):749-754.(in Chinese)
[17]曹芸芸.倾转旋翼飞行器飞行动力学数学建模方法研究[D].南京:南京航空航天大学,2012.CAO Yunyun.Research on mathematical modeling method for tilt rotor aircraft flight dynamics[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2012.(in Chinese)
[18]岳海龙,夏品奇.倾转旋翼机前飞动力学稳定性分析[J].航空动力学报,2007,22(11):1863-1867.YUE Hailong,XIA Pinqi.Dynamic stability analysis of tiltrotor aircraft in forward flight[J].Journal of Aerospace Power,2007,22(11):1863-1867.(in Chinese)
[2]FERGUSON S W.Development and validation of a simulation for a generic tilt-rotor aircraft[R].NASA CR-166537,1989.
[3]JHEMI A A,CARLSON E B,ZHAO Y J,et al.Optimization of rotorcraft flight following engine failure[J].Journal of the American Helicopter Society,2004,49(2):117-126.
[4]HARENDRA P B,JOGLEKAR M J,GAFFEY T M,et al.V/STOL tilt rotor study:Volume 5a mathematical model for real time flight simulation of the Bell model 301tilt rotor research aircraft[R].NASA-CR-114614,1973.
[5]PASHILKAR A A,PRADEEP S.Computation of flight mechanics parameters using continuation techniques[J].Journal of Guidance,Control,and Dynamics,2001,24(2):324-329.
[6]ANANTHKRISHNAN N,SINHA N K,Level flight trim and stability analysis using extended bifurcation and continuation procedure[J].Journal of Guidance,Control,and Dynamics,2001,24(6):1225-1228.
[7]万绍峰,曹龙,黄俊森,等.数值延拓算法应用于直升机配平计算[J].直升机技术,2015(2):11-15.WANG Shaofeng,CAO Long,HUANG Junsen,et al.Helicopter trim calculation by numerical continuation method[J].Helicopter Technique,2015(2):11-15.(in Chinese)
[8]CAO Yihua,CAO Long,WAN Shaofeng.Trim calculation of the CH-53 helicopter using numerical continuation method[J].Journal of Guidance,Control and Dynamics,2014,37(4):1343-1349.
[9]曹龙.直升机外吊挂动力学建模与飞行性能分析[D].北京:北京航空航天大学,2014.CAO long.Dynamics modeling and flying performance analysis of helicopter with slung-load[D].Beijng:Beijing University of Aeronautics and Astronautics,2014.(in Chinese)
[10]MCVICAR J S G,BRADLEYT R.Robust and efficient trimming algorithm for application to advanced mathematical models of rotorcraft[J].Journal of Aircraft,1995,32(2):439-442.
[11]BERND K,HINKE M O,JORGE G.Numerical continuation methods for dynamical systems[M].Berlin:Springer,2007.
[12]高正,陈仁良.直升机飞行动力学[M].北京:科学出版社,2003.
[13]曹芸芸,陈仁良.倾转旋翼飞行器旋翼对机翼向下载荷计算模型[J].航空动力学报,2011,26(2):468-474.CAO Yunyun,CHEN Renliang.Mathematical model for calculating wing download of tiltrotor aircraft[J].Journal of Aerospace Power,2011,26(2):468-474.(in Chinese)
[14]夏青元,徐锦法,金开保.倾转旋翼飞行器的建模和操纵分配策略[J].航空动力学报,2013,28(9):2016-2028.XIA Qingyuan,XU Jinfa,JIN Kaibao.Tilt-rotor aircraft modeling and its manipulation assignment strategy[J].Journal of Aerospace Power,2013,28(9):2016-2028.(in Chinese)
[15]KLEINHESSELINK K.Stability and control modeling of tiltrotor aircraft[D].College Park:University of Maryland,2007.
[16]沙虹伟,陈仁良.倾转旋翼机飞行力学特性[J].航空动力学报,2012,27(4):749-754.SHA Hongwei,CHEN Renliang.Flight dynamics characteristic of tilt rotor aircraft[J].Journal of Aerospace Power,2012,27(4):749-754.(in Chinese)
[17]曹芸芸.倾转旋翼飞行器飞行动力学数学建模方法研究[D].南京:南京航空航天大学,2012.CAO Yunyun.Research on mathematical modeling method for tilt rotor aircraft flight dynamics[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2012.(in Chinese)
[18]岳海龙,夏品奇.倾转旋翼机前飞动力学稳定性分析[J].航空动力学报,2007,22(11):1863-1867.YUE Hailong,XIA Pinqi.Dynamic stability analysis of tiltrotor aircraft in forward flight[J].Journal of Aerospace Power,2007,22(11):1863-1867.(in Chinese)