Development of Supersonic Retro-Propulsion for Future Mars Entry, Descent, and Landing Systems-Reference-Cited by-同舟云学术

Development of Supersonic Retro-Propulsion for Future Mars Entry, Descent, and Landing Systems

Published:2010-06-28 Issue: Volume: Page:
ISSN:
Container-title:10th AIAA/ASME Joint Thermophysics and Heat Transfer Conference
language:
Short-container-title:

Author:

Edquist Karl¹,Korzun Ashley²,Studak Joseph³,Dyakonov Artem¹,Shidner Jeremy⁴,Kipp Devin⁵,Tigges Michael³,Prakash Ravi⁵,Trumble Kerry⁶,Dupzyk Ian⁷

Affiliation:

1. NASA Langley Research Center

2. Georgia Institute of Technology

3. NASA Johnson Space Center

4. Analytical Mechanics Associates, Inc.

5. NASA Jet Propulsion Laboratory

6. NASA Ames Research Center

7. ELORET Corporation

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2010-5046

Reference44 articles.

1. Starting with the two Viking landers in 1976 and continuing through the successful Mars Phoenix mission in

2. less than 0.6 metric tons (t). The upcoming Mars Science Laboratory (MSL) mission (2011 launch) will have an

3. 092 0.173 0.167 0.9

4. development effort in the 1960s and 1970s developed SRP to nearly the level of maturity the concept has today.

5. EDL-SA and ETDP teams have resumed from where original investigations left off more than 30 years ago. A substantial number of wind tunnel tests were completed in the 1960s and early 1970s using small-scale models

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