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一種提高風(fēng)洞動(dòng)態(tài)試驗(yàn)數(shù)據(jù)質(zhì)量的模型姿態(tài)控制和測(cè)量技術(shù)

發(fā)布時(shí)間:2018-10-18 19:14
【摘要】:低速風(fēng)洞動(dòng)態(tài)試驗(yàn)裝置通常采用“電機(jī)+減速器+偏心機(jī)構(gòu)+線性傳動(dòng)機(jī)構(gòu)”的方式,存在傳遞環(huán)節(jié)多、機(jī)械間隙大等問(wèn)題,給模型運(yùn)動(dòng)的精確控制和模型姿態(tài)的精確測(cè)量帶來(lái)較大困難。為滿足大型客機(jī)等大飛機(jī)對(duì)低速風(fēng)洞動(dòng)態(tài)試驗(yàn)的要求,基于現(xiàn)有的靜態(tài)試驗(yàn)通用支撐平臺(tái),采用“電子凸輪”技術(shù),建立了一套迎角/側(cè)滑角解耦、可進(jìn)行飛機(jī)小振幅動(dòng)導(dǎo)數(shù)和大振幅非定常氣動(dòng)特性研究的動(dòng)態(tài)試驗(yàn)裝置。利用該動(dòng)態(tài)試驗(yàn)裝置進(jìn)行了某飛機(jī)大尺度動(dòng)態(tài)試驗(yàn)?zāi)P蛣?dòng)導(dǎo)數(shù)試驗(yàn)和大振幅振蕩試驗(yàn),獲得了試驗(yàn)數(shù)據(jù)的重復(fù)性,并研究了動(dòng)態(tài)試驗(yàn)數(shù)據(jù)和靜態(tài)試驗(yàn)數(shù)據(jù)之間的相關(guān)性。試驗(yàn)結(jié)果表明:利用該裝置獲得的某飛機(jī)動(dòng)態(tài)試驗(yàn)數(shù)據(jù)重復(fù)性較好、規(guī)律合理,能滿足大型飛機(jī)動(dòng)態(tài)試驗(yàn)要求。
[Abstract]:The low speed wind tunnel dynamic test device usually adopts the "linear drive mechanism of the eccentric mechanism of the motor reducer", which has many transfer links and large mechanical clearance, etc. It is difficult to control the motion of the model and to measure the attitude of the model accurately. In order to meet the requirement of low speed wind tunnel dynamic test for large airliner and other large aircraft, a set of decoupling of angle of attack / side slip angle is established based on the existing universal support platform of static test and "electronic cam" technology. A dynamic test device that can be used to study the unsteady aerodynamic characteristics of aircraft with small amplitude dynamic derivative and large amplitude. The dynamic derivative test and large amplitude oscillation test of a large scale dynamic test model of an aircraft were carried out by using this dynamic test device. The repeatability of the test data was obtained, and the correlation between the dynamic test data and the static test data was studied. The experimental results show that the dynamic test data obtained by this device have good repeatability and reasonable regularity, and can meet the requirements of large aircraft dynamic test.
【作者單位】: 西北工業(yè)大學(xué)航空學(xué)院;中國(guó)空氣動(dòng)力研究與發(fā)展中心;
【分類號(hào)】:V211.7

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