Finite Element Analysis Of Hypersonic Aircraft And Heat Protection Panel

When hypersonic aircraft is flight in supersonic or hypersonic, the effect of viscous of the air leads to temperature rise around the surface of the aircraft and causes intense aerodynamic heating, which have serious effect on the normal flight and the security of hypersonic aircraft. Up to now, there are lots of research about the coupling of the aerodynamic force, aerodynamic heat and structure deformation of the simple geometry,for example, beams,plates,wings,etc. However there is less study on the aerodynamic force and aerodynamic thermal. Theanalysis of the hypersonic aerothermodynamics has become one of the key technologies in the area of the hypersonic aircraft design. And the matter of the thermal dissipation is also the key problem in the design process, for the thermal environment of the hypersonic aircraft is completely complex.Therefore it is vital significant for hypersonic aircraft design and material selection to analyze the characteristics of the hypersonic aircraft and its thermal performance and to research the simulation analysis of the thermal protective structure.This paper summarizes the development situation of hypersonic technology, the research status of aerodynamic force of pneumatic heat at domestic and overseas and the necessity of carrying out the work by fully combined with reference material and literatures, it. In the paper, the flow characteristics of hypersonic flow and the thermal environment of aircraft are systematic analyzed as well as the basic knowledge of geometric modeling is simply summarized. The paper discussed train of thought and character of the modeling and briefly descripted the grid generation technique through the platform of Pro/E 3D modeling software and ANSYS finite element analysis Three-dimensional modeling of a typical X-51A aircraft is carried out by using Pro/E software, and the parametric modeling is realized. By modifying the size of the model to drive the entire model, the process of updating only takes few seconds to complete. Setting up the type of materials, boundary conditions and mesh division of the aircraft use the Workbench. Calculating the lift force, drag coefficient and other aerodynamic characteristic parameters under the Maher number 6 and the angle of attack 0～8 degree by FLUNT aims to get the pressure distribution and velocity vector of the aircraft surface. In addition, analyzing the character of the dynamic and thermal of the whole structure of the aircraft is to get the equivalent stress, strain diagram of the aircraft, the natural vibration frequency and vibration mode of the rigid body motion, the temperature distribution and the heat flux density distribution of the aircraft under the conditions of the rigid motion. Finally, the analysis results are consistent with the test results of the reentry aircraft. To some certain extent, the research results are useful for the study of the coupling of the aircraft and the complex physical field.At the same time, the paper has also built the three-dimensional model of the typical reinforced wall heat structure of the aircraft and carried through a series of dynamics analysis, thermal performance analysis and so on. The modes of the panels are analyzed and compared under the uniform and non-uniform temperature field, in order to get the curve of the vibration frequency, the equivalent stress,strain distribution and safety coefficient distribution of panels.It is extremely significant for the study on thermal noise fatigue and thermal flutter analysis of reusable aircraft in the future to conduct t dynamics analysis and thermal analysis of thermal protective structure.