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Max Launch Abort System

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The Max Launch Abort System (MLAS) was a proposed alternative to the Maxime Faget-invented "tractor" launch escape system (LES) that was planned for use by NASA for its Orion spacecraft in the event an Ares I malfunction during launch required an immediate abort.[1]

Fabrication and launch of the MLAS test vehicle
Components of the MLAS test vehicle
MLAS test vehicle flight profile

Designed by NASA engineers and reported on the website NASASpaceFlight.com on December 6, 2007, the proposed MLAS used four existing Huntsville-built Thiokol solid-rocket motors (built in 1988) placed at 90° intervals within the Orion's bullet-shaped fairing.[2] The fairing was originally designed to protect the Orion spacecraft from aerodynamic stresses during launch and to provide an interface between the spacecraft's crew module with the LES.

The MLAS was designed with the aim of reducing the height of the Orion/Ares I stack while also reducing weight and center-of-gravity issues of a traditional LES.[3] The bullet-shaped MLAS was also expected to provide better aerodynamic qualities during the first two minutes of flight, reducing stresses when the vehicle encounters the "max Q" region of hypersonic flight.[4] The MLAS was also expected to simplify production, as existing hardware would be employed.[5]

There are several drawbacks to MLAS. First, the bullet-shaped protective cover would have to be modified and reinforced to allow for the use of the solid-rocket motors, something not needed with the LES, which bolts on top of the LIDS docking ring assembly.[6] Second, the necessity to fire multiple motors (LES uses one motor and multiple nozzles) simultaneously for an abort decreases the theoretical reliability of the launch abort system by introducing more failure modes.[7]

Like the existing LES, the MLAS would provide protection to the Orion spacecraft crew during the first 2+1⁄2 minutes of flight, with the MLAS being jettisoned, along with the service module's fairing panels, after the solid-rocket first stage was jettisoned.[8] If implemented, the Orion/Ares I stack would have resembled the towerless Gemini-Titan stack used between 1965 and 1966, in which ejection seats were used as the primary form of escape for the astronauts who flew on the ten Gemini missions.[9]

The MLAS concept was dropped with the transformation of the Crew Exploration Vehicle into the Orion Multi-Purpose Crew Vehicle, and the switch of the launch vehicle from Ares I (with its perennial underperformance) to the Delta IV Heavy or Space Launch System.[10]

July 2009 test launch

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A "pad abort" flight test of the Max Launch Abort System was performed at NASA's Wallops Flight Facility on July 8, 2009, at 10:26 UTC.[11][12] A primary test goal was the successful separation of a mock crew capsule from the abort system.[11] The test vehicle weighed over 45,000 pounds (20,000 kg) and was over 33 feet (10 m) tall.[13]

The test vehicle had several differences from the actual proposed system. The main difference was that the four propulsion rockets were not located in the forward fairing, but in a boost skirt located at the bottom of the test vehicle.[14] The rockets in the fairing were represented by geometric dummies.[11] The propulsion thrust was not balanced between the rockets by a manifold system, contrary to what was foreseen with the actual system.[15]

References

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  This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.

  1. ^ "NASA's Max Launch Abort System (MLAS) Overview". NASA. Retrieved August 15, 2024.
  2. ^ "NASA Considering Alternate Launch Abort System for Orion". NASASpaceFlight.com. December 6, 2007. Retrieved August 15, 2024.
  3. ^ "NASA's Constellation Program: Max Launch Abort System". NASA. Retrieved August 15, 2024.
  4. ^ "Max Q: The Ultimate Challenge of Space Flight". NASA. October 29, 2019. Retrieved August 15, 2024.
  5. ^ "NASA's Wallops Flight Facility and the MLAS". NASA/Wallops Flight Facility. July 1, 2009. Retrieved August 15, 2024.
  6. ^ Isakowitz, Steven J. (2010). International Reference Guide to Space Launch Systems. AIAA. pp. 357–359. ISBN 978-1-60086-784-2.
  7. ^ Wood, Eric M. (2010). "Reliability Considerations of Multiple Solid Rocket Motors in Launch Abort Systems". Journal of Spacecraft and Rockets. 47 (2): 317–321. doi:10.2514/1.47414 (inactive 1 November 2024).{{cite journal}}: CS1 maint: DOI inactive as of November 2024 (link)
  8. ^ Connors, Mary M. (2008). Launch Escape Systems and Emergency Recovery: Historical Overview and Future Prospects. NASA. pp. 112–115. ISBN 978-0-16-081519-8. {{cite book}}: Check |isbn= value: checksum (help)
  9. ^ Shayler, David (2001). Gemini: Steps to the Moon. Springer-Praxis. pp. 192–194. ISBN 978-1-85233-405-5.
  10. ^ "NASA's Orion Multi-Purpose Crew Vehicle (MPCV)". NASA. Retrieved August 15, 2024.
  11. ^ a b c Hautaluoma, Grey; Edwards, Ashley; Henry, Keith; Powell, Rebecca (July 8, 2009). "NASA Tests Alternate Launch Abort System For Astronaut Escape". NASA. NASA Release 09-156.
  12. ^ "Max Launch Abort System (MLAS)". NASA. July 8, 2009.
  13. ^ "MLAS". NASA/Wallops Flight Facility. Retrieved July 11, 2009.
  14. ^ Hautaluoma, Grey; Edwards, Ashley; Henry, Keith; Powell, Rebecca (July 8, 2009). "NASA Tests Alternate Launch Abort System For Astronaut Escape". NASA. NASA Release 09-156.
  15. ^ "MLAS". NASA/Wallops Flight Facility. Retrieved July 11, 2009.

Further reading

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  Media related to Max Launch Abort System at Wikimedia Commons

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