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Flight Performance Feasibility Studies for the Max Launch Abort System

Author
Gilbert, Michael G.
Published
August 19, 2013.
Physical Description
1 electronic document
Additional Creators
Beaty, James R. and Tarabini, Paul V.
Online Version

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Summary
In 2007, the NASA Engineering and Safety Center (NESC) initiated the Max Launch Abort System Project to explore crew escape system concepts designed to be fully encapsulated within an aerodynamic fairing and smoothly integrated onto a launch vehicle. One objective of this design was to develop a more compact launch escape vehicle that eliminated the need for an escape tower, as was used in the Mercury and Apollo escape systems and what is planned for the Orion Multi-Purpose Crew Vehicle (MPCV). The benefits for the launch vehicle of eliminating a tower from the escape vehicle design include lower structural weights, reduced bending moments during atmospheric flight, and a decrease in induced aero-acoustic loads. This paper discusses the development of encapsulated, towerless launch escape vehicle concepts, especially as it pertains to the flight performance and systems analysis trade studies conducted to establish mission feasibility and assess system-level performance. Two different towerless escape vehicle designs are discussed in depth: one with allpropulsive control using liquid attitude control thrusters, and a second employing deployable aft swept grid fins to provide passive stability during coast. Simulation results are presented for a range of nominal and off-nominal escape conditions.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 20140002406.
NF1676L-16007.
AIAA Atmospheric Flight Mechanics Conference; 19-22 Aug. 2013; Boston, MA; United States.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15439412