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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
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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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