Spacecraft High Temperature Thermal Protection Systems Heat Transfer Calculations And Numerical Analysis

Aerodynamic heating generated in the shock layer surrounding can lead to the nose cap temperature as high as 1793℃, and the leading edges temperature can reach 1455℃, when space aircraft re-entry as speed as 8Ma in 27km high space. So it is necessary to establish insulation equipment, that can make inner temperature of aircraft decrease as low as 177℃, so as to make sure inner equipment and flight personnel sale. Several decade later, metallic thermal protection system's develop have made great rapid progress, and will be considered lor insulating major portions of a new generation of reusable launch vehicles. Therefore, the insulation performance of space aircraft is investigated by. using theory analysis and numerical simulation.First, it is analyzed by theory that the progress of multi-layer insulation for space aircraft, gas natural convection contributions are minimal during the process, thus, il can be ignored. The combined radiation and conduction heat transfer through fibrous and multi-layer insulations is investigated using a finite volume approach and a two-flux formulation, the vary of effective thermal conductivity vs the vary of temperature will be gained. In the next place, heat transfer through honeycomb sandwich structure, high porosity structure, and contact heat transfer among solids is be molded using finite element method. Finally, heat transfer through the nose cap and leading edge of space aircraft is molded using finite clement method. This paper can provide some useful information for study of insulation of space aircraft.The following conclusions are reached based on the numerical simulation and theory analysis. The effective thermal conductivity of multi-lay insulation significantlyincreases with temperature increasing. The study ior honeycomb sandwich structure has shown that the most important structure parameter is as follows: honeycomb depth, honeycomb ribbon thickness, lace sheet thickness, in circle diameter of honeycomb, and temperature of upper and bottom sheet. For high porosity structure, it is high effective adiabatic structure.