Journal of Projectiles, Rockets, Missiles and Guidance >
A Calculation Method of Aircraft's Rolling Dynamic Derivatives Based on Quasi-steady Assumption
Received date: 2012-10-18
Online published: 2025-05-26
A quasi-steady method based on solving N-S equation was developed to calculate roll-damping moment coefficient derivative of aircraft. Finner missile was taken as a typical example, and the roll-damping moment coefficient derivative was calculated, also the effects of mach number, rolling speed and the difference of grids between the interfaces on the derivative were analyzed. The research shows that the numerical result is consistent with experiment data, and the roll-damping moment coefficient derivative obtained by both methods have the same trend; This method costs less time and obtains result quickly, which is propitious to engineering design.
MI Baigang , ZHAN Hao , ZHU Jun . A Calculation Method of Aircraft's Rolling Dynamic Derivatives Based on Quasi-steady Assumption[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2013 , 33(3) : 21 -24 . DOI: 10.15892/j.cnki.djzdxb.2013.03.029
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