基于滑模控制律的机翼极限环主动抑制

王诗其; 张征; 宋晨; 杨超; 郑焱午

doi:10.13700/j.bh.1001-5965.2023.0376

基于滑模控制律的机翼极限环主动抑制

doi: 10.13700/j.bh.1001-5965.2023.0376

王诗其^{1, 2},
张征¹,
宋晨^2, ,,
杨超²,
郑焱午¹

1.
中国商用飞机有限责任公司北京民用飞机技术研究中心，北京 102211
2.
北京航空航天大学航空科学与工程学院，北京 100191

基金项目:

国家自然科学基金(11402013)

详细信息

通讯作者:
E-mail：songchen@buaa.edu.cn

中图分类号: V215.3
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- 文章访问数: 24
- HTML全文浏览量: 2
- PDF下载量: 6
- 被引次数: 0
出版历程
- 收稿日期: 2023-06-15
- 录用日期: 2023-10-30
- 网络出版日期: 2023-11-17
- 整期出版日期: 2025-06-30

Limit cycle oscillation suppression of an airfoil based on sliding mode control law

1.
COMAC Beijing Aircraft Technology Research Institute，Beijing 102211，China
2.
School of Aeronautic Science and Engineering，Beihang University，Beijing 100191，China

Funds:

National Natural Science Foundation of China (11402013)

More Information

Corresponding author: E-mail：songchen@buaa.edu.cn

摘要

摘要:
间隙非线性机翼系统在一定速度范围内会发生极限环振荡，传统线性控制律对极限环抑制效果通常不显著且鲁棒性不足，因此，需设计相应的非线性控制律来提高系统的控制效果及鲁棒性。通过对间隙非线性二元翼段气动弹性系统进行线性二次调节(LQR)控制律设计，结果显示：极限环速度范围由11.4～16.9 m/s优化至12.9～19.2 m/s。同时，对间隙非线性二元翼段气动弹性系统进行滑模控制律(SMC)设计，结果显示：极限环速度范围由11.4～16.9 m/s优化至29.4～39.3 m/s。算例结果表明：针对间隙非线性系统，所设计SMC效果优于LQR控制律。
- 间隙非线性 /
- 极限环振荡 /
- 控制律 /
- 线性二次调节 /
- 滑模控制律
Abstract:
Limit cycle oscillation happens in airfoil systems with freeplay nonlinearity within a specific velocity range. Because the traditional linear control law’s limit cycle suppression effect is typically insignificant and its robustness is insufficient, a corresponding nonlinear control law must be designed in order to improve the system’s control effect and robustness. According to this article, the limit cycle speed range is optimized between 11.4−16.9 m/s and 12.9−19.2 m/s. The linear quadratic regulartor (LQR) control law is created for the 2D airfoil aeroelastic system with freeplay nonlinearity. At the same time, the sliding mode control law (SMC) is designed for the 2D airfoil aeroelastic system with freeplay nonlinearity above, it shows that the speed range of the limit cycle is optimized from 11.4−16.9 m/s to 29.4−39.3 m/s. The result of the calculating example shows that the SMC law is better than that of LQR for nonlinear systems in this paper.
- freeplay nonlinearity /
- limit cycle oscillation /
- control law /
- linear quadratic regulator /
- sliding mode control law

HTML全文

图 1 二元翼段^[13]

Figure 1. Two-dimensional airfoil^[13]

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图 2 位移-力关系曲线^[11]

Figure 2. Displacement-force curve^[11]

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图 3 闭环系统框图（LQR）

Figure 3. Block diagram of closed loop system (LQR)

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图 4 闭环系统框图（SMC）

Figure 4. Block diagram of closed loop system (SMC)

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图 5 线性系统开环响应（速度为16.9 m/s）

Figure 5. Open-loop response of linear system (the speed is 16.9 m/s)

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图 6 非线性系统开环响应（速度为16 m/s）

Figure 6. Open-loop response of nonlinear system (the speed is 16 m/s)

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图 7 线性系统闭环响应（LQR, 速度为16.9 m/s）

Figure 7. Closed-loop response of linear system (LQR, the speed is 16.9 m/s)

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图 8 线性系统闭环响应（LQR, 速度为24.9 m/s）

Figure 8. Closed-loop response of linear system (LQR, the speed is 24.9 m/s)

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图 9 非线性系统闭环响应（LQR, 速度为16 m/s）

Figure 9. Closed-loop response of nonlinear system (LQR, the speed is 16 m/s)

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图 10 非线性系统闭环响应（LQR, 速度为24.9 m/s）

Figure 10. Closed-loop response of nonlinear system (LQR, the speed is 24.9 m/s)

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图 11 线性系统闭环响应（SMC, 速度为24.9 m/s）

Figure 11. Closed-loop response of linear system (SMC, the speed is 24.9 m/s)

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图 12 线性系统闭环响应（SMC, 速度为39.3 m/s）

Figure 12. Closed-loop response of linear system (SMC, the speed is 39.3 m/s)

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图 13 非线性系统闭环响应（SMC, 速度为24.9 m/s）

Figure 13. Closed-loop response of nonlinear system (SMC, the speed is 24.9 m/s)

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图 14 非线性系统闭环响应（SMC, 速度为29.4 m/s）

Figure 14. Closed-loop response of nonlinear system (SMC, the speed is 29.4 m/s)

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表 1 二元翼段参数^[14]

Table 1. Parameters of two-dimensional airfoil^[14]

参数	数值	参数	数值
a	−0.68	b/m	0.135
m/kg	12.387	I_α	0.065
x_α	0.3267	c_h/(N·s·m⁻¹)	27.43
c_α/(N·s)	0.036	c_lβ	3.358
c_mβ	−0.635	ρ/(kg·m⁻³)	1.225
k_h/(N·m⁻¹)	2884.4	k	28

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