腹部襟翼对飞翼布局飞行器起降气动特性的影响  

Effects of belly flap on take-off and landing characteristics of a flying-wing vehicle

作　　者：陈宪 陈诚[1] 黄江涛[1] 陈其盛[1] 余龙舟 钟世东[1] CHEN Xian;CHEN Cheng;HUANG Jiangtao;CHEN Qisheng;YU Longzhou;ZHONG Shidong(China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心,绵阳621000

出　　处：《航空学报》2022年第3期143-154,共12页Acta Aeronautica et Astronautica Sinica

摘　　要：以某飞翼布局飞行器为初始外形,利用数值模拟方法针对起降状态下腹部襟翼的安装位置及偏度进行了选型研究,并得到了腹部襟翼打开对升降舵舵效以及地面效应的影响规律。结果表明,当腹部襟翼位于重心后40%平均气动弦长时,在保持大迎角良好增升效果的同时对俯仰力矩的改变量也较小;随着腹部襟翼偏角变大,升力系数和阻力系数呈现出准线性增长,而俯仰力矩变化量较小,升降舵偏转1°左右即可配平;相比于腹部襟翼关闭状态,腹部襟翼打开后,升降舵舵效降低约6%,飞行器地面效应引起增升量变大,但纵向静稳定度有所降低。Taking a flying wing configuration model as the initial shape of flying wing configuration aircraft,the location and the deflection angle of belly-flaps in the take-off and landing process are studied by the method of numerical simulation,and the influence law of belly-flap deflection on elevator rudder effect and ground effect is obtained.The results show that when the belly-flap is located at 40%mean aerodynamic chord behind the center of gravity,a high lift enhancement efficiency can be maintained at high angles of attack,and there is a small change in the pitching moment.As the deflection angle of the belly-flap increases,the lift and the drag show a quasi linear growth,while the change of the pitching moment is small and can be trimmed by about 1°deflection of the elevator.When the belly-flap is deflected,the rudder efficiency of the elevator decreases by about 6%,and the increment of lift caused by ground effect increases,while the longitudinal static stability is decreased.

关 键 词：飞翼布局 起降状态 腹部襟翼 升降舵 地面效应 

分 类 号：V224.5[航空宇航科学与技术—飞行器设计]