基于优化算法的倾转旋翼准定常气动模型

吴大卫; 李书

基于优化算法的倾转旋翼准定常气动模型

吴大卫^1,2,
李书¹

1.
北京航空航天大学航空科学与工程学院, 北京 100191
2.
中国商用飞机有限责任公司上海飞机设计研究院, 上海 200232

基金项目: 国家高技术研究发展计划(2012AA112201); 国家自然科学基金(10772013)

计量
- 文章访问数: 2067
- HTML浏览量: 1
- PDF量: 1252
- 被引次数: 0
出版历程
- 收稿日期: 2012-04-16
- 刊出日期: 2013-04-28

Quasi-steady aerodynamic model of tilt rotor based on optimization algorithm

WU Da-wei^1,2,
LI Shu¹

1.
School of Aeronautics Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
2.
Shanghai Aircraft Design and Research Institute, Commercial Aircraft Corporation of China Limited, Shanghai 200232, China

摘要

摘要: 取消了传统直升机旋翼准定常气动模型中对飞行工况和桨叶形状的诸多假设和限制,建立了适合倾转旋翼特殊桨叶形状、桨毂构造以及飞行工况的准定常气动模型.桨叶气动载荷计算基于叶素理论进行数值积分,旋翼挥舞系数通过序列二次规划算法(SQP)进行数值优化求解,诱导速度分布采用Pitt-Peters动态入流模型的稳态形式.利用该方法计算了XV-15倾转旋翼机的旋翼在不同工况下的气动性能以及挥舞系数.计算结果与风洞实验数据吻合良好,误差在8%以内且计算效率高,单一工况求解耗时在5min以内,该方法可用于倾转旋翼机总体设计阶段的性能分析或建立其飞行动力学模型.
- 倾转旋翼 /
- 准定常 /
- 叶素理论 /
- 优化 /
- 气动性能 /
- 挥舞
Abstract: There are many hypotheses and limitations about the flight condition and blade shape in the quasi-steady aerodynamic model of conventional helicopter rotor,and many of them were eliminated considering the special blade shape,hub structure and flight condition of tilt rotor.Aerodynamic loads were calculated through numerical integration based on the blade element theory,and flap coefficients of tilt rotor were solved through sequential quadratic programming (SQP) algorithm.Induced velocity distribution was adopted as the steady form of Pitt-Peters dynamic inflow model.The aerodynamic performance and flap coefficients of the rotor of XV-15 tilt rotor aircraft were predicted by this method.The theoretical results and wind tunnel tests data make good agreement with error less than 8% and this method has high calculation efficiency that one case can be solved within 5 minutes,therefore,this method is applicable for aerodynamic performance prediction in preliminary design of tilt rotor aircraft and suitable to set up its flight dynamics model.
- tilt rotor /
- quasi-steady /
- blade element theory /
- optimization /
- aerodynamic performance /
- flap

HTML

参考文献(17)

[1]	Leishman J G.Principles of helicopter aerodynamics[M].New York:Cambridge University Press,2006.
[2]	Dreier M E.Introduction to helicopter and tiltrotor simulation[M].USA:American Institute of Aeronautics and Astronautics,2007.
[3]	Rosenstein H,McVeigh M A,Mollenkof P A.V/STOL tilt rotor aircraft study mathematical model for a real time simulation of a tilt rotor aircraft (Boeing vertol model 222):Volume 8 [R].NASA CR-114601,1973.
[4]	Harenda P B,Joglekar M J,Gaffey T M,et al.V/STOL tilt rotor study:Volume 5 a mathematical model for real time flight simulation of the Bell model 301 tilt rotor research aircraft[R].NASA CR-114614,1973.
[5]	McVeigh M A.Preliminary simulation of an advanced,hingless rotor XV-15 tilt-rotor aircraft [R].NASA CR-151950,1976.
[6]	高正,陈仁良. 直升机飞行动力学[M].北京:科学出版社, 2003.
[7]	Prouty R W.直升机性能及稳定性和操纵性[M].北京:航空工业出版社,1990.
[8]	吴大卫.倾转旋翼机总体方案与飞行动力学研究 [D].北京:北京航空航天大学,2012. WU Dawei.Investigation on conceptual design and flight dynamics of tiltrotor aircraft [D].Beijing:Beijing University of Aeronautics and Astronautics,2012.(in Chinese)
[9]	Pitt D M,Peters D A.Theoretical prediction of dynamic inflow derivatives[J].Vertica,1981,5(1):21-34.
[10]	ZHAO Jinggen.Dynamic wake distortion model for helicopter maneuvering flight [D].USA:Georgia Institute of Technology,2005.
[11]	王适存.直升机空气动力学[M].北京:航空工业教材编审组,1981.
[12]	Chen R T N.A survey of nonuniform inflow models for rotorcraft flight dynamics and control applications [R].NASA TM-102219,1989.
[13]	颜庆津.数值分析[M].北京:北京航空航天大学出版社, 2006.
[14]	孙丰诚,孙建国.基于序列二次规划算法的发动机性能寻优控制[J].航空动力学报,2005,20(5):862-867. SUN Fengcheng,SUN Jianguo.Aero-engine performance seeking control based on sequential quadratic programming algorithm[J].Journal of Aerospace Power,2005,20(5):862-867.(in Chinese)
[15]	Math Works.Matlab manual:optimization toolbox[M].USA: The Math Works,Inc.,2008.
[16]	Bell Helicopter Company.Advancement of proprotor technology:Task 2 wind-tunnel test results [R].NASA CR-114363,1971.
[17]	Helf S,Broman E,Gatchel S,et al.Full scale hover test of a 25 foot tilt rotor [R].NASA CR-114626,1973.