The estimated available center of gravity range aircraft with joined wing configuration
Journal Title: Інформаційні системи, механіка та керування - Year 2015, Vol 0, Issue 12
Abstract
Aircraft is a persistent overload if it independently, without pilot intervention to retain original overload flight mode and return to it after the termination of indignation. Using panel-vortex method of symmetrical features (PANSIM) a complex of parametric studies of the impact position of the center of gravity in the center of gravity range aircraft with joined wing configuration changes depending on the length of the controls on the front and rear wings. Depending on the position of the center of gravity in cruising flight configuration back centering determined based on the stock longitudinal static stability. For each spatial layout of the aircraft with joined wing configuration with rejected down the controls on the front wing and rejected up the controls on the rear wing and depending on their length changes in scope, is set to front centering value. The settlement case to determine the front centering value landing is rejected with the controls, as in this case, the coefficients of lift and moment are most important, but downwash - the least. When performing parametric studies to determine the front centering value, there were two cases of settlement: 1) controls placed only on the front wing span; 2) controls placed on the front wing and on the rear wing. Moreover, the scope of the controls on the rear wing did not exceed the scope of controls on the front wing.
Authors and Affiliations
Дмитро Миколайович Зінченко, Олег Олександрович Хомінич
Keywords
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