基于状态空间涡格法的阵风减缓分析

杨澜; 安朝; 谢长川; 杨超

doi:10.13700/j.bh.1001-5965.2021.0023

基于状态空间涡格法的阵风减缓分析

doi: 10.13700/j.bh.1001-5965.2021.0023

北京航空航天大学航空科学与工程学院, 北京 100083

详细信息

通讯作者:
安朝, E-mail: ac@buaa.edu.cn

中图分类号: V215.3
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- 被引次数: 0
出版历程
- 收稿日期: 2021-01-15
- 录用日期: 2021-03-19
- 网络出版日期: 2021-04-27
- 整期出版日期: 2022-07-20

Gust load alleviation analysis based on vortex lattice method in state-space form

School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China

More Information

Corresponding author: AN Chao, E-mail: ac@buaa.edu.cn

摘要

摘要:
阵风响应计算及阵风减缓控制系统设计是飞行器气动弹性分析中的重要内容。基于状态空间涡格法（VLM）建立飞行器阵风气动力模型，给出有限元结构模态及控制面模态广义自由度与涡格法控制点边界条件的插值关系，建立适用于复杂模型的阵风响应分析方法，弥补了传统阵风响应分析方法需要进行有理函数拟合或迭代计算资源消耗大等不足。在此基础上，基于经典PID控制方法设计阵风减缓控制系统，仿真得到离散阵风及von Karman连续阵风激励下的系统开/闭环时域响应情况，对比响应幅值计算减缓率。仿真计算结果表明：根据所提方法建立的阵风响应分析方法准确，阵风减缓控制系统能有效降低原气动弹性系统的阵风响应。
- 气动弹性 /
- 气动伺服弹性 /
- 阵风响应 /
- 阵风减缓控制系统 /
- 涡格法(VLM)
Abstract:
Gust response and gust load alleviation control system design is an important issue in aeroelasticity. This paper presents a gust response model based on the vortex lattice method (VLM) in state-space formulation and gives the couple relationships between finite element method modes/control surface modes and boundary conditions of VLM, which can be applied to complicated aircraft model. This method can avoid the disadvantages of the traditional gust response analysis method with no requirement of rational function assessment and iteration calculation with lots of resources. Introducing the traditional PID control algorithm, a gust load alleviation system is given, and gust time response of open loop/closed loop under a discrete gust and von Karman continuum gust excitation are presented. The alleviation effect can be solved by contrasting the response amplitude. The simulation results show that gust response analysis results based on this method are accurate and the gust load alleviation control system can alleviate the load response of the original aeroelastic system effectively.
- aeroelasticity /
- aeroservoelasticity /
- gust response /
- gust load alleviation control system /
- vortex lattice method (VLM)

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图 1 涡格法涡环示意图

Figure 1. Illustration of vortex ring in VLM

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图 2 离散阵风风场剖面示意图

Figure 2. Schematic diagram of discrete gust filed

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图 3 阵风减缓控制方案

Figure 3. Gust alleviation control scheme

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图 4 柔性机翼CAD模型

Figure 4. CAD model of flexible wing

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图 5 柔性机翼有限元模型

Figure 5. Finite element model of flexible wing

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图 6 柔性机翼气动面模型

Figure 6. Aerodynamics model of flexible wing

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图 7 不同风速下位移时域响应

Figure 7. Displacement response with different velocities

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图 8 ZAERO颤振分析结果

Figure 8. Flutter analysis results from ZAERO

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图 9 风速32 m/s下加速度时域响应

Figure 9. Acceleration response in time domain (V=32 m/s)

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图 10 风速32 m/s下位移时域响应

Figure 10. Displacement response in time domain (V=32 m/s)

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图 11 风速28 m/s下加速度时域响应

Figure 11. Acceleration response in time domain (V=28 m/s)

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图 12 风速28 m/s下位移时域响应

Figure 12. Displacement response in time domain (V=28 m/s)

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图 13 PID控制参数

Figure 13. PID controller parameters

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图 14 风速32 m/s下开/闭环时域加速度响应

Figure 14. Open/close loop acceleration response (V=32 m/s)

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图 15 风速32 m/s下开/闭环时域位移响应

Figure 15. Open/close loop displacement response (V=32 m/s)

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图 16 风速28 m/s下开/闭环时域加速度响应

Figure 16. Open/close loop acceleration response (V=28 m/s)

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图 17 风速28 m/s下开/闭环时域位移响应

Figure 17. Open/close loop displacement response (V=28 m/s)

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图 18 连续阵风时域加速度响应

Figure 18. Acceleration response with continuum gust

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图 19 连续阵风时域位移响应

Figure 19. Displacement response with continuum gust

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表 1 柔性机翼设计参数

Table 1. Design parameters of the wing model

参数	数值
质量/kg	2.819 9
半展长/m	1.542
翼根弦长/m	0.261
翼梢弦长/m	0.069
扭转角/(°)	-2.0
展弦比	9.3
翼型	超临界翼型

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表 2 柔性机翼模型主要模态信息

Table 2. Modes analysis results of the wing model

模态阶数	模态频率/Hz	模态特征
1	3.35	垂直一弯
2	5.18	水平一弯
3	10.05	垂直二弯
4	17.17	水平二弯
5	25.68	垂直三弯
6	33.05	一阶扭转

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表 3 风速32 m/s下计算结果对比

Table 3. Results contrast with 32 m/s velocity

方法	位移响应/mm	加速度响应/(m·s^-2)
状态空间涡格法	20.45	9.80
ZAERO	19.37	9.59
偏差/%	5.6	2.2

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表 4 风速28 m/s下计算结果对比

Table 4. Results contrast with 28 m/s velocity

方法	位移响应/mm	加速度响应/(m·s^-2)
状态空间涡格法	19.18	9.43
ZAERO	18.32	9.14
偏差/%	4.7	3.2

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