Design method of controllability of low aspect-ratio flying wing configuration combat aircraft

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.