某大型飞机后缘襟翼气动/机构综合优化设计

大型飞机增升装置的研制不仅需要其提供足够的气动性能,也需要对噪声、舒适性等进行综合考量设计,而增升装置是提高大型飞机综合性能的重要系统,也是目前技术发展亟待研究和解决的重要问题。对于增升装置机构设计,通过设计较为简单的铰链襟翼机构来引导襟翼达到较优位置,然后选择气动性能较好的位置作为新的优化位置,求得较优机构位置。机构位置改变结合气动性能验证需要进行大量的迭代计算以及结果优化,因此以机构设计为基础,探究多目标优化计算的新方法,最终实现气动结构一体化设计目标。选用铰链式后缘襟翼为研究对象,综合考量后缘襟翼旋转与扰流板下偏联合运动对于气动性能影响,利用所研究方法,对其进行气动机构一体化设计并得出设计结果。

Comprehensive optimization design of aerodynamics/mechanism of the trailing edge flap of a large aircraft

The development of a large aircraft lift device not only requires to provide sufficient aerodynamic performance, but also requires comprehensive consideration of noise and comfort. The lift device is an important system to improve the overall performance of large aircraft, and also a key problem to be studied and solved in current technology development. For the mechanism design of the lift device, the method adopted in this paper is to guide the flaps to a better position by designing a relatively simple hinge flap mechanism, and then select the position with better aerodynamic performance as the new optimized position to obtain the better mechanism position. The mechanism position change combined with aerodynamic performance verification requires a lot of iterative calculations and result optimization. Based on the mechanism design, this article explores a new method of multi-objective optimization calculation, and finally achieves the goal of integrated design of aerodynamic structure. In this paper, the hinged trailing edge flap is selected as the research object, and the combined movement of trailing edge flap rotation and spoiler downward deflection on the aerodynamic performance is comprehensively considered. Using the research method, the integrated design of aerodynamic mechanism is carried out and the design results are obtained.