Design of an active stabilized drogue for aerial refueling
-
摘要:
为了降低空中加油受油机头波效应对软管-锥套系统产生的气动扰动影响，设计了一种加装环形翼的主动增稳锥套。利用动态模型，进行了对接过程中头波效应的仿真分析，确定了能满足条件的环形翼设计方案，并设计了适用于环形翼的线性二次型调节器（LQR）控制器，利用Matlab/Simulink环境下搭建的空中加油测试平台及静态程序，对环形翼主动增稳效果及调整加油机和受油机相对位置的能力进行了仿真验证。仿真结果表明：所设计的主动增稳锥套能够减弱受油机头波效应的影响,将扰动控制在±5 cm的误差范围内，在抵抗干扰的同时还具有调整与加油机和受油机相对位置的能力。
-
关键词:
- 软式空中加油 /
- 头波效应 /
- 增稳锥套 /
- 计算流体力学（CFD） /
- LQR控制
Abstract:In order to reduce the aerodynamic disturbance caused by the bow wave effect on the hose-drogue system during aerial refueling, an actively stabilized drogue with an annular wing was designed. Using a dynamic model, a simulation analysis of the bow wave effect during the docking process was conducted to determine a feasible design scheme for the annular wing. An linear quadratic regulator (LQR) controller suitable for the annular wing was designed, and simulation verification of the effectiveness of the annular wing and the capability to adjust the relative positions of the tanker and receiver aircraft was performed using a Matlab/Simulink environment-based aerial refueling test platform and a static program. The simulation results indicated that the designed actively stabilized drogue can minimize the influence of the bow wave effect on the receiver aircraft within an error range of ±5 cm, and can also mitigate disturbances and adjust the relative positions of the refueling and receiving aircraft.
-
图 2 软管-锥套系统建模假设示意图
Figure 2. Hose-drogue system configurations and modeling assumptions
图 4 无量纲锥套垂直位置随加油机空速的变化
Figure 4. Dimensionless drogue vertical position vs.tanker airspeed
图 8 升力特性与锥套攻角、侧滑角及环形翼偏角关系图
Figure 8. Lift characteristics under varying drogue angles of attack, side slip angles and annular wing deflection angles
图 9 侧向力特性与锥套攻角、侧滑角及环形翼偏角关系图
Figure 9. Side characteristics under varying drogue angles of attack, side slip angles and annular wing deflection angles
图 10 阻力特性与锥套攻角、侧滑角及环形翼偏角关系图
Figure 10. Drag characteristics under varying drogue angles of attack, side slip angles and annular wing deflection angles
图 11 偏航力矩特性与锥套攻角、侧滑角及环形翼偏角关系图
Figure 11. Yawing moment under various drogue angles of attack, side slip angles, and annular wing offset angles
图 12 俯仰力矩特性与锥套攻角、侧滑角及环形翼偏角关系图
Figure 12. Drogue pitching moment under various drogue angles of attack, side slip angles and annular wing deflection angles
图 14 头波效应下锥套飘摆的垂直、水平位移
Figure 14. Vertical and lateral displacements of the drogue under the bow wave effect
表 1 主动增稳锥套基本系数
Table 1. Baseline parameters of the stabilized drogue
参数 数值 $ {C}_{\mathrm{d}0} $ 3.77577 $ {C}_{\mathrm{l}0} $ − 0.0164 $ {C}_{\mathrm{c}0} $ 0 $ {C}_{\mathrm{n}0} $ 0 $ {C}_{\mathrm{m}0} $ 0.0168 
下载: 导出CSV
表 2 主动增稳锥套攻角气动参数
Table 2. Drogue’s aerodynamic coefficients for 1 angle of attack change
参数 数值 $ {C}_{\mathrm{d}\alpha } $ 0 $ {C}_{\mathrm{l}\alpha } $ − 0.0082 $ {C}_{\mathrm{c}\alpha } $ 0 $ {C}_{\mathrm{n}\alpha } $ 0 $ {C}_{\mathrm{m}\alpha } $ − 0.0084
下载: 导出CSV
表 3 主动增稳锥套侧滑角气动参数
Table 3. Drogue’s aerodynamic coefficients for 1 side slip angle change
参数 数值 $ {C}_{\mathrm{d}\beta } $ 0 $ {C}_{\mathrm{l}\beta } $ 0 $ {C}_{\mathrm{c}\beta } $ − 0.0082 $ {C}_{\mathrm{n}\beta } $ −0.009 $ {C}_{\mathrm{m}\beta } $ 0
下载: 导出CSV
表 4 环形翼偏角气动参数
Table 4. Aerodynamic coefficients of the annular wing relative to 1 deflection angle change
参数 数值 $ {C}_{\mathrm{l}{\theta }_{1}} $ −0.05 $ {C}_{\mathrm{c}{\theta }_{1}} $ 0 $ {C}_{\mathrm{n}{\theta }_{1}} $ 0 $ {C}_{\mathrm{m}{\theta }_{1}} $ −0.016
下载: 导出CSV
表 5 软管和锥套参数
Table 5. Hose and drogue parameters
参数 数值 软管 全长/m 22.5 充油线密度/（kg/m） 4.205 内径/mm 50.8 外径/mm 67.31 弹性模量/107 Pa 1.379 锥套 质量/kg 30 锥套阻尼面积/m2 0.468 绕X轴转动惯量IXX 0.8 绕Y轴转动惯量IYY 1.1057 绕Z轴转动惯量IZZ 1.1057 环形翼投影面积/m2 0.0792
下载: 导出CSV
-
[1] EICHLER J. Dynamic analysis of an in-flight refueling system[J]. Journal of Aircraft,1978,15(5): 311-318. doi: 10.2514/3.58361 [2] HANSEN J L,MURRAY J E,CAMPOS N V. The NASA Dryden flight test approach to an aerial refueling system: NASA/TM-2005-212859 [R]. Providence,US: NASA Dryden Flight Research Center,2005. [3] KNACKE T W. Parachute recovery systems design manual [M]. Richcrest,US,US: Para Pub,1992. [4] VACHON M,RAY R,CALIANNO C. Calculated drag of an aerial refueling assembly through airplane performance analysis: AIAA2004-381[R]. Reston,US: AIAA,2004. [5] DAI Xunhua,QUAN Quan,REN Jinrui,et al. Terminal iterative learning control for autonomous aerial refueling under aerodynamic disturbances[J]. Journal of Guidance,Control,and Dynamics,2018,41(7): 1577-1584. [6] 刘海洲,田浩,黄意新,等. 受油机头波作用下软管-锥套运动特性分析[J]. 哈尔滨工业大学学报,2021,53(12): 16-22. LIU Haizhou,TIAN Hao,HUANG Yixin,et al. Analysis of motion characteristics of hose-drogue under bow wave[J]. Journal of Harbin Institute of Technology,2021,53(12): 16-22. (in Chinese doi: 10.11918/202005037LIU Haizhou, TIAN Hao, HUANG Yixin, et al. Analysis of motion characteristics of hose-drogue under bow wave[J]. Journal of Harbin Institute of Technology, 2021, 53(12): 16-22. (in Chinese) doi: 10.11918/202005037 [7] LIU Yiheng,WANG Honglun,SU Zikang,et al. Deep learning based trajectory optimization for UAV aerial refueling docking under bow wave[J]. Aerospace Science and Technology,2018,80: 392-402. doi: 10.1016/j.ast.2018.07.024 [8] SU Zikang,WANG Honglun,YAO Peng,et al. Back-stepping based anti-disturbance flight controller with preview methodology for autonomous aerial refueling[J]. Aerospace Science and Technology,2017,61: 95-108. doi: 10.1016/j.ast.2016.11.028 [9] 全权,魏子博,高俊,等. 软管式自主空中加油对接阶段中的建模与控制综述[J]. 航空学报,2014,35(9): 2390-2410. QUAN Quan,WEI Zibo,GAO Jun,et al. A survey on modeling and control problems for probe and drogue autonomous aerial refueling at docking stage[J]. Acta Aeronautica et Astronautica Sinica,2014,35(9): 2390-2410. (in ChineseQUAN Quan, WEI Zibo, GAO Jun, et al. A survey on modeling and control problems for probe and drogue autonomous aerial refueling at docking stage[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(9): 2390-2410. (in Chinese) [10] RO K,KUK T,KAMMAN J. Active control of aerial refueling hose-drogue systems: AIAA2010-8400 [R]. Reston,US: AIAA,2010. [11] ELLSWORTH J,FOX W R,LOVENDAHL D E,et al. Guided drogue flight test report: TR E-23027,[R]. Washington,US: Beech Aircraft Corporation,1977. [12] WILLIAMSON W R,REED E,GLENN G J,et al. Controllable drogue for automated aerial refueling[J]. Journal of Aircraft,2010,47(2): 515-527. doi: 10.2514/1.44758 [13] KIRKLAND W L,REED E. Stabilized controllable drogue for aerial flight refueling: US8317136[P]. 2012-11-27. [14] KRISPIN Y,VELGER M. Controllable hose-and-drogue in-flight refueling system: US5326052[P]. 1994-07-05. [15] SAGGIO F,III,RIBBENS W B,OOI K K. Stabilization of a drogue body: US6994294[P]. 2006-02-07. [16] Department of the Navy. Industry day for the actively stabilized drogue refueling system (ASDRS) demonstration [EB/OL]. (2014-04-01) [2023-03-15]. https://sam.gov/opp/6a0b2c51064bfd17867ba8cf9d953ba8/view [17] DIBLEY R,ALLEN M,NABAA N. Autonomous airborne refueling demonstration phase I flight-test results: AIAA 2007-6639 [R]. Reston,US: AIAA,2007. [18] 陈乐乐. 软式空中加油气动相容性及动态特性研究[D]. 南京: 南京航空航天大学,2017. CHEN Lele. Research on aerodynamic compatibility and dynamic characteristics of hose-drogue aerial refuling system[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2017. (in ChineseCHEN Lele. Research on aerodynamic compatibility and dynamic characteristics of hose-drogue aerial refuling system[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2017. (in Chinese) [19] HANSEN J,MURRAY J,CAMPOS N. The NASA Dryden AAR project: a flight test approach to an aerial refueling system: AIAA 2004-4939 [R]. Reston,US: AIAA,2004. -
点击查看大图
计量
- 文章访问数: 636
- HTML浏览量: 246
- PDF量: 60
- 被引次数: 0