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Predicting Ares I Reaction Control System Performance by Utilizing Analysis Anchored with Development Test DataThe Ares I launch vehicle is an integral part of NASA s Constellation Program, providing a foundation for a new era of space access. The Ares I is designed to lift the Orion Crew Module and will enable humans to return to the Moon as well as explore Mars.1 The Ares I is comprised of two inline stages: a Space Shuttle-derived five-segment Solid Rocket Booster (SRB) First Stage (FS) and an Upper Stage (US) powered by a Saturn V-derived J-2X engine. A dedicated Roll Control System (RoCS) located on the connecting interstage provides roll control prior to FS separation. Induced yaw and pitch moments are handled by the SRB nozzle vectoring. The FS SRB operates for approximately two minutes after which the US separates from the vehicle and the US Reaction Control System (ReCS) continues to provide reaction control for the remainder of the mission. A representation of the Ares I launch vehicle in the stacked configuration and including the Orion Crew Exploration Vehicle (CEV) is shown in Figure 1. Each Reaction Control System (RCS) design incorporates a Gaseous Helium (GHe) pressurization system combined with a monopropellant Hydrazine (N2H4) propulsion system. Both systems have two diametrically opposed thruster modules. This architecture provides one failure tolerance for function and prevention of catastrophic hazards such as inadvertent thruster firing, bulk propellant leakage, and over-pressurization. The pressurization system on the RoCS includes two ambient pressure-referenced regulators on parallel strings in order to attain the required system level single Fault Tolerant (FT) design for function while the ReCS utilizes a blow-down approach. A single burst disk and relief valve assembly is also included on the RoCS to ensure single failure tolerance for must-not-occur catastrophic hazards. The Reaction Control Systems are designed to support simultaneously firing multiple thrusters as required
Document ID
20100032022
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Stein, William B. (Jacobs Technologies Engineering Science Contract Group Huntsville, AL, United States)
Holt, K. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Holton, M. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Williams, J. H. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Butt, A. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Dervan, M. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Sharp, D. (Jacobs Technologies Engineering Science Contract Group Huntsville, AL, United States)
Date Acquired
August 25, 2013
Publication Date
July 25, 2010
Subject Category
Launch Vehicles And Launch Operations
Report/Patent Number
M10-0085
Meeting Information
Meeting: 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference
Location: Nashville, TN
Country: United States
Start Date: July 25, 2010
End Date: July 28, 2010
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NNM05AA50C
Distribution Limits
Public
Copyright
Public Use Permitted.

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