窄条翼布局导弹摇滚特性及流动机理

Rock motion and flow mechanism of missile configuration with strake wings

钝头体窄条翼布局导弹在大攻角下拥有极为优异的纵向气动特性,但横向容易失稳,做快速机动时容易诱发非指令的横向不稳定运动。通过开展高速风洞自由摇滚试验和数值模拟,研究了窄条翼导弹自由摇滚特性和流动机理,试验与计算吻合较好。研究发现:较大迎角时,窄条翼面积中心距离尾舵前缘根部5~6倍直径时,模型会进入极限环摇滚,窄条翼位置对模型稳定性有显著的影响,去掉窄条翼或尾舵时,模型均不会进入摇滚;模型空间流场特性表明,气流经过窄条翼时形成的片涡,对背风舵产生强烈的干扰,抑制了尾舵涡的形成和发展,使背风舵动态失稳,导致模型进入极限环摇滚。

Blunt forebody missile configuration with strake wings has excellent longitudinal aerodynamic characteristics,but has serious problems in lateral stability to induce uncommanded motion in unsteadily lateral direction when the missile maneuvers rapidly.Free-to-roll aerodynamics and flow mechanism of missile with strake wings are studied through high speed wind turnel free-to-roll tests and numerical simulation.Results of simulations agree well with wind tunnel test results.Study shows that model enters into limit cycle rock when the distance between the center of the area of strake wings and leading edge of tail fins is 5to 6diameters.Position of strake wings has significant effect on the stability of model.The model will not enter into limit-cycle rock when strakes or tail fins are removed.Spacial flow characteristics show that the wing vortices generated by strake wings can strongly interfere leeward fins to affect the formation and development of fin vortices.This leads to the loss of dynamic stability of leeward fins,and model thus enters limit-cycle rock.