EFFECT OF AERODYNAMIC CROSS-COUPLING ON THE STABILITY OF A ROLLING AIRCRAFT | ||
| International Conference on Aerospace Sciences and Aviation Technology | ||
| Article 5, Volume 5, ASAT CONFERENCE 4 - 6 May 1993, CAIRO, May 1993, Pages 53-60 PDF (1.59 M) | ||
| Document Type: Original Article | ||
| DOI: 10.21608/asat.1993.25599 | ||
| Authors | ||
| A. A. EL AZIZ1; M. H. KATARY2; I. MANSOUR3 | ||
| 1Assistant lecturer, E.A.A, Belbis. | ||
| 2Assiitant professor, Dpt. of Aircraft Mechanics, M.T.C., Cairo. | ||
| 3Professor, Chief of Mechanical Engineering Branch, M.T.C.,Cairo. | ||
| Abstract | ||
| A method for investigation of stability of rolling aircrafts of inertially slender configuration is introduced. It includes the monotonic dependence of lateral-directional derivatives upon angle of attack, which is called "Aerodynamic cross-coupling", and expressed by the derivatives (Cl Cl , Cl6a04' Cn and 0c4 rot 1:20' Cnoacx). An application to a supersonic fighter model is made, in order to emphasize the effect of aerodynamic cross-coupling upon values and stability of pseudosteady roll rates. When results were compared with that obtained by neglecting aerodynamic cross-coupling, it was found that, the stable linear part of response is enlarged and the critical unstable area is completely disappeared. The results of the method were supported by a time domain simulation of the complete nonlinear equations of motion, beside a detailed analysis. Generally, it could be concluded that, the consideration of aerodynamic cross-coupling adds a source of nonlinearity to the response of a rolling aircraft, which may varry the stability margins provided, specially at large aileron deflections. | ||
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