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摘要: 机载投放分离、航天器串联/并联级间分离、整流罩分离和子母弹抛撒等飞行器多体分离问题在当前航空航天领域普遍存在, 安全可控的多体分离是飞行器执行航空航天任务的重要前提. 近年来, 随着飞行任务的多样化和飞行边界的扩展, 飞行器面临更加复杂的多体分离场景, 多体分离方案设计更加精细化, 对多体分离数值模拟的精细度提出了更高的要求. 针对极具复杂性和挑战性的多体分离问题, CFD近年来在复杂场景精细化模拟方面取得了巨大的进步. 本文针对飞行器多体分离数值模拟方法及应用的最新研究进展进行了回顾与展望. 首先总结了飞行器多体分离精细化数值模拟方法, 主要包括耦合网格动态优化技术、耦合分离涡模拟方法以及高精度时间推进耦合算法. 其次总结了复杂约束/流场/控制下的飞行器多体分离耦合模拟方法及其应用, 介绍典型复杂场景飞行器多体分离动态干扰复杂机理认识. 最后指出了飞行器多体分离数值模拟存在的问题及未来发展方向.Abstract: The problems of aircraft multi-body separation, such as airborne weapon delivery separation, spacecraft series/parallel stage separation, fairing separation and submunition scattering, are common in the aerospace field at present. Safe and controllable multi-body separation is an important prerequisite for aircraft to perform aerospace tasks. In recent years, with the expansion of flight boundaries and the diversification of flight missions, aircraft are facing more complex multi-body separation scenarios, so it is necessary to carry out refined multi-body separation scheme design, which puts forward higher requirements for the fidelity and fineness of multi-body separation numerical simulation. In recent years, CFD has made great progress in high-fidelity simulation of complex scenes, aiming at the extremely complex and challenging multi-body separation problem. In this paper, the latest research progress of high-fidelity numerical simulation methods and applications of aircraft multi-body separation is reviewed and prospected. Firstly, the refined simulation methods of aircraft multi-body separation are summarized, including coupled grid dynamic optimization technology, coupled separation vortex simulation method and high-precision time-marching coupling algorithm. Secondly, the coupling simulation method of aircraft multi-body separation under complex constraints/flow field/control and its application are introduced. Then, the understanding of complex mechanism of dynamic interference of aircraft multi-body separation in typical complex scenes is introduced. Finally, the existing problems and future development direction of high fidelity numerical simulation of aircraft multi-body separation are pointed out.
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图 1 非结构混合网格单元加密模式 (a)三角形单元加密方法, (b)四边形单元加密方法, (c)四面体单元加密方法, (d)三棱柱单元加密方法, (e)六面体单元加密方法, (f)金字塔单元加密方法 (唐静 等 2023)
图 15 耦合舵面控制的多体分离仿真流程 (周乃春 等 2013)
图 16 WPSF模型舵面偏转随时间变化方式A和B. (a)舵面偏转规律A, (b)舵面偏转规律B (周乃春 等 2013)
图 17 外挂物姿态随时间变化曲线. (a)偏航角, (b)俯仰角, (c)滚转角 (周乃春 等 2013)
图 18 不同控制律外挂物的位置和姿态对比图 (a) t=0.15 s, (b) 0.30 s (周乃春 等 2013)
图 23 轨道级横向分离不同时刻流场涡结构图. (a)轨道级重心为0.75, (b)轨道级重心为0.80 (Wang et al. 2023a)
图 24 轨道级纵向分离不同时刻流场图. (a)尖锥模型, (b)轨道级头部无尖锥 (Wang et al. 2024)
图 25 约束力节点分解示意图 (Toniolo et al. 2008)
图 27 t=0 ms级间流场结构 (a) 激波IS作用干扰区的空间流场, (b) 激波RS1作用干扰区的空间流场(范孝华 等 2023)
图 29 不同计算方法的网格和结果云图对比. (a)旋翼贴体网格和计算结果云图, (b)旋翼桨盘网格和计算结果云图(Li et al. 2020)
图 33 无扰流板数值计算结果. (a)压力系数云图和马赫数云图, (b)流线和涡量等值面 (Cui et al. 2022)
图 34 扰流板高度h=δ数值计算结果. (a)压力系数云图和马赫数云图, (b)流线和涡量等值面 (Cui et al. 2022)
图 35 扰流板高度h=4.8δ数值计算结果. (a)压力系数云图和马赫数云图, (b)流线和涡量等值面 (Cui et al. 2022)
图 36 有无扰流板空腔流动示意图. (a)无扰流板, (b)带扰流板 (Cui et al. 2022)
图 37 不同扰流板高度分离特性对比. (a)分离物姿态角对比图, (b)分离安全性对比图 (Cui et al. 2022)
图 42 头罩分离气动力图. (a)法向力, (b)俯仰力矩 (Cui et al. 2022)
图 43 A类涡动态转移演化. (a) 19.8 ms, (b) 20.7 ms, (c) 21.6 ms, (d) 24.3 ms (Cui et al. 2022)
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