Calculation and analysis method and system suitable for multi-layer thin-wall heat prevention and insulation structure and medium

Abstract

The invention provides a calculation and analysis method suitable for a multi-layer thin-wall heat prevention and insulation structure. The calculation and analysis method comprises the steps that S1, three-dimensional non-uniform thermal loads borne by a control surface at different moments in the actual flight process of an aircraft are calculated through fluid dynamics; s2, establishing a typical skeleton skin structure of the air rudder by adopting a composite material layering and laying technology; s3, interpolating the thermal load to the outermost layer node of the control surface by adopting an interpolation program based on the calculated three-dimensional non-uniform thermal load at the typical moment; s4, obtaining heat flow of the hot wall by adopting non-uniform heat flow subprogram interpolation based on the node thermal load of the layering unit obtained by interpolation calculation, and obtaining net heat flow borne by the structure at different moments by considering radiation; and S5, accurately calculating and extracting a three-dimensional temperature field at the typical characteristic moment of the whole flight trajectory of the air rudder by adopting three-dimensional numerical heat transfer analysis. According to the method, a solution is provided by coupling the composite shell unit with the non-uniform heat flux subprogram, the calculation precision can be met, and the design calculation efficiency is improved.

Description

technical field [0001] The invention relates to the technical field of aerospace design, in particular to a calculation and analysis method, system and medium suitable for multi-layer thin-walled heat-insulating structures. Background technique [0002] When the aircraft is flying at high speed in the atmosphere, the air rudder is used to precisely control the flight trajectory of the aircraft. In the actual flight process, the steering gear needs to continuously control the air rudder according to the designed flight trajectory. Due to the limitation of the installation space and power of the steering gear, In the design process, the mass and moment of inertia of the air rudder surface are usually required to be as small as possible, so as to improve the working stability and sensitivity of the steering gear. Therefore, the current design of air rudder surfaces is gradually carried out in the form of thin-walled skin and hollowed out skeleton. Through the optimization of th...

AI Technical Summary

Problems solved by technology

This existing technology cannot obtain the temperature field distribution during the actual flight, which provides a basis for the safety design of the air rudder, and the calculation accuracy is not enough

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