html5-img
1 / 1

AEROFAST : THERMAL/ABLATION ANALYSIS OF THE FRONT HEAT SHIELD FOR A MARTIAN AEROCAPTURE MISSION

Cork based TPS. Silicon based glue. CFRP. Aluminum honeycomb. CFRP. S/D=0.482. S/D=0.561. AEROFAST : THERMAL/ABLATION ANALYSIS OF THE FRONT HEAT SHIELD FOR A MARTIAN AEROCAPTURE MISSION A.J. van Eekelen, G. Pinaud, J.-M. Bouilly. Problem description.

jacqui
Download Presentation

AEROFAST : THERMAL/ABLATION ANALYSIS OF THE FRONT HEAT SHIELD FOR A MARTIAN AEROCAPTURE MISSION

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. Cork based TPS Silicon based glue CFRP Aluminum honeycomb CFRP S/D=0.482 S/D=0.561 AEROFAST: THERMAL/ABLATION ANALYSIS OF THE FRONT HEAT SHIELD FOR A MARTIAN AEROCAPTURE MISSION A.J. van Eekelen, G. Pinaud, J.-M. Bouilly Problem description In the frame of the AEROFAST (AEROcapture for Future space tranSporTation) R&D project (FP7), we aim to increase the TRL level of a Martian Aerocapture mission. The Aerocapture trajectory and maneuver results in significant aerodynamic heating, necessitating a Thermal Protection System (TPS). The selected shield has an Apollo like shape with a 3.6 m diameter. The thermal and ablation behavior of a low density (phenolic impregnated) cork TPS is analyzed. The heat shield is subjected to a 3D convection and radiation load obtained for a CO2 Martian atmosphere. Modelling approach Loads and boundary conditions Thermal response calculation Finite element model 3D transient temperature dependent (convection) heat flux, evaluated using an Euler-boundary layer computation and empirical correlation adapted to CO2 gas. Heat flux at t = 160. s [kw/m2] Energy balance: Mass conservation: Arrhenius-type charring law: Boundary balance: Explicit ablation law: The elements have multiple degrees of freedom per node (T,P,,1,…,n), and the balance equations are implemented on a moving mesh (transport terms). The 3D half model consists of 58.894 elements with a total of 144.031 degrees of freedom. Through the thickness and 3D finite element distribution Results 1D calculation 3D calculation Parametric analysis to determine the TPS thickness (17 mm),for a maximum allowable structure temperature of 180 °C. Edge cross-section for  = 180° Conclusions A 3D finite element model, including charring and ablation, has been implemented in SAMCEF. A preliminary TPS design of a phenolic impregnated cork material has been obtained, while complementary work on advanced (cork based) TPS material modeling is underway within the AEROFAST project.

More Related