扰流板对内埋导弹偏航姿态角的影响  

Spoiler's Effect on the Yawing Attitude Angle of the Missile in the Bay

作　　者：管德会 蔡为民[1] 

机构地区：[1]中航工业沈阳飞机设计研究所,辽宁沈阳110035

出　　处：《航空学报》2014年第4期942-947,共6页Acta Aeronautica et Astronautica Sinica

基　　金：国家级项目~~

摘　　要：在内埋武器舱前缘设计扰流板进行流动控制,可改善内埋导弹分离过程的偏航力矩特性,从而使弹头反向舱门,保证分离航向安全。为了研究该问题,通过理论分析在内埋武器舱前缘设计了不同高度的扰流板;通过部件测力风洞试验研究了不同高度扰流板对舱内流型、内埋导弹偏航力矩特性的影响,进而分析了扰流板对内埋导弹偏航分离特性的影响;通过轨迹捕获风洞试验验证了分离偏航姿态角特性分析的可靠性。研究结果表明:在内埋武器舱前缘设计一定高度的扰流板可以有效控制舱内流型,改善内埋导弹分离的航向气动特性,提高分离航向安全性。A number of spoilers are designed in the leading edge of the weapons bay which may possibly control the flow and improve the yawing moment characteristic in the missile separating course so as to force the missile＇s head to reverse for the safety of the separation yawing. To study the problem, spoilers of different heights are built in the leading edge of the weapons bay through theoretical analysis and a wind tunnel test is conducted to measure the forces acting on the parts so as to study the spoilers＇ effect on the flow patterns in the bay and the missile＇s yawing moment characteristics. Furthermore, the spoilers＇ effect on the missile＇s yawing separation characteristics is analyzed, and the credibility of the separation ya- wing attitude angle characteristic analysis is validated by a track capture wind tunnel test. The result shows that designing spoilers with certain heights in the leading edge of the weapons bay can effectively control the flow patterns in the bay, im- prove the missile＇s yawing aerodynamic characteristic, and improve the separating yawing safety.

关 键 词：武器舱 扰流板 流动控制 风洞试验 分离特性 姿态角 

分 类 号：V211.46[航空宇航科学与技术—航空宇航推进理论与工程] O353.5[理学—流体力学]