直升机抛射物体平衡及稳定性分析
|
摘要
基于部件级建模理论建立了建立直升机-外挂装置系统六自由度飞行动力学模型。对所建模型进行了配平计算,与参考数据进行了对比。计算分析了不同速度下采用不同方式抛射物体时直升机的稳定性。结果表明,单侧抛射由于反冲力不对称,抛射物体对于直升机的滚转角和横向周期变距有显著的影响;随飞行速度增大,抛射物体对于直升机横向荷兰滚模态稳定性影响增大,当前飞速度达到50m/s以上时,荷兰滚模态演变为两个发散的非周期模态,稳定性明显变差,直升机应在较低速度下抛射物体。
A six freedoms flight dynamics model for a helicopter with pylons was built based on the theory of component-level.Trim calculation was conducted,and the result compared with the existing conclusion.Stability was analyzed for the helicopter casting objects with different patterns at different flight velocities.The result indicated that there was great effect on rolling angle and lateral control-stick when the helicopter cast objects by one-side due to the asymmetry of the recoil force.With the increase of the forward-flight velocity,casting objects had a greater effect on Dutch mode.Dutch mode evolved into two divergent aperiodic modes as the helicopter cast objects at a velocity higher than 50 m/s,flight stability became worse obviously.The helicopter should cast objects at a lower velocity.
A six freedoms flight dynamics model for a helicopter with pylons was built based on the theory of component-level.Trim calculation was conducted,and the result compared with the existing conclusion.Stability was analyzed for the helicopter casting objects with different patterns at different flight velocities.The result indicated that there was great effect on rolling angle and lateral control-stick when the helicopter cast objects by one-side due to the asymmetry of the recoil force.With the increase of the forward-flight velocity,casting objects had a greater effect on Dutch mode.Dutch mode evolved into two divergent aperiodic modes as the helicopter cast objects at a velocity higher than 50 m/s,flight stability became worse obviously.The helicopter should cast objects at a lower velocity.
引文
[1]TALBOT P D.A mathematical model of a single main rotor helicopter for piloted simulation[R].NASA TM84281,1982.
[2]CHEN R T N.A simplified rotor system mathematical model for piloted flight dynamics simulation[R].NASATM78575,1979.
[3]CHEN R T N.Effects of primary rotor parameters on flapping dynamics[R].NASA TP1431,1980.
[4]HOWLETT J J.UH-60ABlack Hawk engineering simulation program:VolumeⅠmathematical model[R].NASACR166309,1981.
[5]BALLIN M G.Validation of a real-time engineering simulation of the UH-60A helicopter[R].NASA TM88359,1987.
[6]HILBERT K B.A mathematical model of UH-60helicopter[R].NASA TM85890,1984.
[7]CALLAHAN C,BASSETT D.Application of a comprehensive analytical model of rotor aerodynamics and dynamics(CAMRAD)to the McDonnell Douglas AH-64Ahelicopter[R].NASA CR177455,1988.
[8]CAO Yihua,LI Guozhi,YANG Qian.Studies of trims,stability,controllability,and some flying qualities of a tandem rotor helicopter[J].Journal of Aerospace Engineering,2009,223(G2):171-177.
[9]李国知,曹义华,杨倩.纵列式直升机配平计算及稳定性、操纵性分析[J].北京航空航天大学学报,2009,35(1):74-77.LI Guozhi,CAO Yihua,YANG Qian.Analysis for determining trim,stability and control ability of tandem helicopter[J].Journal of Beijing University of Aeronautics and Astronautics,2009,35(1):74-77.(in Chinese)
[10]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.
[11]SU Yuan,CAO Yihua.Studies of helicopter dynamic stability and control laws[J].Aircraft Engineering and Aerospace Technology,2001,73(2):132-137.
[12]苏媛,曹义华,方振平.直升机近地飞行时的配平和机动操纵分析[J].航空动力学报,2010,25(2):348-353.SU Yuan,CAO Yihua,FANG Zhenping.Trimming and maneuvering control of a helicopter flight near the ground[J].Journal of Aerospace Power,2010,25(2):348-353.(in Chinese)
[13]吕少杰,魏靖彪,刘宁,等.旋翼气动特性分析及直升机配平计算[J].航空动力学报,2017,32(10):2484-2490.LShaojie,WEI Jingbiao,LIU Ning,et al.Rotor aerodynamic characteristics analysis and helicopter trimming[J].Journal of Aerospace Power,2017,32(10):2484-2490.(in Chinese)
[14]孙传伟.直升机飞行动力学模型与飞行品质评估[D].南京:南京航空航天大学,2001.SUN Chuanwei.Flight dynamics modeling for rotorcraft flying quality evaluation[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2001.(in Chinese)
[15]李攀.旋翼非定常自由尾迹及高置信度直升机飞行动力学建模研究[D].南京:南京航空航天大学,2010.LI Pan.Rotor unsteady free-vortex wake model and investigation on high-fidelity modeling of helicopter flight dynamic[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2010.(in Chinese)
[16]高正,陈仁良.直升机飞行动力学[M].北京:科学出版社,2003.
[17]PADFIELD G D.Helicopter flight dynamics:the theory and application of flying qualities andmodelling[M].2nd ed.Oxford:Blackwell Publishing,2007.
[2]CHEN R T N.A simplified rotor system mathematical model for piloted flight dynamics simulation[R].NASATM78575,1979.
[3]CHEN R T N.Effects of primary rotor parameters on flapping dynamics[R].NASA TP1431,1980.
[4]HOWLETT J J.UH-60ABlack Hawk engineering simulation program:VolumeⅠmathematical model[R].NASACR166309,1981.
[5]BALLIN M G.Validation of a real-time engineering simulation of the UH-60A helicopter[R].NASA TM88359,1987.
[6]HILBERT K B.A mathematical model of UH-60helicopter[R].NASA TM85890,1984.
[7]CALLAHAN C,BASSETT D.Application of a comprehensive analytical model of rotor aerodynamics and dynamics(CAMRAD)to the McDonnell Douglas AH-64Ahelicopter[R].NASA CR177455,1988.
[8]CAO Yihua,LI Guozhi,YANG Qian.Studies of trims,stability,controllability,and some flying qualities of a tandem rotor helicopter[J].Journal of Aerospace Engineering,2009,223(G2):171-177.
[9]李国知,曹义华,杨倩.纵列式直升机配平计算及稳定性、操纵性分析[J].北京航空航天大学学报,2009,35(1):74-77.LI Guozhi,CAO Yihua,YANG Qian.Analysis for determining trim,stability and control ability of tandem helicopter[J].Journal of Beijing University of Aeronautics and Astronautics,2009,35(1):74-77.(in Chinese)
[10]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.
[11]SU Yuan,CAO Yihua.Studies of helicopter dynamic stability and control laws[J].Aircraft Engineering and Aerospace Technology,2001,73(2):132-137.
[12]苏媛,曹义华,方振平.直升机近地飞行时的配平和机动操纵分析[J].航空动力学报,2010,25(2):348-353.SU Yuan,CAO Yihua,FANG Zhenping.Trimming and maneuvering control of a helicopter flight near the ground[J].Journal of Aerospace Power,2010,25(2):348-353.(in Chinese)
[13]吕少杰,魏靖彪,刘宁,等.旋翼气动特性分析及直升机配平计算[J].航空动力学报,2017,32(10):2484-2490.LShaojie,WEI Jingbiao,LIU Ning,et al.Rotor aerodynamic characteristics analysis and helicopter trimming[J].Journal of Aerospace Power,2017,32(10):2484-2490.(in Chinese)
[14]孙传伟.直升机飞行动力学模型与飞行品质评估[D].南京:南京航空航天大学,2001.SUN Chuanwei.Flight dynamics modeling for rotorcraft flying quality evaluation[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2001.(in Chinese)
[15]李攀.旋翼非定常自由尾迹及高置信度直升机飞行动力学建模研究[D].南京:南京航空航天大学,2010.LI Pan.Rotor unsteady free-vortex wake model and investigation on high-fidelity modeling of helicopter flight dynamic[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2010.(in Chinese)
[16]高正,陈仁良.直升机飞行动力学[M].北京:科学出版社,2003.
[17]PADFIELD G D.Helicopter flight dynamics:the theory and application of flying qualities andmodelling[M].2nd ed.Oxford:Blackwell Publishing,2007.