On the basis of structured mesh finite volume method and dynamic mesh technique, a CFD method for calculating the dynamic performance of aircraft was developed by using flow control equation and rigid body dynamic equation of enforced oscillation form solved by dual-time stepping LU-SGS approach. Through exploring the origins of unstable identification result, large dispersion of the identification result of different methods, over reliance on manual processing and other problems existed in some occasions of practical application using integration method, T-F method, least square method and other typical dynamic derivative identification method, the improvement measures were put forward. The effectiveness of the method was proved by the confirmation of the Finner missile and HBS trajectory contour and other typical examples.
LI Li
. Research and Improvement of Identification Method for Dynamic Derivatives of Aircraft Based on Enforced Oscillation[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2017
, 37(6)
: 1
-6
.
DOI: 10.15892/j.cnki.djzdxb.2017.06.001
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