Analysis Of The Structural Design And Characteristics Of The Aircraft Cold Cover

Heat distortion and thermal stress analysis technology in the field of military and civilian scientific research have a very important project needs and the apply of broad prospects. According to this thesis research projects requirements of the aircraft colded-cover and hot thermal deformation, analy the t Theory and simulation studies. Achieving the purpose of stealth aircraft ,the aircraft minimize the temperature, thermal radiation is minimized too .According to the colded-cover's design requirements and working principle, complete structural design, including the selection of the materials, structures within the shell and its annex, refrigeration systems and the design of the link structure. It also details calculation method of the vacuum solar radiational heat on aircraft, according to a vacuum in the heat balance equation and various other radiation method of calculating the volume of aircraft colded-cover enclosures are calculated. On this basis, the paper key also carry on the finite element theoretical analysis to colded-cover in the undercooling heat conduction question, and establish a the thermal conductivity three-dimensional model of colded-cover shell by using of ANSYS FEM software,then the the temperature field is produced, last field of stress has been calculated which produces by the temperature field changes. From the field of temperature to thermal deformation and field of stress, through empirical datum and computed result contrast, proves that the cold-cover design is reasonable. Colded-cover's design also provide an effective reference materials.