小长细比制导火箭提高操纵性气动布局研究

为了在保证小长细比火箭具有静稳定性的同时进一步提高操纵性,平衡静稳定度与操纵性的矛盾,在原有弹箭模型基础上加装反安定面后对2种模型进行数值仿真,分析了反安定面对全弹流场以及气动特性的影响。各部件气动分析结果表明:全弹法向力系数提高了2%～3%,静稳定度下降,压心向质心靠近; 全弹法向力使得法向过载提高,全弹机动性得到提高。加装反安定面之后使弹头部法向力提高,在一定攻角范围内上尾舵受洗流干扰严重,使上尾舵法向力效率有所降低,尾部升力减小,降低了静稳定度,两部分同时作用使全弹操纵性显著提高。

Study on Improving Maneuverable Aerodynamic Layout of GuidedRockets With Small Length to Diameter Ratio

In order to further improve the maneuverability of rockets with small length-diameter ratio while ensuring the static stability and balancing the contradiction between the static stability and the maneuverability,the anti-stable wings were installed on the basis of the original projectile model,and the numerical simulation of the two models was carried out,and the influence of anti-stable wings on the flow field and aerodynamic characteristics of whole projectile was analyzed. The results show that the normal force coefficient of the whole projectile is increased by 2%-3%,and the static stability is decreased,and the pressure center is close to the centroid. The normal overload is increased due to the normal force of whole projectile. After installing the anti-stable wings,the normal force of the warhead is increased,and the upper tail rudder is affected seriously by the down wash flow within a certain angle of attack,and the normal force efficiency of the upper tail rudder is reduced. The tail lift is reduced,and the static stability is reduced. The maneuverability of the whole projectile is increased significantly when the two parts work at the same time.