定向能载荷约束下面对称飞行器定向定姿制导技术

doi:10.7527/S1000-6893.2024.30196

Abstract

Abstract:

Airborne directed energy weapons are one of the decisive factors to gain asymmetric advantages in future offensive and defensive confrontations. To address the problem of multiple constraints of the position， flight direction and bank attitude of the plane symmetrical aircraft under the requirement of effective damage to the target caused by directed energy load， a multiple constraint maneuvering guidance strategy with specified direction and attitude is proposed based on lateral acceleration compensation. The mission scenario of airborne directed energy loads attacking ground targets is described， and the maneuvering laws as well as constraints of position， flight direction and bank attitude of the plane symmetrical aircraft restricted by directed energy load are revealed. Based on the kinematic model and the multiple constraints such as position， specified direction and attitude of plane symmetrical aircrafts， the maneuvering guidance strategy of “virtual guidance- specified attitude attack” is designed to coordinate the imposed time and conditions of each constraint， which helps avoid the problem of command solution difficulty caused by excessive constraints. The coupling correlation characteristics existing in all constraints are analyzed， and a specified direction virtual guidance mechanism is proposed to guide the aircraft to the target on the specified course. On this basis， a specified direction and attitude maneuvering strategy with lateral acceleration compensation is proposed to actively generate the lateral acceleration for realizing dynamic balance of the aircraft， which can ensure that the plane symmetrical aircraft can simultaneously satisfy and maintain the heading angle as well as the bank angle constraints required for the normal operation of the directed energy load， and the directed energy load has sufficient irradiation time. The simulation results indicate that the proposed maneuvering guidance strategy based on lateral acceleration compensation can meet the requirements of the guidance mission with specified direction and attitude of the plane symmetrical aircraft restricted by directed energy load， and can provide certain reference for supporting the practical application of airborne directed energy weapons.

Key words: airborne directed energy, plane symmetrical aircraft, lateral acceleration compensation, bank angle constraint, heading angle constraint

CLC Number:

V249

Lu BAI, Defu LIN, Duo ZHENG, Mingjun WEI. Guidance technology of specified direction and attitude for plane symmetrical aircraft with directed energy load constraint[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(22): 330196.

Figures/Tables 34

Fig.1

Table 1

Definitions of aircraft kinematics variables

变量	定义
$m / k g$	飞行器质量
$V / m ⋅ s - 1$	飞行器速度大小
$θ / (°)$	弹道倾角
$ψ V / (°)$	航向角
$γ / (°)$	倾斜角
$g / (m ⋅ s - 2)$	重力加速度
$q / (N ⋅ m - 2)$	动压
$S / m 2$	特征面积
$P / N$	推力
$F x / N$	阻力
$F y / N$	升力
$F z / N$	侧向力
$C x$	阻力系数
$C y$	升力系数
$C z$	侧向力系数
$x, y, z / m$	飞行器位置坐标

Table 1

Fig.2

Fig.3

Fig.4

Fig.5

Fig.6

Fig. 7

Table 2

Initial simulation conditions of aircraft

参数	数值
$P / N$	3 572
$m / k g$	1 944
$S / m 2$	0.36
$N y$	5
$N z$	5
$g / (m ⋅ s - 2)$	9.8

Table 2

Table 3

Different constraints for single target situation

项目	约束1	约束2
$θ f / (°)$	0	0
$H f / m$	500	500
$ψ V f / (°)$	9.48	-19.48
$γ f / (°)$	-15	15

Table 3

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

Table 4

Simulation results analysis of different constraints in single target situation

项目	约束1			约束2			要求
项目	期望值	实际值	偏差值	期望值	实际值	偏差值	要求
$ψ V f / (°)$	9.48	9.63	0.15	-19.48	-19.72	-0.24	满足
$θ f / (°)$	0	0.10	0.10	0	0.10	0.10	满足
$γ f / (°)$	-15	-14.95	0.05	15	15.02	0.02	满足
$H f / m$	500	499.73	-0.27	500	499.71	-0.29	满足

Table 4

Fig.16

Fig.17

Fig.18

Table 5

Simulation parameters of multi-target situation

仿真参数	目标 $T 1$	目标 $T 2$	目标 $T 3$
位置坐标 $/ m$	（6 000，500， 400）	（13 000，100， -200）	（20 000，600， 500）
$η / (°)$	-5	1	-10
$L / m$	800	800	800
$R s / m$	200	200	200

Table 5

Table 6

Constraints corresponding to different targets in multi-target situation

约束项	目标 $T 1$	目标 $T 2$	目标 $T 3$
$θ f / (°)$	0	0	0
$ψ V f / (°)$	9.48	-13.48	4.48
$H f / m$	500	100	600
$γ f / (°)$	-15	10	-5

Table 6

Fig. 19

Fig.20

Fig.21

Fig.22

Fig.23

Fig.24

Fig.25

Fig.26

Table 7

Simulation results analysis of constraints in multiple target situation

约束项		目标 $T 1$	目标 $T 2$	目标 $T 3$	要求
$ψ V f / (°)$	期望值	9.48	-13.48	4.48	满足
	实际值	9.63	-13.58	4.58
	偏差值	0.15	-0.10	0.10
$θ f / (°)$	期望值	0	0	0	满足
	实际值	0.10	0.09	-0.01
	偏差值	0.10	0.09	-0.01
$γ f / (°)$	期望值	-15	10	-5	满足
	实际值	-14.95	10.01	-5
	偏差值	0.05	0.01	0
$H f / m$	期望值	500	100	600	满足
	实际值	499.73	99.81	600.31
	偏差值	-0.27	-0.19	0.31

Table 7

Table 8

Monte Carlo simulation statistics with measurement noise and wind interference

项目	$ψ V f / (°)$	$θ f / (°)$	$γ f / (°)$	$H f / m$
期望值	9.48	0.00	-15.00	500.00
平均值	9.64	0.06	-14.98	499.34
平均偏差	0.16	0.06	0.02	-0.66
最大偏差绝对值	0.52	0.21	0.86	1.22
要求	满足	满足	满足	满足

Table 8

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Guidance technology of specified direction and attitude for plane symmetrical aircraft with directed energy load constraint

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