Aerospace Instrument-Making Annotation << Back THEORETICAL AND EXPERIMENTAL INVESTIGATION OF THE DRONE INSTRUMENT BAY THERMAL STATE OF UNPRESSURIZED COMPATMENT WITH HONEYCOMB STRUCTURES OF AIRFRAME V.N. Nikolaev, S.A. Gusev The method for determination of an drone compartment thermal condition, based on a mathematical model of a unpressurized compartment thermal condition was developed. A symbolic model of the system of a unpressurized heat insulated compartment with the thermal conditions supporting system can be represented by a system of one-dimensional equations of an honeycomb structures of airframe and ordinary difference equations of convective heat transfer of the inner surface of the honeycomb structures of the lining and inner surface of the lining in compartments, on-board equipment, air, transfer of enthalpy from the thermal conditions supporting system. Development of solution techniques for solving heat exchange direct and inverse problems and for determining confi dence intervals of parametric identification estimations was carried out. Confidential intervals of estimations of factors nonlinear mathematical model of a thermal condition of a compartment of a kind can be defi ned with the help dispersion matrix errors of estimations required factors of model. Parametrical identification was carried out by the measured in the compartment surface temperatures of one of the blocks and the inner surface of the heat insulation sheathing around the block. In this case, the measurement results for a cold climate in a typical flight mode of a drone were used. For the purpose of experimental verifi cation of the proposed model in different flight modes and air overboard, as well as on elements of the instrument compartment, temperatures of the compartment elements calculated by the model were compared with measured values. The verification showed that the constructed mathematical model of the instrument compartment thermal state is adequate to the real thermal state of unpressurized venting heat-insulated compartment of the drone. Keywords: honeycomb structures, mathematical model, direct problem, inverse problem, stochastic differential equations, thermal state, airborne equipment, thermal conditions supporting system, instruments bay. Contacts: E-mail: nikvla50@mail.ru, E-mail: sag@osmf.sscc.ru Pp. 10-19.