窄条翼布局导弹摇滚特性及流动机理
收稿日期: 2016-05-09
修回日期: 2016-08-24
网络出版日期: 2016-09-26
基金资助
国家自然科学基金（11372336，91216203，11532016）
Rock motion and flow mechanism of missile configuration with strake wings
Received date: 2016-05-09
Revised date: 2016-08-24
Online published: 2016-09-26
Supported by
National Natural Science Foundation of China (11372336, 91216203, 11532016)
冯黎明 , 达兴亚 , 吴军强 , 赵忠良 . 窄条翼布局导弹摇滚特性及流动机理[J]. 航空学报, 2017 , 38(4) : 120410 -120410 . DOI: 10.7527/S1000-6893.2016.0252
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 5 to 6 diameters. 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.
Key words： strake wing; missile; limit-cycle rock; dynamic; flow interference
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