敏捷转弯伞弹系统动力学建模与分岔特性分析

doi:10.7527/S1000-6893.2023.29012

Abstract

Abstract:

Traditional projectiles are difficult to realize the quick， small-radius and large-angle agile turn due to the limitation of maneuverability. In this paper， a parafoil-missile system is proposed to realize agile turn by adding a suspending parafoil as the control surface on the missile. Firstly， a 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 flap deflection is 0°， 25° and 50° through trajectory simulation in the longitudinal 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 when the flap deflection is different 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 proposed can provide important reference to improving the performance of agile turn of traditional tactical missiles.

Key words: tactical missile, ram parafoil, multi-body dynamics, agile turn, bifurcation analysis

CLC Number:

V212

Hongmiao ZHOU, Jianqiao YU, Yong YU. Dynamic modeling and bifurcation analysis of agile turn of parafoil⁃missile system[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(7): 229012-229012.

Figures/Tables 16

Fig.1

Fig.2

Fig.3

Fig.4

Table 1

Fig.5

Fig.6

Table 2

Comparison of agile turn performance of parafoil⁃missile system at different flap deflections

襟翼偏转角

Φ

/（°）

转弯半径/

转弯末速/

（m·s^-1）

转弯时间/

翼伞平衡攻角/（°）

20.34

147.54

0.40

5.5

20.94

133.63

0.43

1.6

16.59

121.73

0.37

0.1

Table 2

Fig.7

Table 3

Table 4

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

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伞弹系统	参数	数值
翼伞	质量m^*/kg	6
	弦长c/m	2.133 6
	展长b/m	6.400 8
	弧面下反角β/（°）	9.55
	伞绳长度R/m	4.78
导弹	质量m_m/kg	73
	弹长/m	2.643
	弹径/m	0.122
	质心位置（距头部）/m	1.27

平衡点	目标	Φ/（°）	μ/（°）	α_p/（°）
1	最小转弯半径	50	-1.77	5.8
2	最大转弯末速	0	-5	3.3

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Dynamic modeling and bifurcation analysis of agile turn of parafoil⁃missile system

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