Imperial College London
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ProfessorMatthewSanter

Faculty of Engineering, Department of Aeronautics

Professor of Aerospace Structures
 
 
 
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Contact

 

+44 (0)20 7594 5117m.santer

 
 
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Location

 

335City and Guilds BuildingSouth Kensington Campus

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Summary

 

Publications

Citation

BibTex format

@article{Peacocke:2019:10.2514/1.A34310,
author = {Peacocke, L and Bruce, P and Santer, M},
doi = {10.2514/1.A34310},
journal = {Journal of Spacecraft and Rockets},
pages = {1221--1230},
title = {Coupled aerostructural modeling of deployable aerodecelerators for Mars entry},
url = {http://dx.doi.org/10.2514/1.A34310},
volume = {56},
year = {2019}
}
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RIS format (EndNote, RefMan)

TY  - JOUR
AB  - An analysis of deployable aerodecelerators has been performed using a developed six-degree-of-freedom entry trajectory simulator coupled with a structural model of the deployable structural members, or ribs, to investigate the effect of aerodecelerator flexibility on the trajectory and configuration design. The modified Newtonian method is used in the entry trajectory simulator, and the deployable ribs are modeled as Euler–Bernoulli beams. It is shown that, although flexibility is beneficial in reducing the mass and volume of the deployed ribs, an increase in peak heat flux will result. However, if mass savings from flexible ribs can be reallocated toward increasing the diameter of the entry vehicle, significant benefits can be gained.
AU  - Peacocke,L
AU  - Bruce,P
AU  - Santer,M
DO  - 10.2514/1.A34310
EP  - 1230
PY  - 2019///
SN  - 0022-4650
SP  - 1221
TI  - Coupled aerostructural modeling of deployable aerodecelerators for Mars entry
T2  - Journal of Spacecraft and Rockets
UR  - http://dx.doi.org/10.2514/1.A34310
UR  - https://arc.aiaa.org/doi/10.2514/1.A34310
UR  - http://hdl.handle.net/10044/1/65991
VL  - 56
ER  -
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