摘要
为了保证滑翔增程弹箭在滑翔飞行过程中有效地增程,必须对滑翔弹箭的舵面进行气动设计与分析.阐述了制导炮弹舵面参数确定的原则,研究了滑翔增程弹舵面几何参数的选择、舵面尺寸确定的方法.仿真结果表明,采用该方法确定的舵面气动性能能够保证滑翔增程弹在滑控段飞行过程中稳定性适当,静稳定性储备量约在4%左右;操纵性较好,舵面偏转10°,能够产生约6°的平衡攻角;稳定性与操纵性、舵偏角和平衡攻角匹配较好,为滑翔增程弹舵面的气动设计提供了参考.
In order to assure that the range of gliding extended range projectile can be extend- ed efficiently, the aerodynamic design and analysis of canard rudder surface of gliding projectile were carried. The principle used to confirm rudder surface parameters of guided projectile was explained. In point of the gliding extended range projectile, the choice of canards parameters and the confirmation method of canards size were studied. The simulation results show that the aerodynamic performance of rudder surface confirmed by this method can provide enough stability while projectile is flying in the course of gliding control. The static stability storage is about 4%. The flexibility is better, and 6° balanceable angle of attack can be brought about when rudder surface is rotated 10°. The matching between stability and flexibility, rotating angle of canard and balanceable angle of attack is better. The method provides reference for the aerodynamic design of rudder surface simulation of the gliding extended range projectile.
出处
《弹道学报》
EI
CSCD
北大核心
2006年第4期33-37,共5页
Journal of Ballistics
关键词
滑翔增程弹
鸭式舵
稳定性
操纵性
gliding extended range projectile
canard rudder
stability
flexibility
