留言板

尊敬的读者、作者、审稿人, 关于本刊的投稿、审稿、编辑和出版的任何问题, 您可以本页添加留言。我们将尽快给您答复。谢谢您的支持!

姓名
邮箱
手机号码
标题
留言内容
验证码

基于混合遗传算法的直升机前推/后拉配平

王巍 刘春 李东升

王巍, 刘春, 李东升等 . 基于混合遗传算法的直升机前推/后拉配平[J]. 北京航空航天大学学报, 2017, 43(10): 1994-2002. doi: 10.13700/j.bh.1001-5965.2016.0834
引用本文: 王巍, 刘春, 李东升等 . 基于混合遗传算法的直升机前推/后拉配平[J]. 北京航空航天大学学报, 2017, 43(10): 1994-2002. doi: 10.13700/j.bh.1001-5965.2016.0834
WANG Wei, LIU Chun, LI Dongshenget al. Push-forward/pull-backward trim for helicopter based on hybrid genetic algorithm[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(10): 1994-2002. doi: 10.13700/j.bh.1001-5965.2016.0834(in Chinese)
Citation: WANG Wei, LIU Chun, LI Dongshenget al. Push-forward/pull-backward trim for helicopter based on hybrid genetic algorithm[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(10): 1994-2002. doi: 10.13700/j.bh.1001-5965.2016.0834(in Chinese)

基于混合遗传算法的直升机前推/后拉配平

doi: 10.13700/j.bh.1001-5965.2016.0834
基金项目: 

沈阳航空航天大学国防重点学科实验室开放基金 SHSYS2015004

详细信息
    作者简介:

    王巍, 女, 博士研究生, 讲师。主要研究方向:直升机飞行仿真建模技术; 刘春, 男, 博士, 教授, 博士生导师。主要研究方向:飞行器仿真建模技术、虚拟现实

    通讯作者:

    王巍, E-mail: wangwei7832@163.com

  • 中图分类号: V211.52;V212.12

Push-forward/pull-backward trim for helicopter based on hybrid genetic algorithm

Funds: 

Key Laboratory of National Defense Open Foundation of Shenyang Aerospace University SHSYS2015004

More Information
  • 摘要:

    针对直升机配平模型为多元且初始值难以确定的非线性方程组,以及全局最优解不唯一等问题,发展了一种基于遗传算法/拟牛顿法的高效混合迭代算法。介绍了直升机各个模块动力学方程。其中在旋翼建模中,考虑实际飞行环境下桨叶的运动和操纵特性,以动态入流和叶素法为理论基础,建立了具有配平特性的旋翼气动力模型。基于直升机飞行仿真动力学模型,详细推导了前推/后拉的配平变量和约束方程。通过构造目标函数,将全机配平问题转化为优化问题。通过计算UH-60A直升机在前推/后拉的配平解,并与飞行测试数据进行比较验证。结果表明,前推配平结果与飞行数据有偏差,后拉配平结果与飞行数据吻合。旋翼非定常气动特性是引起总距和脚蹬配平计算误差的主要原因。建立的配平算法适用于直升机不同稳定飞行条件下的仿真。

     

  • 图 1  前推/后拉的配平状态

    Figure 1.  Trim attitude of push-forward/pull-backward

    图 2  配平过程

    Figure 2.  Trim process

    图 3  混合遗传算法流程图

    Figure 3.  Flowchart of hybrid genetic algorithm

    图 4  目标函数迭代曲线

    Figure 4.  Iterative curves of objective function

    图 5  加速度和角加速度配平结果(机体坐标系)

    Figure 5.  Trim results of acceleration and angular acceleration in body coordinate system

    图 6  旋翼功率配平结果

    Figure 6.  Trim results of rotor power

    图 7  Euler配平结果(地球惯性坐标系)

    Figure 7.  Trim results of Euler angles in earth inertial coordinate system

    图 8  总距杆、横向周期变距杆、纵向周期变距杆及脚蹬配平结果

    Figure 8.  Trim results of collective stick, lateral cycle stick, longitudinal cycle stick and pedal

  • [1] DE MARCO A, DUKE E L, BERNDT J S.A general solution to the aircraft trim problem[C]//AIAA Modeling and Simulation Technologies Conference and Exhibit.Reston:AIAA, 2007:3.
    [2] 张镭. 飞行模拟器飞行仿真系统建模与软件实现[D]. 哈尔滨: 哈尔滨工业大学, 2009: 62-69.

    ZHANG L.Flight simulation modeling and software development for flight simulator[D].Harbin:Harbin Institute of Technology, 2009:62-69(in Chinese).
    [3] PADFIELD G D.Helicopter flight dynamics:The theory and application of flying qualities and simulation modeling[M].Oxford:Blackwell Publishing Ltd., 2007:192-204.
    [4] SEKULA M K, GANDHI F.Effects of auxiliary lift and propulsion on helicopter vibration reduction and trim[J].Journal of Aircraft, 2004, 41(3):645-656. doi: 10.2514/1.496
    [5] STEIJL R, BARAKOS G, BADCOCK K.A framework for CFD analysis of helicopter rotors in hover and flight[J].Intermational Journal of Numerical Methods in Fluids, 2006, 51(8):819-847. doi: 10.1002/(ISSN)1097-0363
    [6] 杨超, 洪冠新.求解非线性代数方程组的一种建议方法[J].飞行力学, 1997, 15(2):42-46. http://www.cnki.com.cn/Article/CJFDTOTAL-FHLX199702008.htm

    YANG C, HONG G X.A suggested method of solving the nonlinear algebraic equations[J].Flight Dynamics, 1997, 15(2):42-46(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-FHLX199702008.htm
    [7] SUBRAMANIAN S, VENKATARATNAM S, GAON-KAR G H.Parallel fast-floquet analysis of trim and stability for large helicopter models[J].Mathematical and Computer Modeling, 2001, 33(10-11):1155-1176. doi: 10.1016/S0895-7177(00)00305-8
    [8] SCHANK T C.Optimal aeroelastic trim for rotorcraft with constrained non-unique trim solutions[D].Atlanta:Georgia Institute of Technology, 2008:87-90.
    [9] YAMASHITA N, FUKUSHIMA M.Modified Newton methods for solving a semi smooth reformlation of mono-tone complementarity problems[J].Math Program, 1997, 76(3):469-491. doi: 10.1007/BF02614394
    [10] 孙传伟, 黄一敏, 高正.直升机飞行品质评估数学建模研究[J].飞行力学, 2001, 19(1):10-12. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201707001.htm

    SUN C W, HUANG Y M, GAO Z.Investigation of helicopter mathematical model appropriate for flying quality evaluation[J].Flight Dynamics, 2001, 19(1):10-12(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201707001.htm
    [11] SUBRAMANIAN S, GAONKAR G H, MAIER T H.A theoretical and experimental investigation of hingeless-rotor stability and trim[C]//Twenty-Third European Rotorcraft Forum.Dresdoen:ERF, 1997:10-18.
    [12] BURDEN R L, FAIRES J D.Numerical analysis[M].7th ed.Boston:Prindle, Weber & Schmidt, 2001:851-865.
    [13] 刘国强. 基于遗传算法的直升机旋翼桨叶气动外形优化设计[D]. 南京: 南京航空航天大学, 2011: 11-12.

    LIU G Q.Aerodynamic shape optimization design for helicopter rotor blades based on the genetic algorithm[D].Nanjing:Nanjing University of Aeronautics and Astronautics, 2011:11-12(in Chinese).
    [14] ZHANG L, HUANG Q T, JIANG H Z.Trimming aircraft on the ground based on the hybrid genetic algorithm[J].The Japan Society for Aeronautical and Space Sciences, 2009, 52(177):117-224. https://www.jstage.jst.go.jp/article/tjsass/52/177/52_177_117/_article
    [15] 王海涛, 高金源.基于混合遗传算法求解飞机平衡状态[J].航空学报, 2005, 26(4):470-475. http://youxian.cnki.com.cn/yxdetail.aspx?filename=BJHK201710007&dbname=CJFDPREP

    WANG H T, GAO J Y.Solving the equilibrium states of aircraft based on mixture genetic algorithm[J].Acta Aeronautica et Astronautica Sinica, 2005, 26(4):470-475(in Chinese). http://youxian.cnki.com.cn/yxdetail.aspx?filename=BJHK201710007&dbname=CJFDPREP
    [16] 栾志博, 郑淑涛, 李洪人.基于混合遗传算法求解飞机定常状态[J].吉林大学学报(工学版), 2011, 41(1):165-170. http://www.cnki.com.cn/Article/CJFDTOTAL-JLGY201101033.htm

    LUAN Z B, ZHENG S T, LI H R.Solution of steady state of aircraft based on mixture genetic algorithm[J].Journal of Jilin University(Engineering and Technology Edition), 2011, 41(1):165-170(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-JLGY201101033.htm
    [17] DAI J Y.Robust flight controller design for helicopters based on genetic algorithms[C]//Proceedings of 15th Triennial World Congress of IFAC.Barcelona:IFAC, 2002:68-75.
    [18] 吴超, 谭剑锋, 王浩文, 等.基于GA/LM混合优化的直升机全机配平算法[J].飞行力学, 2014, 32(1):5-9. http://www.cnki.com.cn/Article/CJFDTOTAL-FHLX201401003.htm

    WU C, TAN J F, WANG H W, et al.Optimal trim for helicopter based on GA and LM hybrid algorithm[J].Flight Dynamics, 2014, 32(1):5-9(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-FHLX201401003.htm
    [19] 朱明勇, 招启军, 王博.基于CFD和混合配平算法的直升机旋翼地面效应模拟[J].航空学报, 2016, 37(8):2539-2551. http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201608020.htm

    ZHU M Y, ZHAO Q J, WANG B.The simulation of helicopter rotor in-ground-effect based on CFD method and hybrid trim algorithm[J].Acta Aeronautica et Astronautica Sinica, 2016, 37(8):2539-2551(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201608020.htm
    [20] TALBOT P D, TINLING B E, DECKER W A, et al.Mathematical model of a single main rotor helicopter for piloted simulation:NASA-TM-84281[R].Washington, D.C.:NASA, 1982.
    [21] PITT D M, PETERS D A.Theoretical prediction of dynamic inflow derivatives[J].Vertica, 1981, 5(1):21-34. http://industry.wanfangdata.com.cn/dl/Detail/ExternalResource?id=njhkht201502005%5e10
    [22] 代冀阳, 吴国辉, 朱国民.适于直升机配平计算的混合遗传算法[J].飞行力学, 2010, 28(1):24-27. http://www.cnki.com.cn/Article/CJFDTOTAL-FHLX201001007.htm

    DAI J Y, WU G H, ZHU G M.Equilibrium computation of helicopters used by hybrid genetic algorithm[J].Flight Dynamics, 2010, 28(1):24-27(in Chinese). http://www.cnki.com.cn/Article/CJFDTOTAL-FHLX201001007.htm
    [23] BALLINM G.Validation of a real-time engineering simulation of the UH-60A helicopter:NASA-TM-88360[R].Washington, D.C.:NASA, 1987.
    [24] HOWLETT J J.UH-60A black hawk engineering simulation program:VolumeⅠ-Mathematical model:NASA CR-166309[R].Washington, D.C.:NASA, 1981.
    [25] DREIER M E.Introduction to helicopter and tiltrotor flight simulation[M].Reston:AIAA, 2007:328.
  • 加载中
图(8)
计量
  • 文章访问数:  389
  • HTML全文浏览量:  2
  • PDF下载量:  376
  • 被引次数: 0
出版历程
  • 收稿日期:  2016-10-27
  • 录用日期:  2017-02-06
  • 刊出日期:  2017-10-20

目录

    /

    返回文章
    返回
    常见问答