简控火箭弹舵翼气动干扰特性研究
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摘要
为了研究固定鸭舵简控火箭弹舵翼气动干扰特性,在验证数值方法适用性和可靠性的基础上,采用数值模拟方法对该弹气动特性进行仿真分析。计算得到不同弹长和不同舵翼相对夹角(鸭舵组件反旋角)工况下由鸭舵和尾翼产生的空气动力参数,仿真获得火箭弹外流场压力分布。研究分析了弹体长径比和舵翼相对夹角对鸭舵和尾翼气动特性的影响规律。结果表明:鸭舵与尾翼之间的气动干扰受弹体长径比影响,当弹体长径比达到一定数值时鸭舵对尾翼的气动干扰消失,且这种舵翼气动干扰特性对不同舵翼相对夹角情况同样适用;研究结果可用于简化固定鸭舵火箭弹气动特性的研究方法,提高火箭弹气动外形设计效率。
In order to study the aerodynamic interference characteristics between the canard rudder and tail fin of simple-control rocket with fixed canard rudder( SCR),the applicability and reliability of the numerical methods were validated firstly,and then the numerical simulation method was used to simulate and analyze the aerodynamic characteristics of the rocket. The aerodynamic parameters of the canard rudder and tail fin under different projectile lengths and different relative angles between the canard rudder and tail fin( anti-rotation angles of the canard rudder assemblies) were calculated,and the pressure distribution of the flow field of rocket was obtained by simulation. The effects of the ratio of length to diameter of the rocket and relative angle between the canard rudder and tail fin on the aerodynamic characteristics of the canard rudder and tail fin were analyzed. Calculation results show that the aerodynamic interference between the canard rudder and the tail fin is affected by the ratio of length to diameter of the rocket. When the ratio of length to diameter of the rocket reaches a certain value,the aerodynamic interference of the fixed canard to tail fin disappears,and the aerodynamic interference characteristics between the canard rudder and tail fin are also applicable to the situations of different relative angles between the canard rudder and tail fin. The research results can be used to simplify the research method of the aerodynamic characteristics for the fixed canard rudder rocket,and improve the design efficiency of its aerodynamic shape.
In order to study the aerodynamic interference characteristics between the canard rudder and tail fin of simple-control rocket with fixed canard rudder( SCR),the applicability and reliability of the numerical methods were validated firstly,and then the numerical simulation method was used to simulate and analyze the aerodynamic characteristics of the rocket. The aerodynamic parameters of the canard rudder and tail fin under different projectile lengths and different relative angles between the canard rudder and tail fin( anti-rotation angles of the canard rudder assemblies) were calculated,and the pressure distribution of the flow field of rocket was obtained by simulation. The effects of the ratio of length to diameter of the rocket and relative angle between the canard rudder and tail fin on the aerodynamic characteristics of the canard rudder and tail fin were analyzed. Calculation results show that the aerodynamic interference between the canard rudder and the tail fin is affected by the ratio of length to diameter of the rocket. When the ratio of length to diameter of the rocket reaches a certain value,the aerodynamic interference of the fixed canard to tail fin disappears,and the aerodynamic interference characteristics between the canard rudder and tail fin are also applicable to the situations of different relative angles between the canard rudder and tail fin. The research results can be used to simplify the research method of the aerodynamic characteristics for the fixed canard rudder rocket,and improve the design efficiency of its aerodynamic shape.
引文
[1]钟扬威,王良明,张立研,等.一种基于速度方向修正的旋转稳定弹弹道跟踪制导方法研究[J].弹道学报,2017,29(4):15-21.ZHONG Yangwei,WANG Liangming,ZHANG Liyan,et al.Study on trajectory tracking guidance method for spin stabilized projectile based on velocity direction correction[J].Journal of Ballistics,2017,29(4):15-21.(in Chinese)
[2]ROGERS J,COSTELLO M.Design of a roll-stabilized mortar projectile with reciprocating canards[J].Journal of Guidance Control&Dynamics,2015,33(4):1026-1034.
[3]WEMERT P,LEOPOLD F,BIDINO D,et al.Wind tunnel tests and open-loop trajectory simulations for a 155 mm canards guided spin stabilized projectile[C]//AIAA Atmospheric Flight Mechanics Conference.Honolulu,Hawaii:AIAA,2008:1327-1343.
[4]CHANG S.Dynamic response to canard control and gravity for a dual-spin projectile[J].Journal of Spacecraft&Rockets,2016,53(3):1-9.
[5]常思江,王中原,刘铁铮.鸭式布局双旋弹飞行动力学建模与仿真[J].弹道学报,2014,26(3):1-5.CHANG Sijiang,WANG Zhongyuan,LIU Tiezheng.Modeling and simulation of flight dynamics for dual-spin stabilized projectile equipped with canards[J].Journal of Ballistics,2014,26(3):1-5.(in Chinese)
[6]WANG Yu,WANG Xiaoming,YU Jiyan.Influence of control strategy on stability of dual-spin projectiles with fixed canards[J].Defence Technology,2018,14(6):709-719.
[7]BLAZEK J.Computational fluid dynamics:principles and applications[M].London:Elsevier Science,2005.
[8]吴萍.二维弹道修正弹气动布局分析[D].南京:南京理工大学,2014.WU Ping.The aerodynamic configuration analysis of two-dimension trajectory correction projectile[D].Nanjing:Nanjing University of Science&Technology,2014.(in Chinese)
[2]ROGERS J,COSTELLO M.Design of a roll-stabilized mortar projectile with reciprocating canards[J].Journal of Guidance Control&Dynamics,2015,33(4):1026-1034.
[3]WEMERT P,LEOPOLD F,BIDINO D,et al.Wind tunnel tests and open-loop trajectory simulations for a 155 mm canards guided spin stabilized projectile[C]//AIAA Atmospheric Flight Mechanics Conference.Honolulu,Hawaii:AIAA,2008:1327-1343.
[4]CHANG S.Dynamic response to canard control and gravity for a dual-spin projectile[J].Journal of Spacecraft&Rockets,2016,53(3):1-9.
[5]常思江,王中原,刘铁铮.鸭式布局双旋弹飞行动力学建模与仿真[J].弹道学报,2014,26(3):1-5.CHANG Sijiang,WANG Zhongyuan,LIU Tiezheng.Modeling and simulation of flight dynamics for dual-spin stabilized projectile equipped with canards[J].Journal of Ballistics,2014,26(3):1-5.(in Chinese)
[6]WANG Yu,WANG Xiaoming,YU Jiyan.Influence of control strategy on stability of dual-spin projectiles with fixed canards[J].Defence Technology,2018,14(6):709-719.
[7]BLAZEK J.Computational fluid dynamics:principles and applications[M].London:Elsevier Science,2005.
[8]吴萍.二维弹道修正弹气动布局分析[D].南京:南京理工大学,2014.WU Ping.The aerodynamic configuration analysis of two-dimension trajectory correction projectile[D].Nanjing:Nanjing University of Science&Technology,2014.(in Chinese)