导转翼面对二维弹道修正弹跨音速气动性能的影响  

The Guided Canard Size Effect on Two-dimensional Trajectory Correction Transonic Aerodynamic Performance

作　　者：张英 肖晨星 李朝博 霍鹏飞[1,2] 陈超 ZHANG Ying;XIAO Chenxing;LI Chaobo;HUO Pengfei;CHEN Chao(Xi'an Institute of Electromechanical Information Technology,Xi'an 710065,China;Science and Technology on Electromechanical Dynamic Control Laboratory,Xi'an 710065,China)

机构地区：[1]西安机电信息技术研究所,陕西西安710065 [2]机电动态控制重点实验室,陕西西安710065

出　　处：《探测与控制学报》2023年第3期23-30,共8页Journal of Detection & Control

摘　　要：为了研究不同翼展导转翼面对加榴炮二维弹道修正杀爆弹跨音速气动性能的影响,在升力翼面不变的前提下,改变导转翼面尺寸,形成了4种不同导转翼面的加榴炮二维弹道修正杀爆弹气动外形。采用有限体积法,基于Spalart-Allmaras湍流模型,求解三维黏性Navier-Stokes方程,获取了这4种气动外形翼面及弹体的阻力系数、升力系数、俯仰力矩系数、滚转力矩系数等气动参数。为验证数值模拟结果,对其中的模型3进行了风洞实验,经对比,数值模拟与实验结果相符。结合其他模型计算结果,研究了不同导转翼面对导转翼面自身、对升力翼面及对加榴炮二维弹道修正杀爆弹弹体三个方面的气动影响。结果表明,跨音速下导转翼面翼展的增加对翼面及弹体的气动影响并不呈线性关系,存在临界翼展;同时,对当前气动布局,0.95 Ma附近是气动参数变化趋势发生明显改变的马赫数,需要重点关注。In order to study the influence of different guided wings span on the transonic aerodynamic performance of two-dimensional trajectory correction bomb of howitzer,four aerodynamic shapes of different guided wings were formed by changing the size of the guided wings on the condition that the lift wings remained unchanged.Based on Spalart-Allmaras turbulent model,the three dimensional vicious Navier-Stokes equation were solved by finite volume method.The aerodynamic parameters such as drag coefficient,lift coefficient,pitch moment coefficient and roll moment coefficient were obtained.In order to verify the numerical simulation results,wind tunnel experiments were carried out on model 3.By contrast,the unmerical simulation results accorded with the experimental results.Combined with the calculation results of other models,the aerodynamic effects on the guided wings,the lift wing and the body of two-dimensional trajectory correction bomb of howitzer were analyzed respectively.The results showed that there were no linear relationship between the aerodynamic effects and the increase of guide wings span at transonic speed conditions.A critical size were exited among the four models.The variation trend of aerodynamic parameters changed at 0.95 Ma under the current aerodynamic layout.

关 键 词：弹道修正 跨音速 数值模拟 风洞实验 

分 类 号：TJ430[兵器科学与技术—火炮、自动武器与弹药工程]