Imperial College London
Portrait Picture

DrPaulBruce

Faculty of Engineering, Department of Aeronautics

Reader in High-Speed Aerodynamics
 
 
 
//

Contact

 

+44 (0)20 7594 5048p.bruce

 
 
//

Location

 

333City and Guilds BuildingSouth Kensington Campus

//

Summary

 

Publications

Citation

BibTex format

@article{Braun:2017:10.1016/j.actaastro.2017.03.003,
author = {Braun, M and Bruce, P and Levis, E},
doi = {10.1016/j.actaastro.2017.03.003},
journal = {Acta Astronautica},
pages = {22--33},
title = {Strategies to utilize advanced heat shield technology for high-payload mars atmospheric entry missions},
url = {http://dx.doi.org/10.1016/j.actaastro.2017.03.003},
volume = {136},
year = {2017}
}
Download

RIS format (EndNote, RefMan)

TY  - JOUR
AB  - Present Entry, Descent and Landing (EDL) technology for interplanetary missions does not have the capabilities to meet the demanding requirements that come with future missions. A popular target for such missions is Mars and today efforts are made to send manned as well as sophisticated robotic probes to the Martian surface. Because present EDL technology has reached its limits, fundamentally new approaches are needed to significantly extend capabilities. Systematic evaluation of novel EDL technologies and optimization of EDL strategies are crucial needs for conceptual design. A computational framework will be presented tailored to enable systematic EDL analysis with special regards to novel EDL technology and event strategies. The benefits of flexible heat shield concepts that come with liberties in the choice of the ballistic coefficient will be shown in comparison with solid shield alternatives for payload classes of 2, 25 and 40 tonnes to show potential for manned and robotic missions. Furthermore, benefits of the new methodology for novel EDL event strategies are presented and discussed. The introduced methodology will help designers exploit new directions for conceptual design regarding EDL systems in terms of entry mass optimization and mission capabilities.
AU  - Braun,M
AU  - Bruce,P
AU  - Levis,E
DO  - 10.1016/j.actaastro.2017.03.003
EP  - 33
PY  - 2017///
SN  - 0094-5765
SP  - 22
TI  - Strategies to utilize advanced heat shield technology for high-payload mars atmospheric entry missions
T2  - Acta Astronautica
UR  - http://dx.doi.org/10.1016/j.actaastro.2017.03.003
UR  - http://gateway.webofknowledge.com/gateway/Gateway.cgi?GWVersion=2&SrcApp=PARTNER_APP&SrcAuth=LinksAMR&KeyUT=WOS:000401676700003&DestLinkType=FullRecord&DestApp=ALL_WOS&UsrCustomerID=1ba7043ffcc86c417c072aa74d649202
UR  - http://hdl.handle.net/10044/1/50689
VL  - 136
ER  -
Download