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Guidance, Navigation and Control (Gn and C) Design Overview and Flight Test Results from NASA's Max Launch Abort System

Guidance, Navigation and Control (Gn and C) Design Overview and Flight Test Results from NASA's Max Launch Abort System

Guidance, Navigation and Control (Gn and C) Design Overview and Flight Test Results from NASA's Max Launch Abort System.cNasa Technical Reports Server (Ntrs)
Guidance, Navigation and Control (Gn and C) Design Overview and Flight Test Results from NASA's Max Launch Abort System
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Author: Nasa Technical Reports Server (Ntrs)
Page Count: 38 pages
Published Date: 16 Jul 2013
Publisher: Bibliogov
Publication Country: United States
Language: English
ISBN: 9781289172398
File Name: Guidance,.Navigation.and.Control.(Gn.and.C).Design.Overview.and.Flight.Test.Results.from.NASA's.Max.Launch.Abort.System.pdf
Download Link: Guidance, Navigation and Control (Gn and C) Design Overview and Flight Test Results from NASA's Max Launch Abort System
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The National Aeronautics and Space Administration Engineering and Safety Center designed, developed and flew the alternative Max Launch Abort System (MLAS) as risk mitigation for the baseline Orion spacecraft launch abort system already in development. The NESC was tasked with both formulating a conceptual objective system design of this alternative MLAS as well as demonstrating this concept with a simulated pad abort flight test. Less than 2 years after Project start the MLAS simulated pad abort flight test was successfully conducted from Wallops Island on July 8, 2009. The entire flight test duration was 88 seconds during which time multiple staging events were performed and nine separate critically timed parachute deployments occurred as scheduled. This paper provides an overview of the guidance navigation and control technical approaches employed on this rapid prototyping activity; describes the methodology used to design the MLAS flight test vehicle; and lessons that were learned during this rapid prototyping project are also summarized.

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