Review on determination of Carbon Phenolic composite structure thickness under aero-thermal loading.

2nd International Conference on Advancements in Aeromechanical Materials for Manufacturing

航空航天工程;材料科学;机械制造

Gupta, M Satyanarayana^1 ; Rao, Sharad H.^1

Aeronautical Department, MLR Institute of Technology, Dundigal, Hyderabad

500043, India^1

关键词: Aerodynamic loading;    Aerospace structure;    Hypersonic speed;    Residual thickness;    Simulation software;    Surface temperatures;    Thermal loadings;    Thermal Protection System;   

Others  :  https://iopscience.iop.org/article/10.1088/1757-899X/455/1/012042/pdf
DOI  :  10.1088/1757-899X/455/1/012042

来源: IOP

【 摘 要 】

Composite structures are used in many part of aerospace structures for their unique characteristics and properties. This composite structures are design and fabricated to protect payloads from severe aerodynamic loading and heating during their performance. Carbon-epoxy is used for internal layer because of its structural properties whereas Carbon-phenolic (C-Ph) composites are well fabricated to meet the requirements of thermal protection system. In this review paper, behavior of thermal protection system under aero-thermal load during re-entry at hypersonic speed through earth atmosphere has been studied. Vehicles shapes design, velocity, trajectory and heating rate experienced are the factors that are playing important role in performance of Thermal protection systems has been studied. Modeling of blunt body using CAD and imported to simulation software USIM to visualize different properties of the atmosphere and blunt body model. The pyrolysis and erosion of the ablator was simulated by implementing finite element models. Through the studied of velocities, shapes and heat flux conditions, the rate of ablation, surface temperature, residual thickness of the material has been estimated.