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摘要:
为解决蜂群突防能力弱、作战半径小的弱点，加快形成分布式协同作战的平台级能力，提出一种弹携式蜂群无人机作战系统，利用导弹载体内埋搭载多架小型低成本无人机，通过导弹-蜂群多级运载的战术制定，实现蜂群的快速有利部署。采用兼顾总体相容性的气动布局优化设计技术，综合运用布局选型、数值仿真分析及风洞试验验证，完成一种高致密嵌入式的蜂群布局方案设计，依靠对翼面折叠的小型无人机沿集束柱周向布置的内埋措施，可实现单枚导弹搭载80架小型蜂群无人机的运载能力。针对导弹-蜂群高速多体分离的设计难点，采用优化的分离策略设计，基于改进延迟分离涡模拟方法及重叠网格技术进行蜂群多体分离仿真，结果能够满足蜂群无人机的安全分离。最终的设计方案既保证了蜂群多体量饱和式攻击的作战效能，又实现了系统突防能力和续航能力的显著提升，可满足未来强对抗战场的多种作战使用需求。
Abstract:One type of missile swarm system is proposed, where numerous small UAVs are compressed in a missile carrier, to solve the weakness of swarm penetration capability and operational radius while speeding up the formation of cooperation. It uses tactics by multistage transport, making the swarm deploy rapidly. Taking advantage of the compatibility design, aerodynamic configuration optimization design technology, layout selection, numerical simulation analysis, and wind tunnel test, the research achieves a kind of compact missile swarm layout design, one missile can carry 80 small UAVs by arranging UAVs circumferentially around the cylinder. In order to overcome the challenge of multibody separation design, a swarm can safely separate by adopting an optimum separation approach that has been confirmed by improved delayed detached eddy simulation and nested grid. Finally, the design scheme can not only ensure the efficiency of saturation attack but also improve the capability of penetration and endurance, meeting the requirement of future strong confrontation battlefield.
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Key words:
- swarm /
- missile carrier /
- multistage transport /
- compatibility /
- configuration design /
- multibody separation
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图 10 舵面偏转引起纵向气动力增量曲线
Figure 10. Longitudinal aerodynamic increment curves by deflection
图 12 无人机多体分离计算模型示意图
Figure 12. Diagram of UAV multibody seperation computational model
图 17 优化后1号无人机分离俯仰角和y向位移变化曲线
Figure 17. Optimized NO.1 UAV sepration pitch angle and y-directim displacement variation
表 1 气动布局方案和设计依据
Table 1. Aerodynamic configuration scheme and design basis
需求约束 设计依据 布局特征 巡航要求 保证50～70 m/s低速飞行
续航时间1 h，提升设计点
最大升阻比，增升减阻大展弦比平直机翼
较薄的低速高升力
翼型超声速无动
力滑翔不损失低速巡航能力前提
下，有效抑制滑翔阶段激
波阻力小钝头前机身
中等后掠机翼模块化装载要求 能根据不同作战分工装载
不同侦察、传感、电子对
抗、弹药等模块化设备
载荷机身头部模块化
侦察、打击设备
尾部推进装置高密度填充要求 保证内部模块化装载同时，
提高填充空间利用率折叠下单翼
折叠全动V尾翼面折叠要求 翼面蜂巢填充时应折叠
收放便于高效利用空间
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表 2 分离初始条件
Table 2. Separation of initial conditions
Ma H/km 初始速度/(m·s–1) 初始角速度/(rad·s–1) 1号 3号 5号 1.2 6 5 0 0 0
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表 3 优化后初始条件设计值
Table 3. Design value of initial conditions after optimization
Ma H/km 初始速度/(m·s–1) 初始角速度/(rad·s–1) 1号 3号 5号 1.2 6 9 12 6 6
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