次口径非对称鸭舵对弹道修正弹气动特性的影响  

Study on the Effect of Sub-Caliber Asymmetry Canards on the Aerodynamics of Trajectory Correction Projectiles

作　　者：程杰[1] 王晓鸣[1] 于纪言[1] 姚文进[1] 

机构地区：[1]南京理工大学智能弹药技术国防重点学科实验室,江苏南京210094

出　　处：《北京理工大学学报》2015年第2期133-138,共6页Transactions of Beijing Institute of Technology

基　　金：中央高校基本科研业务费专项基金资助项目(30920130122001)

摘　　要：为研究次口径非对称鸭式布局的弹道修正弹气动特性,基于网格装配的方法建立了修正弹气动力计算模型,并通过风洞试验对超音速条件下的计算结果进行验证,从鸭舵绕流、升阻系数和滚转力矩方面分析鸭舵对修正弹气动参数的影响.研究结果表明,次口径非对称鸭舵使修正弹相比传统弹丸阻力系数增加达14%,但操纵舵引起的升力使弹丸的射程衰减率降至10%.鸭舵安装角对修正弹升力影响效果大于阻力.通过工程简化模型将升力分解为操纵舵提供的升力和由于鸭舵的存在使弹体产生的升力两部分,拟合出鸭舵对弹体升力的干扰因子.To investigate the aerodynamics of trajectory correction projectiles （TCP） with sub- caliber asymmetry canards, a numerical model was established based on the assembling mesh, and its accuracy was validated by the results of wind tunnel tests. The effect of canards on TCP was analyzed in three aspects, flow around canards, lift and drag coefficients as well as the roll moment supplied by spin canards. The results indicate that the drag coefficient increases by 14% than conventional projectiles, but the lift created by maneuver canards improves the percentage of range reduction to 10%. The cant angles of canards have more significant effect on lift than drag. The TCP＇s lift is contributed by two parts： surfaces of maneuver canards and the asymmetry pressure distribution on projectiles for the existence of canards. A simplified model was utilized to express the lift coefficient with a confounding factor obtained by curve fitting.

关 键 词：气动特性 弹道修正 鸭舵 风洞试验 非对称 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]