CAJ | 학술논문

针对某大展弦比多控制面弹性机翼风洞模型,分别从频域和时域进行阵风响应分析和阵风响应减缓控制律设计.采用经典控制理论设计控制律,通过操纵位于0.6和0.8翼展处的内外侧控制面减小由正弦阵风引起的翼尖加速度(WTA).低频段的阵风减缓的数值分析与风洞试验结果均表明:多控制面的阵风减缓效果优于单控制面.当来流速度为14 m/s时,针对频率为2～5 Hz的阵风,采用多控制面得到的WTA减小10%～24%;当来流速度在8～16 m/s时,针对频率为2 Hz的正弦阵风,闭环状态下的翼尖加速度减小10%～40%;结构有限元模型与真实模型存在工程允许的误差导致理论与试验结果存在一定的误差.本文的工作对工程实际中采用阵风减缓技术具有参考价值.
침대모대전현비다공제면탄성궤익풍동모형,분별종빈역화시역진행진풍향응분석화진풍향응감완공제률설계.채용경전공제이론설계공제률,통과조종위우0.6화0.8익전처적내외측공제면감소유정현진풍인기적익첨가속도(WTA).저빈단적진풍감완적수치분석여풍동시험결과균표명:다공제면적진풍감완효과우우단공제면.당래류속도위14 m/s시,침대빈솔위2～5 Hz적진풍,채용다공제면득도적WTA감소10%～24%;당래류속도재8～16 m/s시,침대빈솔위2 Hz적정현진풍,폐배상태하적익첨가속도감소10%～40%;결구유한원모형여진실모형존재공정윤허적오차도치이론여시험결과존재일정적오차.본문적공작대공정실제중채용진풍감완기술구유삼고개치.
Based on a wind tunnel model of a high aspect ratio elastic wing which has multi-control surfaces, frequency-domain and time-domain approaches to gust response analysis and gust response alleviation control law design are presented. The control laws are designed using classical control theory. The control surfaces, which are located at 0.6 and 0.8 of the wingspan, are manipulated to reduce the wing-tip acceleration (WTA) excited by "sine" gust. Numerical analysis and test results on the low frequency show that gust alleviation using multi-control surfaces is better than that of single control surface. When the air speed is 14 m/s and the gust frequency ranges from 2-5 Hz, the WTA using multi-control surfaces is alleviated by 10%-24%. When the air speed ranges from 8-16 m/s, the WTA in close-loop is alleviated by 10%-40% for the "sine" gust whose frequency is 2 Hz. The error between the finite element model and the reality model brings on the error between the results obtained by theory and test. This article are of reference value to extend gust alleviation technique to engineering application.