摘要
对复合材料前掠翼的亚临界发散试验和模型设计技术进行研究。采用测量结构应变的Southwell亚临界发散试验技术,对两个大展弦比复合材料机翼进行发散动压的亚临界预测。在亚临界风洞试验前进行了发散动压的计算,其后特别进行了临界发散风洞试验,以对Southwell亚临界发散预测方法进行验证。计算结果和临界试验结果均表明,利用Southwell亚临界发散试验技术进行大展弦比复合材料机翼发散动压的预测能够取得较好的效果。该亚临界方法可以推广到高速模型发散试验和飞行试验。同时也验证了模型发散速度随着前掠角的增大而减小的结论。
The divergence experimental prediction and model design techniques were studied for composite forward -swept wings, and the Southwell method, a subcritical divergence experimental technique with testing of structural strain, was used to predict the divergence dynamic pressure. Two high-aspect-ratio composite forward-swept wings were tested using the subcritical method. In order to predict and validate the results of the subcritical experiment, the divergence dynamic pressures were calculated prior to the subcritical wind-tunnel experiment, and the critical divergence wind-tunnel experiments were performed especially after the subcritical wind-tunnel experiment. Both the calculation results and testing results indicate that better results could be attained by using the Southwell method. The subcritical method could be used in high-pressure divergence tests and flight tests. The divergence speed decreases with increase of the forward-swept angle.
出处
《复合材料学报》
EI
CAS
CSCD
北大核心
2008年第1期200-204,共5页
Acta Materiae Compositae Sinica
基金
国家自然科学基金(10502003
10432040)
新世纪优秀人才支持计划(NCET-04-0170)
关键词
气动弹性
发散
亚临界发散试验技术
前掠翼
复合材料
大展弦比机翼
aeroelasticity
divergence
subcritical divergence experimental technique
forward swept wing
composite
high- aspect- ratio wing
