飞翼飞机开裂式阻力方向舵铰链力矩的预测

Split drag rudder hinge moment predict for flying wing aircraft

飞翼布局无人机开裂式阻力方向舵是一新型操纵面。文中对开裂式阻力方向舵对飞翼的航向操纵特性进行了分析,建立了舵面受力模型和全面的航向舵容量计算公式。通过全机风洞测力试验数据分析证实该模型合理、正确。依据该受力模型将舵面铰链力矩和全机受力联系起来,建立了一种新的通过全机测力试验数据预测开裂式阻力方向舵铰链力矩的实用方法。最后通过风洞测压试验结果得到阻力舵铰链力矩,并与预测结果进行了比较。两者最大相对误差为15%,且舵偏角越大,误差越小。40°舵偏时误差仅为2.5%。

Split drag rudders（SDR） with flying wing aircraft are innovative control surfaces.Relate to it,this paper analyzes moment for yawing control characteristics,constructs the force model for SDR and more general SDR control volume formula.Using the flying wing aircraft model wind tunnel dynamometry experimentation data,this paper proves that the force model for SDR is precise.According as this model,the hinge moment of SDR and the force received by aircraft are contacted.Using wind tunnel dynamometry experimentation data,a new rough estimation method is constructed to compute the hinge moment of SDR.Through SDR model wind tunnel pressure measure data,then the hinge moment is computed.The rough estimation result and pressure measure result are compared.The most fractional error between them is 15%.It is important that rudder deflection is bigger while the fractional error is smaller.When rudder deflection is 40 degree,the fractional error is only 2.5%.