飞翼式UCAV低空段动静稳定性研究

采用飞翼式气动布局的UCAV能够很好地满足现代作战的要求。这种非常规布局的飞机, 由于它缺少尾翼, 对于飞机的动静稳定性分析来说是一个挑战。对于无垂尾飞机, 其稳定性的主要努力方向应该在低空段。本文在低空段, 对于飞机的纵向和侧向运动上采用解藕的分析方法获得飞机的运动方程; 接着根据风洞试验的数据, 在MATLAB中建立仿真模型获得飞机的仿真曲线, 通过对仿真曲线的分析, 验证了飞机的纵向和侧向的不稳定性。最后, 通过与已经成功应用于实战的B-2隐形飞机的对比, 分析了在应用控制增稳的控制技术后, 飞翼式布局的UCAV的实用性。

Static And Dynamic Stability Analysis of a Flying Wing UCAV in Low Altitude Flight Phase

Flying wing UCAV will satisfy requirements for future wars. Because the flying wing UCAV, as an unconventional configuration , has no empennage, it will be a challenge to analyze the static and dynamic stabilities of the vehicle. For the tailless air vehicle, the consideration of stability shall be given in the low altitude flight phase. In this paper, the vehicle equations of motion are derived using a longitudinal/lateral motion decoupling analysis technique, A simulation model is created in MATLAB from available wind tunnel data. The analysis of simulation curves shows that the vehicle is unstable in the longitudinal and lateral axes. It is suggested by reference to the B-2 bombing aircraft which has proven successful in wars that using a control augmentation system, the flying-wing configuration of UCAV will be practicable.