I.V. Morozova - Junior Research Scientist, Central Aerohydrodynamical Institute, named after prof. N.E. Zhukovsky (TsAGI) V.I. Sadchikov - Ph.D. (Eng.), Associate Professor, Leading Research Scientist, Central Aerohydrodynamical Institute, named after prof. N.E. Zhukovsky (TsAGI). E-mail: flight15@tsagi.ru

Research of dynamics and safety of separation of the various aviation objects allocated on exterior points under the wing or inside of airplane, is one of the important problems at designing and making of the aviation complex. Usually for its solution in wind tunnels for determination of interference aerodynamic coefficients of the object because of effect of the aerodynamic field of an airplane for various parameters are conducted: Mach numbers, angles of attack and slip of an airplane, linear and an angular data of model of object concerning airplane model. Thus for objects which are operated on path launching, models are executed with not turned down operating controls and problems of a possible modification of their effectiveness in the field of the airplane are not considered. In this article, along with the conventional approach to determination of interference performances in wind tunnel, the estimate of effect of the aerodynamic field of an airplane on aerodynamic characteristics (AСh) object at deflected operating controls is given, that allows evaluating effectiveness of operating controls of object in the conditions of interference effect of an airplane. With usage of experimental data mathematical models and the software are developed, allowing determining aerodynamic characteristics (including effectiveness of operating controls) object in an insulated status, and also in the presence of an airplane. The estimate of interference disturbances effect on effectiveness of control surfaces is received for longitudinal motion. Mathematical models and the software of controlled flight are developed for researches of dynamics and safety of the separating object from an airplane. Parametric researches of the separating object from a compartments of the airplane that execute the established level flight at various combinations of a flying height, a Mach number and initial angular rates of object in the control channels stipulated by operation of the launcher are conducted. From the analysis of calculations follows that for the considered conditions of separation the stable disturbed motion of the object with damping of transient phenomena is implemented. Thus object separation occurs without a collision to airplane configuration items, and corresponds to monotonous removal downwards and back from an airplane. More reliable estimate of effect can be received with usage of mathematical model ACh, considering side interference disturbances, and is required to execute additional experimental (or calculated) researches.