【作者】 吴萍；

【导师】 陈少松； 谭献忠；

【作者基本信息】 南京理工大学 ， 热能工程， 2014， 硕士

【摘要】 精确打击弹药在现代战争中使用比例越来越高,而导弹造价昂贵,不能大规模装备,库存量大的无控弹无法达到精度要求,介于两者之间的弹道修正弹以其较高的效费比获得许多国家的青睐。弹道修正弹是指弹箭在飞行弹道的合适位置,通过修正机构的作用改变弹箭气动外形来改变气动力从而达到改变落点坐标、提高射击密集度指标的一种智能弹箭。本文描述了对鸭式布局的二维弹道修正弹进行气动力研究的过程,给出了风洞实验和数值模拟的结果,进行了气动特性的分析。首先,设计一组拥有不同舵偏角的鸭式布局二维弹道修正弹模型,对这组模型进行亚、跨和超音速下的风洞静态测力实验,得到了模型气动力和力矩系数随马赫数、攻角和舵偏角的变化规律,拍摄了超音速下纹影照片。采用数值计算的方法研究了二维修正弹不旋转和在超音速条件下转速为10000r/min和15000r/min的气动特性,得到了不旋转和旋转条件下模型的流场分布规律,并借此对气动特性的变化规律进行了分析。通过纹影照片和数值模拟流场的观察,原模型在头部与圆弧接触部位出现了一道激波,这会对模型的气动特性产生不利的影响。为此对前期研究的模型进行了改进,设计了一组新布局模型,在超音速条件下,采用数值计算的方法对改进后模型不旋转和转速为1OOOOr/min和15000r/min状态的气动特性进行研究,得到不旋转和旋转状态下的气动特性规律。对比两种气动布局模型的气动特性发现：改进后模型阻力系数有降低,但减阻效果不明显,模型在旋转后阻力系数也会有降低；改进后模型升力系数有增加,模型修正力提高了,模型升力系数不随转速变化而变化；改进后模型的俯仰力矩系数增加了,模型俯仰力矩系数不随转速变化而变化；改进后模型的滚转力矩也增加了,模型改变姿态的能力提高了,旋转后模型滚转力矩系数减小了,转速越大滚转力矩系数越小；改进后模型的压心系数小于改进前模型压心系数。本文对两种鸭式气动布局二维弹道修正弹气动特性的研究结果可为二维弹道修正弹的弹道设计和研究提供基础依据。更多还原

【Abstract】 The use of precision strike munitions occupies more and more proportion in modern warfare, for guided missiles are too expensive to equip the army in large-scale, and inventories of uncontrolled rockets could not achieve the required accuracy, the Trajectory correction projectile with its high benefit-cost ratio has obtained the favor of many countries. Trajectory correction projectile is an intelligent missile, it modify impact coordinate and improve fire intensity targets by changing aerodynamic shape with correcting mechanism in proper position of flight. This article describes the process of canard controlled two-dimension trajectory correction projectile’s aerodynamic research, the results of wind tunnel experiments and numerical simulations were given, aerodynamic characteristics were analyzed.First, a pair of canard controlled two-dimension models of trajectory correction projectiles with different rudder angles were designed, the aerodynamic characteristics of models were studied by wind tunnel test in subsonic, transonic and supersonic. The variation of Models’aerodynamic force and moment coefficients with Mach number, angle of attack and rudder angle were gotten, schlieren photographs were taken in supersonic. Model non-rotating in the experiment mach number and rotating speed10000r/min and15000r/min in supersonic were investigated by the method of numerical simulation, models’flow field distribution in rotating and non-rotating conditions were used to analysis variation of the aerodynamic characteristics.By observing the Schlieren photograph and flow field numerical simulation, original model appeared a shock wave at the head with the circular contact area, which will adversely affect the aerodynamic characteristics of models. To improve the original models, a new pair of canard controlled models were designed. Under the condition of supersonic, the new models non-rotating and rotating speed10000r/min and15000r/min were investigated by the method of numerical simulation, aerodynamic characteristics in non-rotating and rotating were gotten. Comparing aerodynamic characteristics of the two aerodynamic configuration models, the drag coefficient of optimized model reduced, but the reduction of drag effect was not obvious, under rotating conditions the drag coefficient of models all reduced. The lift coefficient of optimized models increased, it illustrated that models’ correction ability increased, under rotating conditions the lift coefficient of models all showed little change. The pitching moment coefficient of optimized models increased and had little change after rotating. The rolling moment coefficient of optimized models also increased, illustrated that models’ change attitude ability increased, under rotating conditions the rolling moment coefficient of models all decreased, decreased with the increased of rotational speed. The pressure center coefficient of optimized models was less than the origin models’.The results of this study on the two kinds of canard controlled two-dimensional trajectory correction projectiles aerodynamic configuration provided basis for the two-dimensional trajectory correction ballistic design and research.更多还原