无人机导弹滑弹一体式发射气动干扰数值模拟

发布时间：2018-06-10 20:23

本文选题：无人机 + 导弹发射　；参考：《中北大学》2016年硕士论文

【摘要】：在现代战争中,作为信息化武器装备的无人机发挥着越来越重要的作用,集侦察、监视和攻击能力于一体是无人机未来发展方向之一,挂载精确制导武器是该方向无人机的主要攻击手段。武器与载机的分离属于多体分离问题,分离初期存在显著的气动干扰,导弹点火时产生的尾喷流对无人机的气动干扰尤为严重,影响载机的飞行稳定性。因此,研究无人机挂载导弹发射时产生的气动干扰问题对无人机的飞行安全和导弹的安全分离具有重要意义。本论文着重研究机载导弹滑弹一体式发射过程中尾喷流对无人机的气动影响。研究以计算流体力学为理论依据,以CFD软件Fluent为研究平台,结合二维非结构动网格技术,模拟机载导弹滑弹一体式发射的过程。文中使用CATIA建立简化的模型,采用非结构网格生成技术对流场域进行网格的划分。考虑到导弹与无人机之间的相对运动,使用Fluent的动网格技术对计算过程中较大变形的网格进行自动更新。与机翼相连的网格静止,固联于导弹的网格跟随导弹运动,是运动网格。在Fluent中定义流场域的性质以及边界条件等,并监控机翼升、阻力系数的变化情况。通过对机载导弹滑弹一体式发射过程的模拟得到:使用滑弹一体式发射装置在一定程度上降低了导弹尾喷流对机翼的气动影响以及弹射后不同时间点火对机翼的气动干扰。同时,对无人机不同的飞行速度下,导弹的发射过程进行模拟,发现不同马赫数下,尾喷流对机翼的气动影响不同。该模拟结果为无人机导弹滑弹一体式发射装置的研究提供一定参考。
[Abstract]:In modern warfare, UAV, as an information-based weapon, plays an increasingly important role. It is one of the future development directions of UAV to integrate reconnaissance, surveillance and attack capabilities. Mounted precision guided weapon is the main attack method of UAV in this direction. The separation of weapons and aircraft is a multi-body separation problem. There is significant aerodynamic interference in the initial stage of separation. The aerodynamic interference caused by the tail jet produced by missile ignition is especially serious, which affects the flight stability of the aircraft. Therefore, it is of great significance to study the aerodynamic interference caused by the launch of unmanned aerial vehicle (UAV) mounted missile for UAV flight safety and missile safety separation. In this paper, the aerodynamic effect of tail jet on UAV is studied. Based on the theory of computational fluid dynamics (CFD) and CFD software fluent, this paper simulates the integrated launching process of airborne missile with unstructured dynamic grid technology. In this paper, CATIA is used to build a simplified model, and unstructured mesh generation technique is used to generate meshes in the flow field. Considering the relative motion between missile and UAV, fluent dynamic grid technology is used to automatically update the large deformation mesh in the calculation process. The grid attached to the wing is stationary, and the mesh attached to the missile follows the missile's motion, which is the moving grid. The properties of flow field and boundary conditions are defined in fluent, and the change of wing lift and drag coefficient is monitored. Through the simulation of the integrated launching process of airborne missile, it is concluded that the aerodynamic effect of missile tail jet on the wing and the aerodynamic interference caused by ignition at different time after ejection are reduced to some extent by using the integrated missile launcher. At the same time, the missile launch process is simulated at different flight speeds, and it is found that the tail jet has different aerodynamic effects on the wing under different Mach numbers. The simulation results provide a certain reference for the research of UAV missile sliding missile integrated launcher.
【学位授予单位】：中北大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V279;TJ760

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