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推力矢量型V/STOL飞行器动态过渡过程的操纵策略优化

周涛 王子安 龚正 佘崇民 赵彤 张同任

周涛, 王子安, 龚正, 等. 推力矢量型V/STOL飞行器动态过渡过程的操纵策略优化[J]. 航空动力学报, 2023, 38(2):408-419 doi: 10.13224/j.cnki.jasp.20210412
引用本文: 周涛, 王子安, 龚正, 等. 推力矢量型V/STOL飞行器动态过渡过程的操纵策略优化[J]. 航空动力学报, 2023, 38(2):408-419 doi: 10.13224/j.cnki.jasp.20210412
ZHOU Tao, WANG Zian, GONG Zheng, et al. Control strategy optimization of dynamic transition processes of thrust-vectored V/STOL aircraft[J]. Journal of Aerospace Power, 2023, 38(2):408-419 doi: 10.13224/j.cnki.jasp.20210412
Citation: ZHOU Tao, WANG Zian, GONG Zheng, et al. Control strategy optimization of dynamic transition processes of thrust-vectored V/STOL aircraft[J]. Journal of Aerospace Power, 2023, 38(2):408-419 doi: 10.13224/j.cnki.jasp.20210412

推力矢量型V/STOL飞行器动态过渡过程的操纵策略优化

doi: 10.13224/j.cnki.jasp.20210412
基金项目: 国家自然科学基金(11402115); 江苏高校优势学科建设工程资助项目
详细信息
    作者简介:

    周涛(1998-),男,硕士生,主要从事飞机飞行动力学与控制研究

  • 中图分类号: V249.1

Control strategy optimization of dynamic transition processes of thrust-vectored V/STOL aircraft

  • 摘要:

    针对推力矢量型垂直/短距起降(vertical/short takeoff and landing, V/STOL)飞行器的动态过渡过程模型,综合考虑过渡走廊限制、操纵冗余及不同起降任务需求指标,研究最优过渡操纵策略。考虑V/STOL 飞行器的喷射气流效应,对飞行器进行全量动力学建模。利用可达平衡集方法,建立通用过渡走廊计算框架。设计了能够在V/STOL过渡段和高速飞行间平稳过渡的操纵方式。将推力矢量飞行器的动态倾转过渡过程转化为非线性动态最优控制问题,根据不同起降任务特点建立合理的指标和约束,采用直接转换法和序列二次规划算法进行求解,得出不同任务特点下的最优操纵策略与过渡过程。采用可达平衡集计算过渡走廊的方法,不仅不受飞行器类型的限制,更简化了构造过程,具有良好的通用性与鲁棒性。以光滑过渡为目标的优化结果使得飞行员在飞行器过渡过程中的操纵量变化大幅减小,从而使得飞行员能更加专注于对飞行器运动的操纵;以距离更短为目标的优化结果则使得降落过程的飞行距离缩短了30%左右。从操纵策略出发的优化结果使得驾驶员能够更好掌握操纵关注点及边界,增加了整个动态过渡过程的安全性。

     

  • 图 1  F-35B缩比模型图

    Figure 1.  Reduced ratio F-35B aircraft model

    图 2  动力系统纵向操纵原理

    Figure 2.  Longitudinal control principle of power system

    图 3  倾转过渡走廊计算流程

    Figure 3.  Computional flowchart for conversion corridor

    图 4  V/STOL飞行器的倾转过渡走廊

    Figure 4.  Conversion corridor of V/STOL aircraft

    图 5  短距起飞倾转过渡过程最优解

    Figure 5.  Optimal solution for tilting transition process of short take-off

    图 6  垂直起飞倾转过渡过程最优解

    Figure 6.  Optimal solution for tilting transition process of vertical take-off

    图 7  短距降落倾转过渡过程最优解

    Figure 7.  Optimal solution for tilting transition process of short landing

    表  1  缩比F35-B主要参数

    Table  1.   Main characteristics of reduced ratio F-35B

    参数数值
    ${d_{ {\text{tf} } } }/{\rm{m}}$0.476
    ${d_{ {\text{tn} } } }/{\rm{m}}$0.561
    ${x}_{0} /{\rm{m}}$0.513
    ${\textit z}_{0} /{\rm{m} }$0.100
    ${l}_{0}/{\rm{m}}$0.141
    ${{\textit z}_{\text{n} } }/{\rm{m} }$0.100
    下载: 导出CSV

    表  2  执行器饱和参数

    Table  2.   Actuator saturation parameters

    参数最大值
    ${\delta }_{ {\rm{e} } }/(\text{°})$[−30, 30]
    ${T_{\text{f} } }/{\rm{N}}$[0, 79.6]
    ${T_{\text{n} } }/{\rm{N}}$[0, 79]
    ${\delta _{\text{n} } }/(\text{°})$[0, 90]
    下载: 导出CSV

    表  3  全过程的操纵设计

    Table  3.   Whole process of control design

    驾驶杆油门杆脚蹬滚轮
    纵向横向
    ${ {\textit z}_{\rm{e}}}$轴速度${y_{\rm{e}}}$轴速度${x_{\rm{e}}}$轴速度${ {\textit z}_{\rm{e}}}$轴角速度矢量喷管倾
    转角速度 ($ {\delta }_{4} $)
    俯仰角
    加速度($ {\delta }_{3} $)
    滚转角
    速度
    ${x_{\rm{b}}}$轴
    加速度($ {\delta }_{1} $)
    方向舵
    升降舵副翼矢量喷管
    推力
    方向舵
    下载: 导出CSV

    表  4  约束参数

    Table  4.   Constraint parameters

    参数数值参数数值
    $ t $25 $ N $46
    $ {{\boldsymbol{\dot X}}_{\min }} $[−5,−2,−5,−5] $ {{\boldsymbol{\dot X}}_{\max }} $[5,2,5,5]
    $ {{\boldsymbol{\ddot X}}_{\min }} $[−0.3,−0.3,−0.1,−0.8] $ {{\boldsymbol{\ddot X}}_{\max }} $[0.3,0.3,0.1,0.8]
    $ {{\boldsymbol{\dot U}}_{\min }} $[−3,−4,−5,−3] $ {{\boldsymbol{\dot U}}_{\max }} $[3,4,5,3]
    $ {{\boldsymbol{\ddot U}}_{\min }} $[−1,−1,−1,−0.5] $ {{\boldsymbol{\ddot U}}_{\max }} $[1,1,1,0.5]
    下载: 导出CSV
  • [1] SADDINGTON A J,KNOWLES K. A review of out-of-ground-effect propulsion-induced interference on STOVL aircraft[J]. Progress in Aerospace Sciences,2005,41(3): 175-191.
    [2] MARGASON R,ARLEDGE T,WARDWELL D,et al.Jet efflux characteristics and their influence on STOVL aircraft propulsion-induced effects[R].SAE Technical Paper 962250,1996.
    [3] BUCHHOLZ M D.Highlights of the JSF X-35 STOVL jet effects test effort[R].AIAA-2002-5962, 2002.
    [4] 郑志成,周洲. 垂直起降飞机设计中升力风扇估算模型分析[J]. 飞行力学,2010,28(3): 21-23. doi: 10.13645/j.cnki.f.d.2010.03.006

    ZHENG Zhicheng,ZHOU Zhou. Analysis of the estimation model of lift fan when designing VTOL[J]. Flight Dynamics,2010,28(3): 21-23. (in Chinese) doi: 10.13645/j.cnki.f.d.2010.03.006
    [5] KUHN R F,MARGASON R J,CURTIS P. Jet-induced effects the aerodynamics of jet-and fan-powered V/STOL aircraft in hover and transition[M].Reston, VA, US: AIAA, 2005: 13-52.
    [6] 王向阳,朱纪洪,张义军. 推力矢量型V/STOL飞机动力学建模与分析[R].西安: 第三十二届中国控制会议,2013.
    [7] 祝小平,王睿,周洲. 垂直起降固定翼飞翼布局无人机过渡飞行纵向稳定性研究[J]. 西北工业大学学报,2011,29(4): 548-553. doi: 10.3969/j.issn.1000-2758.2011.04.009

    ZHU Xiaoping,WANG Rui,ZHOU Zhou. Longitudinal stability of vertical-take-off-and-landing (VTOL) fixed wing flying wing UAV during transitional flight[J]. Journal of Northwestern Polytechnical University,2011,29(4): 548-553. (in Chinese) doi: 10.3969/j.issn.1000-2758.2011.04.009
    [8] MAISEL M D,GIULIANETTI D J,DUGAN D C.The history of the XV-15 tilt rotor aircraft:from concept to flight[R].NASA SP-2000-4517,2000.
    [9] 俞志明,陈仁良,孔卫红. 倾转四旋翼飞行器倾转过渡走廊分析方法[J]. 北京航空航天大学学报,2020,46(11): 2106-2113.

    YU Zhiming,CHEN Renliang,KONG Weihong. Analysis method for conversion corridor of quad tilt rotor aircraft[J]. Journal of Beijing University of Aeronautics and Astronautics,2020,46(11): 2106-2113. (in Chinese)
    [10] 曹芸芸,陈仁良. 倾转旋翼飞行器发动机短舱倾转角度-速度包线分析[J]. 航空动力学报,2011,26(10): 2174-2180.

    CAO Yunyun,CHEN Renliang. Investigation on nacelle conversion envelope analysis method of tiltrotor aircraft[J]. Journal of Aerospace Power,2011,26(10): 2174-2180. (in Chinese)
    [11] 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)
    [12] TIAN Y,HE Y,LI X,et al.Simulation testing method of V/STOL flight control strategy[R].Beijing:the 10th World Congress on Intelligent Control and Automation,2012.
    [13] DENHAM J,PAINES J.Converging on a precision hover control strategy for the F-35B STOVL aircraft[R].AIAA-2008-6331,2008.
    [14] 王洛烽,陈仁良,严旭飞. 直升机抛放吊挂后的最优操纵与分析[J]. 航空动力学报,2021,36(3): 543-552.

    WANG Luofeng,CHEN Renliang,YAN Xufei. Optimal control and analysis for helicopter after releasing slung load[J]. Journal of Aerospace Power,2021,36(3): 543-552. (in Chinese)
    [15] 陈金鹤,汪正中,田洪源. 基于最优控制理论的倾转旋翼机跃障飞行仿真[J]. 西北工业大学学报,2020,38(6): 1266-1274. doi: 10.3969/j.issn.1000-2758.2020.06.016

    CHEN Jinhe,WANG Zhengzhong,TIAN Hongyuan. Hurdle-hop simulation of tilt-rotor aircraft based on optimal control theory[J]. Journal of Northwestern Polytechnical University,2020,38(6): 1266-1274. (in Chinese) doi: 10.3969/j.issn.1000-2758.2020.06.016
    [16] 严旭飞,陈仁良. 倾转旋翼机动态倾转过渡过程的操纵策略优化[J]. 航空学报,2017,38(7): 59-69. doi: 10.7527/S1000-6893.2017.520865

    YAN Xufei,CHEN Renliang. Control strategy optimization of dynamic conversion procedure of tilt-rotor aircraft[J]. Acta Aeronautica et Astronautica Sinica,2017,38(7): 59-69. (in Chinese) doi: 10.7527/S1000-6893.2017.520865
    [17] 程志强,朱纪洪,袁夏明,等. 推力矢量垂直短距飞机轨迹优化与控制[J]. 控制理论与应用,2020,37(1): 38-46. doi: 10.7641/CTA.2019.80515

    CHENG Zhiqiang,ZHU Jihong,YUAN Xiaming,et al. Trajectory optimization and control design for transition of thrust-vectored vertical and/or short take-off and landing aircraft[J]. Control Theory and Applications,2020,37(1): 38-46. (in Chinese) doi: 10.7641/CTA.2019.80515
    [18] 龚正. 先进飞行器非定常气动力建模、控制律设计及验证方法研究[D].南京:南京航空航天大学,2011.

    GONG Zheng.Research on unsteady aerodynamic modeling,control law design and clearance for advanced aerospace vehicle[D].Nanjing: Nanjing University of Aeronautics and Astronautics,2011.(in Chinese)
    [19] 叶辉.推力矢量飞机过失速机动的鲁棒控制与边界保护[D].南京:南京航空航天大学,2016.

    YE Hui. Robust control and envelope protection for post-stall maneuver of TVC aircraft[D].Nanjing: Nanjing University of Aeronautics and Astronautics,2016. (in Chinese)
    [20] GOMAN M G,KHRAMTSOVSKY A V,KOLESNIKOV E N. Evaluation of aircraft performance and maneuverability by computation of attainable equilibrium sets[J]. Journal of Guidance,Control,and Dynamics,2008,31(2): 329-339. doi: 10.2514/1.29336
    [21] GILL P E,MURRAY W,SAUNDERS M A.User’s guide for SNOPT version 7: software for large-scale nonlinear programming[D].San Diego, US: University of California,2007.
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出版历程
  • 收稿日期:  2021-08-02
  • 网络出版日期:  2022-10-24

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