操纵面作动对无尾布局无人机纵向气动特性的影响

通过风洞测力实验,研究了不同操纵面作动对某无尾布局无人机纵向气动特性的影响。实验结果表明:升降副翼以及襟副翼正向偏转都会使全机升力系数、阻力系数以及低头力矩增加。升降副翼作动引起的增量要高于襟副翼,并且舵偏角度越大增量越大。全动翼尖作动对全机纵向气动特性基本没有影响。在线性段,鸭翼作动对升力系数和阻力系数影响不大;线性段之外,鸭翼作动使得升力系数和阻力系数减小。迎角α<16°以及α>38°时,鸭翼正向作动使得低头力矩减小,负向作动使得低头力矩增加。操纵面作动对低头力矩的控制效率由高到低依次为:升降副翼、襟副翼、鸭翼和全动翼尖。进一步分析表明不同操纵面的控制效率与舵容量系数具有较大关系。

Influence of control surfaces deflection on longitudinal aerodynamic characteristics of a tailless unmanned aerial vehicle

Influence of control surfaces deflection on longitudinal aerodynamic characteristics of a tailless unmanned aerial vehicle(UAV) with multiple control surfaces was investigated in a wind tunnel using force measurement.Positive deflection of both elevons and flaperons leads to an increment of lift coefficient,drag coefficient and nose-down pitching moment,and the increment is much more significant with a larger deflection angle.Elevons have a better effect than flaperons.However,all-moving tips(AMTs) deflection nearly has no influence on longitudinal aerodynamic characteristics.When deflecting canard wings,lift coefficient and drag coefficient nearly have no changes before stall,while they are reduced after stall.When α<16° and α>38°,positive deflection of canard wings reduces the nose-down pitching moment,and negative deflection increases the nose-down pitching moment.The order of pitching moment control efficiency from higher to lower is: elevons,flaperons,canard wings,AMTs.Further analysis indicates that the control efficiency is related to the control surface volume coefficient.