CAJ | 학술논문

为了研究表征飞行器动态稳定特性的动导数，结合计算流体力学方法，基于滑移网格技术，采用小幅度强迫振动法和差分法两种非定常方法，推导了俯仰组合动导数以及滚转阻尼导数的计算表达式，并结合多参考系模型采用准定常方法计算滚转阻尼导数。建立了基于计算流体力学技术的飞行器动导数计算方法。对国际动导数标模 Finner 导弹进行了计算验证。两种非定常方法对俯仰组合动导数的计算误差分别为0．65％、6．13％，对滚转阻尼导数的计算误差分别为2．5％、0．06％。求解滚转阻尼的准定常方法对于滚转阻尼导数的计算误差为2．67％。三种方法的计算结果与风洞试验结果吻合的很好。非定常方法计算精度高，准定常方法可以快捷迅速得到结果。本文的数值方法不仅适用于超声速，同样可以用于亚、跨声速时的动导数计算。
위료연구표정비행기동태은정특성적동도수，결합계산류체역학방법，기우활이망격기술，채용소폭도강박진동법화차분법량충비정상방법，추도료부앙조합동도수이급곤전조니도수적계산표체식，병결합다삼고계모형채용준정상방법계산곤전조니도수。건립료기우계산류체역학기술적비행기동도수계산방법。대국제동도수표모 Finner 도탄진행료계산험증。량충비정상방법대부앙조합동도수적계산오차분별위0．65％、6．13％，대곤전조니도수적계산오차분별위2．5％、0．06％。구해곤전조니적준정상방법대우곤전조니도수적계산오차위2．67％。삼충방법적계산결과여풍동시험결과문합적흔호。비정상방법계산정도고，준정상방법가이쾌첩신속득도결과。본문적수치방법불부괄용우초성속，동양가이용우아、과성속시적동도수계산。
To study the dynamic stability derivatives of aircraft with CFD technology,an unsteady meth-od for calculating pitching dynamic stability derivative and rolling damp dynamic derivative is developed by u-sing small amplitude oscillation model and differential model,and a quasi-steady method is also built to cal-culate rolling damp dynamic derivative;the unsteady method is based on sliding mesh technique while the quasi-steady method on both sliding mesh technique and moving reference frame model;compared to the dy-namic mesh used before,the sliding mesh technique can improve the computational precision as it avoids the effect of mesh deformation.The finner missile is taken as example to calculate the dynamic derivatives.The errors of two unsteady methods to calculate longitudinal combined derivatives are 0.65% and 6.13% respec-tively,while errors to lateral combined derivatives are 2.5% and 0.06%,and the error of quasi-steady meth-od to obtain lateral combined derivative is 2.67%.The research shows the calculation result is consistent with the experimental data,although the quasi-steady method is less accurate than the unsteady one,never-theless it can get result more quickly.Moreover,both the methods can be used for supersonic,subsonic and transonic dynamic derivative calculation.