传统弹箭类飞行器由于机动能力限制，难以实现快速、小半径、大角度的敏捷转弯。本文通过导弹上加装可控翼伞作为控制面，提出一种翼伞-导弹系统，实现导弹敏捷转弯。首先针对由导弹、翼伞、伞绳、连接点组成的伞弹系统进行动力学建模，给出9自由度伞弹系统动力学模型。通过纵向平面内的弹道仿真，对比分析了在翼伞襟翼偏转角0°、25°和50°情况下伞弹系统的运动情况，结果表明翼伞-导弹系统可以实现敏捷转弯。通过对伞弹系统动力学模型进行分岔分析，研究了不同襟翼偏转角情况下，以翼伞安装角为连续变化参数时系统的分岔曲线，得到导弹实现敏捷转弯的最小转弯半径及最大转弯末速所对应的目标平衡点，分析了目标平衡点附近的吸引域变化情况。弹道仿真结果表明通过合理选取翼伞襟翼偏转角及安装角，可以使质量为73 kg的导弹实现最小转弯半径14.50 m，最小速度损失20.4 m/s。伞弹系统对于提高传统战术导弹的敏捷转弯性能具有重要参考意义。
Traditional projectiles is difficult to realize the quick, small radius and large angle agile turn due to the limitation of maneu-verability. In this paper, a parafoil-missile system, missile with a suspending parafoil as the control surface, is proposed. Firstly, the dynamic model of the parafoil-missile system composed of missile, parafoil, ropes and connection point is proposed, and the dynamic model of the 9-DOF parafoil-missile system is presented. The motion of the parafoil-missile system is compared and analyzed when the flaps deflection is 0°, 25° and 50° through trajectory simulation in the longitu-dinal plane. The analysis results show that the parafoil-missile system can realize agile turn. By means of bifurcation analysis of the dynamic model of the parafoil-missile system, the bifurcation diagram of the system is studied under dif-ferent flap deflections and the rigging angle is taken as the continuous variable parameter. The target stable equilibrium corresponding to the minimum turn radius and the maximum turn final speed of the missile to realize agile turn is obtained. The variation of the attractive region near the target stable equilibrium is analyzed. The trajectory simulation shows that the missile with a mass of 73 kg can achieve the minimum turn radius of 14.50 m and the minimum velocity loss of 20.4 m/s, by selecting the flap deflection and rigging angle reasonably. The parafoil-missile system has important reference significance for improving the performance of agile turn of traditional tactical missiles.
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