论文部分内容阅读
为了使飞机在控制飞行姿态时仍然能保持最优升阻比,提出了一种通过改变翼型形状来代替传统控制舵面来控制飞机俯仰的方法。采用伯恩斯坦多项式对机翼的翼型进行数学建模,并采用遗传算法通过空气动力学仿真对翼型进行优化得到一组在一定飞行环境下、产生附加阻力最小且随升力系数变化的翼型形状。通过对比证明在提供相同升力的情况下,变体翼比传统的控制舵面产生更小的附加阻力。根据翼型形状和升力系数的变化采用数据拟合的方法得到翼型形状控制参数随升力变化的规律。通过算例对变化规律的验证表明其可以用来作为飞行姿态控制的翼型形状变化依据。
In order to maintain the optimal lift-drag ratio in the control of flight attitude, a method of controlling the pitch of the aircraft by changing the shape of the airfoil instead of the traditional control surface is proposed. The Bernstein polynomial is used to mathematically model the airfoil of the wing and the aerodynamic simulation is used to optimize the airfoil using genetic algorithm to obtain a set of wings that generate the least additional drag and vary with the lift coefficient under a certain flight environment Shape. By contrast it is demonstrated that the variant wing produces less additional drag than the conventional control surface in providing the same lift. According to the change of airfoil shape and lift coefficient, the law of airfoil shape control parameters with the change of lift is obtained by data fitting method. The verification of the change rule by the example shows that it can be used as the airfoil shape change control based on the flight attitude control.