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Testing Orions Fairing Separation SystemTraditional fairing systems are designed to fully encapsulate and protect their payload from the harsh ascent environment including acoustic vibrations, aerodynamic forces and heating. The Orion fairing separation system performs this function and more by also sharing approximately half of the vehicle structural load during ascent. This load-share condition through launch and during jettison allows for a substantial increase in mass to orbit. A series of component-level development tests were completed to evaluate and characterize each component within Orion's unique fairing separation system. Two full-scale separation tests were performed to verify system-level functionality and provide verification data. This paper summarizes the fairing spring, Pyramidal Separation Mechanism and forward seal system component-level development tests, system-level separation tests, and lessons learned.
Document ID
20150004067
Acquisition Source
Goddard Space Flight Center
Document Type
Conference Paper
Authors
Martinez, Henry
(Lockheed Martin Space Systems Co. Denver, CO, United States)
Cloutier, Chris
(Lockheed Martin Space Systems Co. Denver, CO, United States)
Lemmon, Heber
(Lockheed Martin Space Systems Co. Denver, CO, United States)
Rakes, Daniel
(Lockheed Martin Space Systems Co. Denver, CO, United States)
Oldham, Joe
(Lockheed Martin Space Systems Co. Denver, CO, United States)
Schlagel, Keith
(Lockheed Martin Space Systems Co. Denver, CO, United States)
Date Acquired
April 2, 2015
Publication Date
May 1, 2014
Publication Information
Publication: The 42nd Aerospace Mechanism Symposium
Subject Category
Spacecraft Design, Testing And Performance
Launch Vehicles And Launch Operations
Mechanical Engineering
Distribution Limits
Public
Copyright
Public Use Permitted.
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