Skip to main content

Abort modes and the challenges of entry, descent and landing

  • Chapter
Martian Outpost

Part of the book series: Springer Praxis Books ((SPACEE))

  • 1349 Accesses

Abstract

For those tasked with designing robust and safe mission architectures, a manned mission to Mars presents problems far exceeding the challenges that have been faced before. For example, one of the overriding factors making a Mars mission so fundamentally different from lunar missions is the lack of opportunity to abort the mission, since, once the trans-Mars injection maneuver (TMI) has been performed, the crew is committed to a four to six month journey. Another equally formidable challenge is assuring the safety of the crew during the nerve-wracking entry, descent and landing (EDL), a phase most planners agree is the most dangerous part of the entire mission.

This is a preview of subscription content, log in via an institution to check access.

Access this chapter

Chapter
USD 29.95
Price excludes VAT (USA)
  • Available as PDF
  • Read on any device
  • Instant download
  • Own it forever
eBook
USD 34.99
Price excludes VAT (USA)
  • Available as PDF
  • Read on any device
  • Instant download
  • Own it forever
Softcover Book
USD 44.99
Price excludes VAT (USA)
  • Compact, lightweight edition
  • Dispatched in 3 to 5 business days
  • Free shipping worldwide - see info

Tax calculation will be finalised at checkout

Purchases are for personal use only

Institutional subscriptions

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

References

  1. Braun, R.D., and Manning, R.M. Mars Exploration, Entry, Descent and Landing Challenges. IEEEAC paper #0076. December 9, 2005.

    Google Scholar 

  2. Clarke, A.C. Fountains of Paradise. Aspect. September, 2001.

    Google Scholar 

  3. Daso, E.O.; Pritchett, V.E., and Wang, T.S. The Dynamics of Shock Dispersion and Interactions in Supersonic Freestreams with Counterflowing Jets. 45th AIAA Aerospace Sciences Meeting, AIAA 2007-1423, Reno, Nevada, January 2007.

    Google Scholar 

  4. Edwards, B.C. The Space Elevator. NIAC Phase II Final Report, March 1, 2003.

    Google Scholar 

  5. Gnoffo, P.A., and Anderson, B.P. Computational Analysis of Towed Ballute Interactions. AIAA 2002-2997, 8th AIAA/ASME Joint Thermophysics and Heat Transfer Conference, St. Louis, MO, June 24–26, 2002.

    Google Scholar 

  6. Hall, J.L., and Le, A.K. Aerocapture Trajectories for Spacecraft with Large, Towed Ballutes. 11th Annual AAS/AIAA Space Flight Mechanics Meeting, Santa Barbara, CA, AAS 01-235, February 11–15, 2001.

    Google Scholar 

  7. Jarvinen, P., and Adams, R. The Effects of Retrorockets on the Aerodynamic Characteristics of Conical Aeroshell Planetary Entry Vehicles. AIAA 70-219, AIAA 8th Aerospace Sciences Meeting, New York, New York, January 1970.

    Google Scholar 

  8. Korzun, A.M. Supersonic Retropropulsion Technology for Application to High Mass mars Entry, Descent and Landing. Georgia Institute of Technology. April 2008.

    Google Scholar 

  9. Masciarelli, J.; Miller, K. Ultralightweight Ballute Technology Advances. Proceedings of the 2nd International Planetary Probe Workshop, NASA Ames Research Center, Moffett Field, CA, August, 2004.

    Google Scholar 

  10. Masciarelli, J.; Miller, K.; Rohrschneider, R.; Morales, A.; Stein, J.; Ware, J.; Lawless, D.; Westhelle, C; Gnoffo, P.; Buck, G.; McDaniel, J. Fly Higher, Fly Lighter, Fly Cooler: Progress in Ultralightweight Ballute technology Development. 53rd Joint Army-Navy-NASA-Air Force (JANNAF) Propulsion Meeting, Monterey, CA, December, 2005.

    Google Scholar 

  11. Mease, K.D.; Leavitt, J.A.; Benito, J,; Talole, A.; Sohl, G.; Ivanov, M.; Ling, L. Advanced Hypersonic Entry Guidance for Mars Pinpoint Landing. NSTC-07-0023. NASA Conference. 2007.

    Google Scholar 

  12. Medlock, K.L., and Longuski, J.M. An Approach to Sizing a Dual-Use Ballute System for Aerocapture, Descent and Landing. 4th International Planetary Probe Workshop, Pasadena, CA, June 27–30, 2006.

    Google Scholar 

  13. Miller, K.L.; Gulick, D.; Lewis, J.; Trochman, B.; Stein, J.; Lyons, D.; Wilmoth, D. Trailing Ballute Aerocapture Concept and Feasibility Assessment. AIAA 2003-4655, 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Huntsville, AL, July, 2003.

    Google Scholar 

  14. Witkowski, A., and Brown, G. Mars Deployable Decelerators Capability Roadmap Summary. 2006 IEEE Aerospace Conference, Paper 1585, Big Sky, Montana, March, 2006.

    Google Scholar 

Download references

Author information

Authors and Affiliations

Authors

Rights and permissions

Reprints and permissions

Copyright information

© 2009 Praxis Publishing Ltd.

About this chapter

Cite this chapter

Seedhouse, E. (2009). Abort modes and the challenges of entry, descent and landing. In: Martian Outpost. Springer Praxis Books. Praxis. https://doi.org/10.1007/978-0-387-98191-8_4

Download citation

Publish with us

Policies and ethics