弹性前掠翼开裂式方向舵操纵特性分析

马斌麟; 苏新兵; 冯浩洋; 王宁; 张亚光

doi:10.13700/j.bh.1001-5965.2017.0142

弹性前掠翼开裂式方向舵操纵特性分析

doi: 10.13700/j.bh.1001-5965.2017.0142

马斌麟¹,
苏新兵^1, ,,
冯浩洋^{1, 2},
王宁¹,
张亚光¹

1.
空军工程大学航空航天工程学院, 西安 710038
2.
中国人民解放军93427部队, 北京 101100

基金项目:

国家自然科学基金 11402301

陕西省自然科学基础研究计划 2015JM1005

详细信息

作者简介:
马斌麟男, 硕士研究生; 主要研究方向:飞行器设计及计算流体力学

苏新兵男, 博士, 副教授, 硕士生导师; 主要研究方向:飞行器设计及计算流体力学

通讯作者:
苏新兵, E-mail:sxinbing01@163.com

中图分类号: V221.3
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出版历程
- 收稿日期: 2017-03-13
- 录用日期: 2017-05-24
- 网络出版日期: 2017-09-20

Control characteristics analysis of split rudder of elastic forward swept wing

1.
College of Aeronautics and Astronautics Engineering, Air Force Engineering University, Xi'an 710038, China
2.
Unit 93427, The Chinese People's Liberation Army, Beijing 101100, China

Funds:

National Natural Science Foundation of China 11402301

Natural Science Basic Research Plan in Shaanxi Province of China 2015JM1005

More Information

Corresponding author: SU Xinbing, E-mail:sxinbing01@163.com

摘要

摘要:
针对机翼弹性变形对前掠翼（FSW）飞行器开裂式方向舵操纵特性的影响，基于计算流体力学/计算结构力学（CFD/CSD）松耦合静气动弹性数值计算方法，计算了亚声速条件下刚性和弹性前掠机翼开裂式方向舵的操纵特性，并分析了机翼弯扭变形对方向舵操纵特性的影响。计算结果表明，右侧开裂式方向舵打开后，与刚性翼相比，弹性翼的失速迎角提前约2°，达到最大升阻比的迎角提前约1°，小迎角时偏航作用增强，出现右滚力矩和滚转力矩"凹坑"现象，大迎角时偏航规律趋势提前约8°，滚转作用加剧；侧滑角增大时，偏航力矩减小的幅度大于刚性翼，滚转力矩完全反效；舵偏角增大时，偏航力矩的增幅小于刚性翼。经比较，在弹性变形影响下，弹性前掠翼的开裂式方向舵操纵特性与刚性前掠翼有明显区别。
- 前掠翼(FSW) /
- 弹性变形 /
- 计算流体力学/计算结构力学(CFD/CSD)松耦合 /
- 开裂式方向舵 /
- 操纵特性
Abstract:
Aimed at the influence of elastic deformation on the control characteristics of split rudder for the forward swept wing (FSW) aircraft, the computational fluid dynamics/computational structural dynamics (CFD/CSD) loose coupling static aeroelastic numerical calculation method was adopted. The calculation and analysis on control characteristics of the split rudder with rigid and elastic wings were performed under the subsonic condition. The simulation had highlighted the influence of wing deformation on the control characteristics of the rudder. The calculation result shows that, when the right side split rudder opens, compared with rigid wing, the stall attack angle of the elastic wing advances about 2°, the attack angle of maximum lift-drag ratio advances about 1°, the yaw effect at small attack angle is enhanced, the "pits" phenomenon of right-roll moment and roll moment appears, and the trend of yaw at high angle of attack advances about 8° with more violent roll action; under the influence of sideslip, the decrease extent of the yawing moment with the increase of sideslip angle is larger than that of the rigid wing, and the roll moment has completely opposite result; under the action of down moment proving by rudder, the increase extent of the yawing moment with the increase of sideslip angle is larger than that of the rigid wing. By comparison, the control characteristics of split rudder for the elastic FSW have a distinct difference with rigid FSW.
- forward swept wing (PSW) /
- elastic deformation /
- computational fluid dynamics/computational structural dynamics (CFD/CSD) loose coupling /
- split rudder /
- control characteristics

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图 1 HIRENASD流场和结构网格

Figure 1. Flow field and structure grids of HIRENASD

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图 2 不同y/b时的压力系数

Figure 2. Pressure coefficient of different y/b

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图 3 前掠翼模型及舵偏角示意图

Figure 3. Schematic of FSW model and rudder deflection angle

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图 4 计算模型

Figure 4. Computational model

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图 5 前掠翼流场和结构网格

Figure 5. Flow field and structure grids of FSW

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图 6 升阻特性

Figure 6. Lift-drag characteristics

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图 7 机翼展向扭转角

Figure 7. Torsional angle of wing along spanwise direction

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图 8 机翼展向弯曲挠度

Figure 8. Bending deflection of wing along spanwise direction

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图 9 翼梢处扭转角响应

Figure 9. Response of torsional angle of wing tip

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图 10 压力云图

Figure 10. Pressure contour

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图 11 偏航力矩特性

Figure 11. Yawing moment characteristics

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图 12 滚转力矩特性

Figure 12. Rolling moment characteristics

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图 13 升力系数

Figure 13. Lift coefficient

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图 14 侧滑偏航特性

Figure 14. Side slip yawing characteristics

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图 15 侧滑时的展向扭转角

Figure 15. Torsional angle with side slip along spanwise direction

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图 16 侧滑滚转特性

Figure 16. Side slip rolling characteristics

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图 17 偏航力矩系数增量及偏航操纵效率随舵偏角的变化

Figure 17. Variation of increment of yawing moment coefficient and yaw control efficiency with rudder deflection angle

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图 18 滚转力矩系数随舵偏角的变化

Figure 18. Variation of rolling moment coefficient with rudder deflection angle

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表 1 前掠翼飞行器的典型飞行状态

Table 1. Typical flight state of FSW aircraft

飞行状态	H/km	Ma
起飞	0	0.2
巡航	10	0.8
空战	5	0.5

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表 2 前掠翼阻力系数增量

Table 2. Increment of drag coefficient for FSW

δ/(°)	ΔC_D/%
δ/(°)	刚性翼	弹性翼
10	10.20	7.55
20	23.64	19.89
30	41.43	35.18

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