一种空中加油主动增稳锥套设计  

Design of an active stabilized drogue for aerial refueling

作　　者：邹贵云 梁梓峰 刘学强[1] ZOU Guiyun;NIO Zifeng;LIU Xueqiang(College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学航空学院,南京210016

出　　处：《航空动力学报》2025年第2期153-163,共11页Journal of Aerospace Power

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。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.

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 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]