基于高速飞行器火力控制模型的智能解算方法

杨犇; 金飞腾; 刘燕斌; 陈柏屹; 彭寿勇

doi:10.13700/j.bh.1001-5965.2022.0503

基于高速飞行器火力控制模型的智能解算方法

doi: 10.13700/j.bh.1001-5965.2022.0503

1.
南京航空航天大学航天学院，南京 211106
2.
南京航空航天大学自动化学院，南京 211106
3.
北京空天技术研究所，北京 100074

基金项目: 中央高校基本科研业务费专项资金(NS2021061)；江苏省基础研究计划青年基金项目(BK20200437)

详细信息

通讯作者:
E-mail：liuyb@nuaa.edu.cn

中图分类号: V271.4；TB553
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- 文章访问数: 330
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- PDF下载量: 9
- 被引次数: 0
出版历程
- 收稿日期: 2022-06-20
- 录用日期: 2022-08-12
- 网络出版日期: 2023-01-12
- 整期出版日期: 2024-05-29

Intelligent solution method based on high-speed aircraft fire control model

1.
College of Astronautics，Nanjing University of Aeronautics and Astronautics，Nanjing 211106，China
2.
College of Automation Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 211106，China
3.
Beijing Aerospace Technology Institute，Beijing 100074，China

Funds: Fundamental Research Funds for the Central Universities (NS2021061); Basic Research Plan of Jiangsu Province for Young Scholars (BK20200437)

More Information

Corresponding author: E-mail：liuyb@nuaa.edu.cn

摘要

摘要:
研究吸气式高速飞行器的火力控制解算问题，针对高速飞行器较传统的亚音速与超音速飞行器系统响应时间短，飞行环境复杂，对火力控制模型解算要求度高等难点，提出了一种高速飞行器火力控制模型的解算方法。构建了面向高速飞行器平台的火力控制模型，并根据高速飞行器的飞行特性，使用快速模拟法结合阿基米德优化算法求解攻击区域，并反解出载机初始的指令信号。仿真结果表明，该解算方法解算精度高，控制参数少，所实现的攻击区域广，且能发挥高速飞行器较强的飞行性能。
- 高速飞行器 /
- 火力控制 /
- 攻击区域 /
- 阿基米德优化算法 /
- 智能解算
Abstract:
This paper studies the fire control calculation problem of air-breathing high-speed aircraft. High-speed aircraft has higher requirements for the fire control model calculation, a more complicated flying environment, and a shorter response time than traditional subsonic and supersonic combat aircraft. A calculation method of the high-speed aircraft fire control model is proposed. First of all, the mathematical model of the air-breathing high-speed flight vehicle is established; and the fire control model of the high-speed aircraft platform is constructed. Then, the attack area is solved using the fast simulation method in conjunction with the Archimedes optimization algorithm based on the flight characteristics of the high-speed aircraft, and the carrier aircraft's initial command signal is solved in reverse. The simulation results show that the solution method has high solution accuracy, few control parameters, wide attack area, and can exert strong flight performance of high-speed aircraft.
- high-speed aircraft /
- fire control /
- attack area /
- Archimedes optimization algorithm /
- intelligent solution

HTML全文

图 1 CAV-H模型气动参数拟合曲面

Figure 1. Fitting surface of CAV-H model aerodynamic parameters

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图 2 空空任务火力控制示意图

Figure 2. Schematic diagram of air-to-air mission fire control

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图 3 不同算法求解Ackley函数的适应度曲线对比

Figure 3. Comparison of fitness curves of different algorithms for solving Ackley function

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图 4 火力控制快速模拟方程组解算过程

Figure 4. Solving process of fire control fast simulation equations

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图 5 火力控制模型指令解算全过程示意图

Figure 5. Schematic diagram of whole process of fire control model instruction solving

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图 6 给定视线角下分别求解出的攻击距离

Figure 6. Attack distances solved respectively under given line of sight angles

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图 7 视线角、投放姿态角与最大攻击距离关系曲线

Figure 7. Relationship curve of line of sight angle, launch attitude angle and maximum attack distance

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图 8 不同初始速度下以载机为中心的攻击区域

Figure 8. Attack area centered on carrier aircraft at different initial speeds

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表 1 算法求解出的函数平均适应值

Table 1. Average fitness value of function solved by algorithm

函　数	PSO	PIO	QPIO	AOA
Ackley	0.003	0.0057	6.09×10⁻⁷	2.80×10⁻¹³
Rastrigin	0.00053	2.61×10⁻⁵	0	0
Rosenbrock	3.34×10⁻⁶	7.55×10⁻¹⁸	6.23×10⁻¹²	0

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表 2 仿真参数设置

Table 2. Simulation parameter settings

仿真条件	条件参数值
载机初始高度h/km	$ 23 $
载机初始速度V₁₀/(m·s⁻¹)	$ 1\;475(Ma\text{=5}) $
目标平均运动速度V_M0/(m·s⁻¹)	$ 450(Ma\text{=1}\text{.5}) $
导弹比例导引系数K	$ 4 $
算法种群规模N	$ 30 $
算法最大迭代次数$ {t_{{\text{max}}}} $	$ 1\;000 $
算法其他参数	$ {C}_{1}\text{=2}，{C}_{2}=6，{C}_{3}=2，{C}_{4}=0.5 $

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表 3 约束参数设置

Table 3. Constraint parameter settings

约束参数	条件值
视线角速度$\dot q$/((°)·s⁻¹)	[0,20]
雷达位标器探测角$\left\| \varsigma \right\|$/(°)	$ \leqslant 114$
击毁目标所需相对速度${V_{\mathrm{r}}}$/(m·s⁻¹)	$5$
切向过载$\left\| {{n_x}} \right\|$	$ \leqslant 30$
法向过载$\left\| {{n_y}} \right\|$	$ \leqslant 30$
火力控制命中时间${t_{\mathrm{m}}}$/s	$ \leqslant 10$

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表 4 算法解算结果对比

Table 4. Comparison of algorithm solution results

视线角/(°)	初始姿态角/(°)		视线角/(°)
视线角/(°)	传统火控计算方法	AOA智能解算	传统火控计算方法	AOA智能解算
0	0	0.0657	7064.666	7065.659
10	7.5	6.0265	7106.679	7107.513
20	12.5	12.4944	7233.633	7234.100
30	20	18.9247	7446.523	7447.495
40	25	25.64	7750.234	7750.793
50	30	32.6228	8140.742	8147.354

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