Abstract
In this case of study the analysis of methods of designing unmanned aircraft launch container with regard to the requirements of sustainability were conducted. In this study theoretical and empirical methods were used, theoretical calculations are confirmed by field experiment.Based on theoretical approaches were formed and justified a general outline of aircraft. During the work was used a complex method of decision-making based on expert analysis. For this was defined a list of criteria that most accurately describes the requirements for object of development, calculated numerical values of the coefficients weight and numerical values of each criterion for a particular layout . In the analysis was founded that the most rational aerodynamic layout for a "tandem" or "duck" with a total normalized value 0.8145. Determination of design parameters were based on a region of acceptable rational values of design options 6 specific wing load and energy available. Field of values formed with consideration of general requirements and restrictions placed for the aircraft. Considering layout restrictions layout of unmanned aircraft was designed and main geometrical characteristics was calculated.Consideration of the impact of geometric parameters on the characteristics of stability was conducted on based of developed mathematical model. Verification of the mathematical model was conducted in a wind tunnel AT-1 ("Antonov"). To determine characteristics of lateral stability were tested model schemes " tandem " with the various positions of the wings: longitudinal making wings was varied (390, 490 and 590 mm), angle V – similarity rear wing (0̊, –5̊, –9̊), swing the front (1050, 1450 mm) and rear wings (1170, 1570 mm).Matches of theoretical calculations with experiment were received as a result of researches indicating the adequacy of the proposed approach. In further studies it will be planned to examine roll handling in detail.
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