摘要
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。
A morphing airfoil instead of traditional horizontal stabilizer and control elements is proposed in order to make the aircraft keep the optimal lift/drag ratio during flight attitude controlling. Bornstein polynomial with order ＂n＂ is used to describe the airfoil configuration. A set of airfoil that can provide a minimum drag coefficient at different lift coefficient in a confirmed flight environment is obtained by aerodynamic optimization simulation using the genetic algorithm. It is proved that the morphing airfoil can provide a smaller drag coefficient than the traditional control element do when the same lift coefficient is provided. The relationship between shape control parameters and lift is fitted according to the optimized airfoil. A set of example is used to verify the morphing regularity.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2012年第6期780-785,共6页
Journal of Nanjing University of Aeronautics & Astronautics
基金
国家自然科学基金(50905085
91116020
11002072)资助项目
关键词
变体机翼
变形机构
传统控制面
气动特性
优化设计
morphing wing
deformation structure
traditional control surface
aerodynamic character
optimization design
