制导航弹气动布局数值分析

【作者】 张洪；

【导师】 乐贵高；

【作者基本信息】 南京理工大学 ， 兵器发射理论与技术， 2010， 硕士

【摘要】 未来战争的战场环境十分恶劣,单一制导模式由于获取的目标信息量有限,很难适应作战需要,必然使精确制导航弹面临着严峻挑战,单模制导技术正朝着双模、多模制导方向发展。空气动力计算是飞行器设计的重要内容之一,可以快速获取空气动力和操作稳定特性,被广泛应用于飞行器设计的初始阶段。而伴随着计算机技术和计算流体力学(CFD)的高速发展,数值模拟的精度正在不断提高,通过计算机数值模拟复杂绕流流场来进行飞行器空气动力特性分析,可以方便快捷地获取空气动力参数、修改设计方案,有效的弥补了风洞实验、飞行试验的高成本、长周期和高风险等缺陷,有效发挥了“数字风洞”的作用。本文以三维Navier-Stokes方程为数值模拟基本方程,建立了基于两种制导模式下的四种制导航弹三维数学物理模型,并用有限体积法对计算区域及控制方程进行离散,应用数值方法对航弹绕流流场进行模拟。通过与风洞吹风实验数据的对比,验证了数值结果的有效性和模拟方法的可靠性。在此基础上对双模制导航弹在不同的攻角(a=-4°、-2°、0°、2°、4°、6°、8°、10°、12°、14°)和不同来流速度(Ma=0.6、0.8、0.9)以及不同舵偏角(δ=0°、-5°、-10°、-15°)下的绕流流动进行数值模拟,着重对航弹的升阻特性、纵向静稳定性进行了详细分析,获取的主要气动参数将为下一阶段的结构设计提供一定的技术性支持。更多还原

【Abstract】 The future battlefield environment is so bad that it is difficult to meet the war requirements for single guided bomb’s the limited amount of information. Precision guided bombs will inevitably face serious challenges. Single-mode dual-mode guidance technology is moving to the direction of multi-mode guidance. Aircraft aerodynamics computation is a key method to the aircraft design, and the operation stability characteristics of aircraft can be quickly obtained in preliminary aircraft design stage. With the high speed development of computer technology and computational fluid dynamics (CFD), and continuous improvement of simulation accuracy; aerodynamic characteristics of aircraft will be quickly and easily realized the aerodynamics parameters are obtained to modify design and replenish wind tunnel tests. Using numerical simulation of complex flow field can reduce cost, long cycle and high-risk defects of wind tunnel test and flight experiment and effectively a "digital wind tunnel" effect.In this thesis, the flow mathematical and physical model for two guided bomb are founded based on three-dimensional Navier-Stokes equation. Finite volume method is used to discrete the flow equations. Numerical calculation method are performed to simulate bomb’s flow field, and the wind tunnel test data are compared with the numerical results to verify the validity and reliability of numerical methods. Numerical simulation for this dual-mode guided bomb’s flow field in different angles of attack (α=-4°、-2°、0°、2°、4°、6°、8°、10°、12°、14°) and the variable flow speeds (Ma=0.6、0.8、0.9) and different rotation rudder angles (δ=0°、-5°、-10°、-15°). The main aerodynamic parameters are obtained and lift and drag characteristics and static stability of guided bomb are analyzed in detail. It will provide some technical support for the next stage of engineering design.更多还原