基于特征根有界摄动分析的高超声速飞行器双通道控制

杨雨宸; 张增辉; 闫佳宁; 张晶; 杨凌宇

doi:10.13700/j.bh.1001-5965.2021.0053

基于特征根有界摄动分析的高超声速飞行器双通道控制

doi: 10.13700/j.bh.1001-5965.2021.0053

1.
北京航空航天大学自动化科学与电气工程学院, 北京 100083
2.
北京机电工程总体设计部, 北京 100854

基金项目:

国家自然科学基金 61273099

国家自然科学基金 61304030

详细信息

通讯作者:
杨凌宇, E-mail: yanglingyu@buaa.edu.cn

中图分类号: V249.12
计量
- 文章访问数: 383
- HTML全文浏览量: 126
- PDF下载量: 28
- 被引次数: 0
出版历程
- 收稿日期: 2021-01-31
- 录用日期: 2021-02-10
- 网络出版日期: 2021-02-24
- 整期出版日期: 2022-10-20

Dual-channel control of hypersonic flight vehicles based on bounded perturbation analysis of eigenvalues

1.
School of Automation Science and Electrical Engineering, Beihang University, Beijing 100083, China
2.
Beijing System Design Institute of the Electro-mechanic Engineering, Beijing 100854, China

Funds:

National Natural Science Foundation of China 61273099

National Natural Science Foundation of China 61304030

More Information

Corresponding author: YANG Lingyu, E-mail: yanglingyu@buaa.edu.cn

摘要

摘要:
针对双通道控制高超声速飞行器横侧向欠驱动、强不确定性的特点，研究了适用于工程应用的控制策略，提出一种基于特征根有界摄动分析的反馈控制鲁棒性分析方法。基于线性化近似分析和工程约束需求，给出了双通道飞行器改善荷兰滚模态动态的2种控制策略，分别为极点配置方案和模态解耦方案。提出了特征根灵敏度矩阵和有界摄动矩阵的概念，用于评估闭环系统对参数不确定的鲁棒性。基于闭环六自由度模型在标称及参数拉偏情况下，对2种方案进行了综合分析和仿真验证。仿真结果表明，2种控制方案均可以解决双通道控制问题，所提特征根有界摄动分析方法可准确评估系统的鲁棒性。
- 高超声速飞行器 /
- 双通道控制 /
- 欠驱动系统 /
- 荷兰滚模态 /
- 特征根灵敏度矩阵 /
- 特征根有界摄动矩阵
Abstract:
Considering the underactuated hypersonic flight vehicles with strong uncertainty of the dual channel attitude control strategy, practical feedback-based dual-channel control schemes are given and the robustness analysis method based on the bounded perturbation analysis of eigenvalues is proposed. Firstly, two control schemes, namely the pole-assignment schemes and modes-decoupling scheme, are given to improve Dutch roll dynamics based on the approximate linearization approach and engineering constraints. Then, to evaluate the robustness of the closed-loop system for the uncertain parameters, the eigenvalue sensitivity matrix, the eigenvalue bounded-perturbation-matrix and eigenvalue bounded-perturbation index are proposed. Finally, simulations and analysis of the proposed schemes and methods are given based on the closed-loop six degree-of-freedom model with nominal parameters and perturbed parameters, respectively. Simulation results demonstrate that both schemes could solve the dual-channel control issue. The results also show that the perturbation analysis of eigenvalues could precisely evaluate the system robustness.
- hypersonic flight vehicles /
- dual-channel control /
- underactuated system /
- Dutch roll mode /
- eigenvalue sensitivity matrix /
- eigenvalue bounded-perturbation-matrix

HTML全文

图 1 Winged-Cone气动布局^[12]

Figure 1. Winged-Cone pneumatic layout^[12]

下载: 全尺寸图片幻灯片

图 2 螺旋与滚转阻尼模态极点

Figure 2. Spiral mode and roll-damping mode poles

下载: 全尺寸图片幻灯片

图 3 荷兰滚阻尼比随迎角和马赫数变化曲线

Figure 3. Dutch roll damping ratio with angle of attack and Mach number

下载: 全尺寸图片幻灯片

图 4 气动系数随马赫数变化曲线

Figure 4. Aerodynamic coefficients with Mach number

下载: 全尺寸图片幻灯片

图 5 飞行包线内ξ相对估计误差

Figure 5. Relative estimation error of ξ in flight envelope

下载: 全尺寸图片幻灯片

图 6 飞行包线内ω相对估计误差

Figure 6. Relative estimation error of ω in flight envelope

下载: 全尺寸图片幻灯片

图 7 方案1极点受L′_p扰动的影响

Figure 7. Poles of method 1 vary with L′_p

下载: 全尺寸图片幻灯片

图 8 方案1倾侧角响应

Figure 8. Bank angle response of method 1

下载: 全尺寸图片幻灯片

图 9 方案1侧滑角响应

Figure 9. Sideslip angle response of method 1

下载: 全尺寸图片幻灯片

图 10 方案1舵面响应

Figure 10. Aileron response of method

下载: 全尺寸图片幻灯片

图 11 方案2极点受扰动的影响

Figure 11. Poles of method 2 vary with uncertainties

下载: 全尺寸图片幻灯片

图 12 方案2倾侧角响应

Figure 12. Bank angle response of method 2

下载: 全尺寸图片幻灯片

图 13 方案2侧滑角响应

Figure 13. Sideslip angle response of method 2

下载: 全尺寸图片幻灯片

图 14 方案2舵面响应

Figure 14. Aileron response of method 2

下载: 全尺寸图片幻灯片

表 1 Winged-Cone主要参数

Table 1. Key parameters of Winged-Cone

参数	数值
S/m²	334.73
c/m	24.384
b/m	18.288
m/kg	136 080
I_x/(kg·m²)	915 300
I_y/(kg·m²)	9 036 000
I_z/(kg·m²)	9 036 000
X_cg/m	-3.5

下载: 导出CSV

参考文献(15)

[1]	任章, 白辰. 高超声速飞行器飞行控制技术研究综述[J]. 导航定位与授时, 2015, 2(6): 1-6. doi: 10.3969/j.issn.2095-8110.2015.06.001 REN Z, BAI C. The overview of difficulties and methods of hypersonic vehicle flight control[J]. Navigation Positioning and Timing, 2015, 2(6): 1-6(in Chinese). doi: 10.3969/j.issn.2095-8110.2015.06.001
[2]	XU B, SHI Z K. An overview on flight dynamics and control approaches for hypersonic vehicles[J]. Science China: Information Sciences, 2015, 58: 1-19.
[3]	WALKER S, SHERK J, SHELL D, et al. The DARPA/AF falcon program: The hypersonic technology vehicle #2 (HTV-2) flight demonstration phase: AIAA 2008-2539[R]. Reston: AIAA, 2008: 104526.
[4]	SACHAN K, PADHI R. Nonlinear robust neuro-adaptive flight control for hypersonic vehicles with state constraints[J]. Control Engineering Practice, 2020, 102: 104526. doi: 10.1016/j.conengprac.2020.104526
[5]	ZHU S P, XU T, WEI C S, et al. Learning-based adaptive fault tolerant control for hypersonic flight vehicles with abrupt actuator faults and finite time prescribed tracking performance[J]. European Journal of Control, 2021, 58: 17-26. doi: 10.1016/j.ejcon.2020.12.003
[6]	ZHOU L L, LIU L, CHENG Z T, et al. Adaptive dynamic surface control using neural networks for hypersonic flight vehicle with input nonlinearities[J]. Optimal Control Applications and Methods, 2020, 41(6): 1904-1927. doi: 10.1002/oca.2584
[7]	YANG Y H, SHAO X L, SHI Y. Back-stepping robust control for flexible air-breathing hypersonic vehicle via α-filter-based uncertainty and disturbance estimator[J]. International Journal of Control Automation and Systems, 2021, 19(1): 1-14. doi: 10.1007/s12555-019-0324-x
[8]	WANG Z, BAO W, LI H. Second-order dynamic sliding-mode control for nonminimum phase underactuated hypersonic vehicles[J]. IEEE Transactions on Industrial Electronics, 2017, 64(4): 3105-3112. doi: 10.1109/TIE.2016.2633530
[9]	史丽楠, 李惠峰, 张冉. 滑翔再入飞行器横侧向耦合姿态控制策略[J]. 北京航空航天大学学报, 2016, 42(1): 120-129. doi: 10.13700/j.bh.1001-5965.2015.0037 SHI L N, LI H F, ZHANG R. Gliding reentry vehicle lateral/directional coupling attitude control strategy[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(1): 120-129(in Chinese). doi: 10.13700/j.bh.1001-5965.2015.0037
[10]	LI X Q, ZHOU J. Attitude tracking of the under-actuated reentry vehicle with actuator saturation[J]. Fire Control and Command Control, 2016, 41(12): 15-19.
[11]	YE L Q, ZONG Q, CRASSIDIS J L, et al. Output-redefinition-based dynamic inversion control for a nonminimum phase hypersonic vehicle[J]. IEEE Transactions on Industrial Electronics, 2018, 65(4): 3447-3457. doi: 10.1109/TIE.2017.2760246
[12]	KESHMIRI S, COLGREN R, MIRMIRANI M. Six DoF nonlinear equations of motion for a heneric hypersonic vehicle: AIAA 2007-6626[R]. Reston: AIAA, 2007.
[13]	SNELL S A, ENNS D F, GARRARD W L. Nonlinear inversion flight control for a supermaneuverable aircraft[J]. Journal of Guidance, Control, and Dynamics, 1992, 15(4): 976-984. doi: 10.2514/3.20932
[14]	吴森堂. 飞行控制系统[M]. 2版. 北京: 北京航空航天大学出版社, 2013: 99-101. WU S T. Flight control system[M]. 2nd ed. Beijing: Beihang University Press, 2013: 99-101(in Chinese).
[15]	RUDISILL C S. Derivatives of eigenvalues and eigenvectors for a general matrix[J]. AIAA Journal, 1974, 12(5): 721-722.