小展弦比飞翼布局作战飞机可控性设计方法

Design Method of Controllability of Low Aspect-ratio Flying Wing Configuration Combat Aircraft

飞翼布局飞机取消了常规布局飞机采用的安定面和操纵面,由此引起其可控性设计的诸多新问题。以某小展弦比飞翼布局作战飞机为例,利用风洞试验结果研究了几种典型新型操纵面的操纵新机理及不同飞行条件下的操纵效能等。基于可控性设计的要求,估算了该飞翼构型作战使用所需的三轴最大控制力矩系数。通过引进舵容量的概念提出了新型操纵面的参数化设计方法,最后对这一新布局方案进行了可控性评估,为飞翼布局飞机概念设计阶段的新型操纵面布置和设计提供了一种实用的方法。

The flying wing configuration aircraft cancels the stabilizers and control surfaces which are implemented on conventional aircraft.As a result,the new problems are brought into the controllability design.A certain flying wing configuration combat aircraft with low aspect-ratio is chosen as an example.Based on the results of wind tunnel tests,the control principles and effectiveness in different flight conditions of several typical innovative control surfaces are analyzed.The largest coefficients of control moments around three axes required for combat are estimated based on controllability requirements.The concept of control-surface volume is imported to introduce the parameter-based design method of control surface.Finally the controllability of the flying wing configuration aircraft is evaluated.A practical method of allocation and design of innovative control surfaces is provided,which can be used for conceptual design of flying wing configuration aircraft.