摘要
飞行试验是获取返回器在真实飞行条件下气动力参数的重要途径,气动辨识结果对于评估理论计算和风洞实验气动数据,改进气动设计具有重要意义。月地高速再入气动环境复杂,气动力预测困难,结果具有很大不确定性,因此给出气动辨识结果的偏差是十分必要的。本文针对月地高速再入飞行试验,发展了返回器气动力参数辨识方法,并利用返回器飞行试验数据提取到了关键气动力参数。研究了返回器气动辨识数据偏差分析技术,剖析了各误差因素产生的气动偏差,并分析了产生气动参数辨识偏差的主要因素。在此基础上利用蒙特卡洛分析方法,计算得到了所有误差综合影响条件下返回器气动辨识结果的偏差区间。结果表明,大气密度、加速度、姿态角、高度、速度等参数的测量误差是产生辨识偏差的主要因素,全程配平迎角的估计结果精度很高,高空稀薄大气段气动力系数和升阻比等参数偏差较大,利用修正克拉马-罗界作为准则计算俯仰力矩导数和喷流推力辨识偏差是可行的。本文获取的月地高速再入返回器气动辨识偏差结果,可以为返回器设计分析提供依据。
Flight test is an important way to obtain the aerodynamic parameters of reentry capsule under real flight conditions.The results of aerodynamic parameters identification play an important role in the evaluation of CFD and wind tunnel experimental data,and in the improvement of aerodynamic design.For the lunar-earth high-speed reentry,the aerodynamic environments are complex,the aerodynamic predictions are difficult,and the results are very uncertain.Therefore,it is very necessary to give the deviations of aerodynamic identification results.Otherwise the aerodynamic data are useless for aircraft design,so the deviations analysis is very important step.In this paper,the aerodynamic parameters estimation methods for lunar-earth high-speed reentry capsule are studied firstly,and the main factors on influencing estimation deviation are analyzed.On this basis,the deviation ranges of main aerodynamic parameters are computed by Monte Carlo method.The results show that the measurement errors of atmospheric parameter,acceleration,attitude angle,altitude,velocity are main factors on influencing estimation deviatons.The deviation ranges of trim angle of attack are very small,and the deviation ranges of lift-drag ratio and aerodynamic coefficients are larger at very high altitude because of the measurement errors of acceleration and atmospheric density.The methods of uncertainty analysis using modified Cramer-Rao to calculate the deviation of pitch moment derivatives and control force are feasible.The results of deviation in this paper can pr ovide the basis for the design and analysis of reentry capsule.
作者
王贵东
李齐
王超
WANG Guidong;LI Qi;WANG Chao(China Academy of Aerospace Aerodynamics,Beijing 100074;China Academy of Space Technology,Beijing 100094)
出处
《空气动力学学报》
CSCD
北大核心
2018年第5期871-877,共7页
Acta Aerodynamica Sinica
基金
国家重点基础研究发展计划(2014CB744100)
关键词
飞船返回器
月地高速再入
偏差分析
飞行试验
气动参数辨识
spaceship reentry capsule
lunar-earth highspeed reentry
deviation analysis
flight test
aerodynamic parameter identification
作者简介
王贵东(1976-),男,博士,高级工程师,主要从事飞行力学、飞行器系统辨识研究.E-mail:wgdbj@sina.com。
