摘要
本文目的在于探索验证微小型飞行器的气动布局与抗突风载荷能力的关系,结合风洞试验验证了结果并进行了数据分析。在低雷诺数条件下采用大边条、小展弦比非常规的气动布局设计,根据性能指标要求对飞行器的机翼面积、翼展、翼型等相关参数进行了分析设计;运用数值模拟等手段对全机简化模型进行了气动力计算,对结果进了行初步的定性分析,为初始的设计提供了验证;结合实际的靶机制作得到了实际飞机的风洞验证缩比模型,对其进行了风洞的常规测力实验。根据风洞试验结果对飞机升降舵舵面与副翼舵面偏转0°、±15°、±30°的气动性能进行了评估,为进一步的理论分析提供依据。结合实际外场飞行实验情况得出飞行器的实际气动性能,并对大量相关风洞试验数据进行了分析;探索性地给出了一条适用于微小型飞行器进行的新设计方法和设计流程,为设计适应于阵风载荷等恶劣气候条件下微小的型飞行器提供了参考新思路。
The object of the research is from a key technology of Micro Air Vehicle,which has a strong engineering background.Breaking through the traditional design of small unmanned aircraft aerodynamic layout of conventional restraints,using of unconventional aerodynamic configuration design,by means of wind tunnel tests to conducted data analysis and combining with the actual target drone produced by the actual aircraft elevator,we perform the evaluation of aileron's aerodynamic control surface deflection,which may help theoretical analysis in turn.This article is designed to the big and small aspect ratio of non-conventional micro and small aircraft aerodynamic layout by means of numerical simulations to give a preliminary qualitative analysis.From wind tunnel force measurement experiments and by using wind tunnel test results on the aircraft performance evaluation,we verify the aircraft's elevator and aileron manipulation effect.Combined with actual field conditions of flight,the actual aerodynamic performance of aircraft conclusions can be reached.
出处
《应用力学学报》
CAS
CSCD
北大核心
2011年第6期649-653,677,共5页
Chinese Journal of Applied Mechanics
基金
国家自然科学基金重点项目(60736025)
