【摘要】：為滿足國(guó)內(nèi)戰(zhàn)斗機(jī)型號(hào)研制對(duì)大迎角過失速機(jī)動(dòng)過程中非定常氣動(dòng)力問題研究的需求,中國(guó)航空工業(yè)空氣動(dòng)力研究院在FL-8風(fēng)洞開發(fā)了一套基于電液伺服馬達(dá)和電機(jī)耦合驅(qū)動(dòng)的雙自由度大幅振蕩試驗(yàn)技術(shù)。簡(jiǎn)單介紹了該系統(tǒng)的基本組成和試驗(yàn)原理,給出了FL-8風(fēng)洞動(dòng)態(tài)標(biāo)準(zhǔn)模型雙自由度大幅振蕩試驗(yàn)的典型結(jié)果,分析表明:該系統(tǒng)運(yùn)行性能穩(wěn)定,試驗(yàn)數(shù)據(jù)可靠,重復(fù)性精度較高,可以有效應(yīng)用于飛行器雙自由度耦合運(yùn)動(dòng)氣動(dòng)特性研究。
[Abstract]:In order to meet the requirements of domestic fighter models for the study of unsteady aerodynamic problems in the process of high angle of attack stall maneuver, A set of two-degree-of-freedom large-amplitude oscillation test technology based on coupling drive of electro-hydraulic servo motor and motor has been developed in FL-8 wind tunnel by China Aeronautical Industry aerodynamics Research Institute. The basic composition and test principle of the system are briefly introduced. The typical results of the two-degree-of-freedom large-amplitude oscillation test of the dynamic standard model of FL-8 wind tunnel are given. The analysis shows that the operation performance of the system is stable and the test data are reliable. Because of its high repeatability, it can be used to study the aerodynamic characteristics of two-degree-of-freedom coupling motion of aircraft.
【作者單位】： 中國(guó)航空工業(yè)空氣動(dòng)力研究院;中國(guó)空氣動(dòng)力研究與發(fā)展中心;
【基金】：航空科學(xué)基金(20143203002)~~
【分類號(hào)】：V211.74
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本文編號(hào)：2442673