飞行力学
飛行力學
비행역학
FIIGHT DYNAMICS
2010年
2期
16-19
,共4页
闭环系统%气动参数辨识%极大似然估计
閉環繫統%氣動參數辨識%極大似然估計
폐배계통%기동삼수변식%겁대사연고계
closed loop system%aerodynamic parameter identification%maximum likelihood estimation
对于闭环控制飞行器动力学系统,如果输入输出数据中含有误差和噪声,将其直接用于辨识气动参数是有偏差的.针对这个问题,利用闭环控制飞行仿真数据,采用两步方法辨识飞行器的气动参数,并与直接开环辨识的结果及参数真值进行对比,表明两步方法辨识结果较直接开环辨识方法具有更高的精度,是一种有效的闭环气动参数辨识方法.
對于閉環控製飛行器動力學繫統,如果輸入輸齣數據中含有誤差和譟聲,將其直接用于辨識氣動參數是有偏差的.針對這箇問題,利用閉環控製飛行倣真數據,採用兩步方法辨識飛行器的氣動參數,併與直接開環辨識的結果及參數真值進行對比,錶明兩步方法辨識結果較直接開環辨識方法具有更高的精度,是一種有效的閉環氣動參數辨識方法.
대우폐배공제비행기동역학계통,여과수입수출수거중함유오차화조성,장기직접용우변식기동삼수시유편차적.침대저개문제,이용폐배공제비행방진수거,채용량보방법변식비행기적기동삼수,병여직접개배변식적결과급삼수진치진행대비,표명량보방법변식결과교직접개배변식방법구유경고적정도,시일충유효적폐배기동삼수변식방법.
For dynamic system of aircraft in closed loop control, the results will be partially inaccurate if in-out data with errors and noises is used for identifying the aerodynamic parameters. In this thesis, the two-step method of aerodynamic parameter identification for aircraft in the closed loop control is developed. The aerodynamic parameters are estimated for simulation example of aircraft in the closed loop control, and the results are compared with parameter's true values and the results of identification by open loop method, it is shown that the closed loop aerodynamic parameter identification method is validated.
