变体航行器动力学建模与仿真

颜奇民; 胡俊华; 陈国明; 刘安; 张强

doi:10.13700/j.bh.1001-5965.2020.0496

变体航行器动力学建模与仿真

doi: 10.13700/j.bh.1001-5965.2020.0496

空军工程大学航空工程学院, 西安 710038

基金项目:

国家自然科学基金 51779263

详细信息

通讯作者:
胡俊华, E-mail: hjh_air@163.com

中图分类号: V212.1;TJ760.1
计量
- 文章访问数: 532
- HTML全文浏览量: 132
- PDF下载量: 63
- 被引次数: 0
出版历程
- 收稿日期: 2020-09-04
- 录用日期: 2020-10-16
- 网络出版日期: 2021-12-20

Dynamic modeling and simulation of morphing vehicle

Aeronautics Engineering College, Air Force Engineering University, Xi'an 710038, China

Funds:

National Natural Science Foundation of China 51779263

More Information

Corresponding author: HU Junhua, E-mail: hjh_air@163.com

摘要

摘要:
针对部分变体航行器变体描述复杂、存在刚体与柔性体耦合导致动力学模型复杂的问题，推导了一种具有普遍适用性的变体航行器动力学方程。将航行器视为由质点组成的整体，建立每个质点的运动微分方程。采用积分思想得到了适用于变体航行器的动力学扩展方程，其中，航行器变体产生的影响可以用附加力与附加力矩描述。对一种具有柔性翼的共形半环翼变体航行器进行了纵向面内开环运动仿真。针对部分附加力与附加力矩难以准确计算的问题，提出了一种便于工程化快速计算的方法，分析了不同变体速率下航行器的动力学响应和附加力、附加力矩的影响。结果表明，附加力和附加力矩与变体速率正相关。
- 变体航行器 /
- 半环翼 /
- 动力学建模 /
- 纵向运动 /
- 动态响应
Abstract:
In view of the problem that the dynamic model of some morphing vehicles is complex, which is caused by the complicated variant description and the rigid-flexible coupling, a general applicable dynamic equation of morphing vehicle is derived. The vehicle is regarded as a whole composed of mass points, and the dynamic differential equation of each mass point is established. The extended dynamic equation suitable for the morphing vehicle is derived by integral method, and the influence of the variants is described as additional forces and additional moments. The longitudinal open-loop motion simulation of a conformal semi-ring wing morphing vehicle with flexible wings is carried out. Aimed at the problem that some additional forces and additional moments are difficult to accurately calculate, a rapid calculation method for engineering is proposed. The dynamic response of the vehicle and the influence of additional forces and additional moments under different variant rates are analyzed. The results show that the additional forces and additional moments are positively correlated with the variant rate.
- morphing vehicle /
- semi-ring wing /
- dynamic modeling /
- longitudinal motion /
- dynamic response

HTML全文

图 1 坐标系建立^[9]

Figure 1. Coordinate system setup^[9]

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图 2 共形半环翼航行器构型^[14-15]

Figure 2. Configuration of conformal semi-ring wing vehicle^[14-15]

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图 3 共形半环翼航行器变体过程

Figure 3. Process of variant of conformal semi-ring wing vehicle

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图 4 航行器正向单侧剖面图

Figure 4. Forward unilateral profile of vehicle

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图 5 航行器变体气动参数

Figure 5. Aerodynamic parameters of vehicle in variant phase

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图 6 静矩及其导数变化曲线

Figure 6. Variation curve of static moment and its derivative

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图 7 机翼收回仿真结果

Figure 7. Simulation results of retracting wing

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图 8 机翼展开仿真结果

Figure 8. Simulation results of unfolding wing

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图 9 附加力与附加力矩变化曲线

Figure 9. Variation curve of additional forces and additional moments

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表 1 两种配平状态下的航行器参数^[17]

Table 1. Vehicle parameters under two trimmed conditions^[17]

配平状态	θ/(°)	高度/km	攻角/(°)	俯仰舵偏角/(°)	推力/N
A	0	2	0.6	3	673
B	67.5	2	8.8	8.5	1 444

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参考文献(17)

[1]	冯金富, 陈国明, 张萌. 变体技术在兵器设计上的应用[J]. 兵器装备工程学报, 2017, 38(12): 215-220. doi: 10.11809/scbgxb2017.12.048 FENG J F, CHEN G M, ZHANG M. Application of morphing technology in aircraft[J]. Journal of Ordnance Equipment Engineering, 2017, 38(12): 215-220(in Chinese). doi: 10.11809/scbgxb2017.12.048
[2]	许来斌, 杨树兴, 陈军, 等. M型机翼变体飞机动力学分析[J]. 北京理工大学学报, 2013, 33(2): 127-132. doi: 10.3969/j.issn.1001-0645.2013.02.004 XU L B, YANG S X, CHEN J, et al. Dynamic analysis of M-wing morphing aircraft[J]. Transactions of Beijing Institute of Technology, 2013, 33(2): 127-132(in Chinese). doi: 10.3969/j.issn.1001-0645.2013.02.004
[3]	王志刚, 徐聘, 周嘉星, 等. 后掠展长组合变形飞行器动力学建模[J]. 飞行力学, 2015, 33(5): 407-410. https://www.cnki.com.cn/Article/CJFDTOTAL-FHLX201505006.htm WANG Z G, XU P, ZHOU J X, et al. Dynamic modeling of aircraft with sweep and span combined morphing[J]. Flight Dynamics, 2015, 33(5): 407-410(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-FHLX201505006.htm
[4]	SEIGLER T M, NEAL D A, BAE J S, et al. Modeling and flight control of large-scale morphing aircraft[J]. Journal of Aircraft, 2007, 44(4): 1077-1087. doi: 10.2514/1.21439
[5]	SEIGLER T M. Dynamics and control of morphing aircraft[D]. Virginia: The Virginia Polytechnic Institute and State University, 2005: 32-39.
[6]	SEIGLER T M, NEAL D A. Analysis of transition stability for morphing aircraft[J]. Journal of Guidance, Control, and Dynamics, 2009, 32(6): 1947-1954. doi: 10.2514/1.44108
[7]	陈伟, 冯高鹏. 变体飞机建模及自适应动态面控制[J]. 测控技术, 2016, 35(2): 91-95. doi: 10.3969/j.issn.1000-8829.2016.02.023 CHEN W, FENG G P. Modeling and adaptive dynamic surface control of morphing aircraft[J]. Measurement and Control Technology, 2016, 35(2): 91-95(in Chinese). doi: 10.3969/j.issn.1000-8829.2016.02.023
[8]	谭骏怡, 胡俊华, 葛阳, 等. 跨介质航行器变体过程动力学的仿真与建模[C]//2019中国系统仿真与虚拟现实技术高层论坛. 北京: 北京国信融合信息技术研究所, 2019: 249-253. TAN J Y, HU J H, GE Y, et al. Simulation and modeling of trans-medium vehicle variation process dynamics[C]//2019 China System Simulation and Virtual Reality Technology High-level Forum. Beijing: Beijing Guoxin Fusion Information Technology Research, 2019: 249-253(in Chinese).
[9]	刘万俊. 导弹飞行力学[M]. 西安: 西安电子科技大学出版社, 2014: 65-73. LIU W J. Missile flight mechanics [M]. Xi'an: Xidian University Press, 2014: 65-73(in Chinese).
[10]	浙江大学理论力学教研室. 理论力学[M]. 3版. 北京: 高等教育出版社, 1999: 194-198. Department of Theoretical Mechanics, Zhejiang University. Theoretical mechanics[M]. 3rd ed. Beijing: Higher Education Press, 1999: 194-198(in Chinese).
[11]	高晓光, 李波, 蔡付东. 坐标系转换矩阵及其微分方程[J]. 飞行力学, 2004, 22(2): 34-36. doi: 10.3969/j.issn.1002-0853.2004.02.009 GAO X G, LI B, CAI F D. Conversion matrix of coordinate and its differential equations[J]. Flight Dynamics, 2004, 22(2): 34-36(in Chinese). doi: 10.3969/j.issn.1002-0853.2004.02.009
[12]	刘延柱, 洪嘉振, 杨海兴. 多刚体系统动力学[M]. 北京: 高等教育出版社, 1989: 11-13. LIU Y Z, HONG J Z, YANG H X. Multi rigid body system dynamics [M]. Beijing: Higher Education Press, 1989: 11-13(in Chinese).
[13]	李元宗, 王耀国. 机器人转动惯性张量的坐标变换[J]. 机器人, 1992, 14(2): 31-35. https://www.cnki.com.cn/Article/CJFDTOTAL-JQRR199202006.htm LI Y Z, WANG Y G. Coordinate transformation of rotating inertial tensor of robot[J]. Robot, 1992, 14(2): 31-35(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-JQRR199202006.htm
[14]	张佳强, 冯金富, 谢奇峰, 等. 适应水-空介质航行的共形半环翼布局概念研究[J]. 空气动力学学报, 2012, 30(5): 685-691. https://www.cnki.com.cn/Article/CJFDTOTAL-KQDX201205021.htm ZHANG J Q, FENG J F, XIE Q F, et al. Research on concept of conformal semi-ring wing configuration for water-air medium voyage[J]. Acta Aerodynamica Sinica, 2012, 30(5): 685-691(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-KQDX201205021.htm
[15]	谭骏怡, 胡俊华, 颜奇民, 等. 共性半环翼跨介质航行器变体气动特性研究[J]. 飞行力学, 2020, 38(1): 1-7. https://www.cnki.com.cn/Article/CJFDTOTAL-FHLX202001001.htm TAN J Y, HU J H, YAN Q M, et al. Study on aerodynamic characteristics of conformal semi-ring wing trans-medium vehicle variants[J]. Flight Dynamics, 2020, 38(1): 1-7(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-FHLX202001001.htm
[16]	MOLER C B. MATLAB数值计算[M]. 喻文健, 译. 北京: 机械工业出版社, 2006: 79-86. MOLER C B. MATLAB numerical calculation [M]. YU W J, translated. Beijing: China Machine Press, 2006: 79-86(in Chinese).
[17]	陈伟, 冯高鹏, 拜云山. 小型变体无人机动力学建模及配平分析[J]. 计算机技术与发展, 2017, 27(2): 125-129. https://www.cnki.com.cn/Article/CJFDTOTAL-WJFZ201702028.htm CHEN W, FENG G P, BAI Y S. Dynamics modeling and trimming analysis for small morphing UAV[J]. Computer Technology and Development, 2017, 27(2): 125-129(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-WJFZ201702028.htm