【摘要】：為滿足國內戰(zhàn)斗機型號研制對大迎角過失速機動過程中非定常氣動力問題研究的需求,中國航空工業(yè)空氣動力研究院在FL-8風洞開發(fā)了一套基于電液伺服馬達和電機耦合驅動的雙自由度大幅振蕩試驗技術。簡單介紹了該系統(tǒng)的基本組成和試驗原理,給出了FL-8風洞動態(tài)標準模型雙自由度大幅振蕩試驗的典型結果,分析表明:該系統(tǒng)運行性能穩(wěn)定,試驗數(shù)據(jù)可靠,重復性精度較高,可以有效應用于飛行器雙自由度耦合運動氣動特性研究。
[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】： 中國航空工業(yè)空氣動力研究院;中國空氣動力研究與發(fā)展中心;
【基金】：航空科學基金(20143203002)~~
【分類號】：V211.74
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本文編號：2442673