Ares I Integration Approach
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The document summarizes the Ares I integration approach for launching the Orion spacecraft. It describes the key elements and configuration of the Ares I rocket, including the first and upper stages. It also outlines the vehicle integration organization and control processes for integrating the different components. Finally, it provides an overview of some of the engineering responsibilities involved in Ares I integration like aerodynamics, loads, guidance and flight control systems.
Ares I Integration Approach
- 1. Ares I Integration Approach Jim Reuter Manager, Ares Vehicle Integration American Astronautical Society Wernher von Braun Memorial Symposium October 21, 2008 National Aeronautics and Space Administration
- 2. Ares I Elements First Stage Derived from current Shuttle RSRM/B Five segments/Polybutadiene Acrylonitrile (PBAN) propellant Recoverable New forward adapter Avionics upgrades ATK Launch Systems Upper Stage Engine Saturn J-2 derived engine (J-2X) Expendable Pratt and Whitney Rocketdyne Orion CEV Interstage Instrument Unit Primary Ares I control avionics system NASA Design / Boeing Production DAC 2 TR 6 Encapsulated Service Module (ESM) Panels Upper Stage 137.1 mT (302.2K lbm) LOX/LH 2 prop 5.5-m (18-ft) diameter Aluminum-Lithium (Al-Li) structures Instrument unit and interstage Reaction Control System (RCS) / roll control for first stage flight Primary Ares I control avionics system NASA Design / Boeing Production Stack Integration 927.1 mT (2,044.0K lbm) gross liftoff mass (GLOM) 99.1 m (325.0 ft) in length NASA-led
- 3. Vehicle Integration Organization Technical Authorities Chief Engineer Avionics & SW Chief Eng Deputy Chief Engineer Chief Safety Officer Vehicle Integration Office Manager Deputy Technical Assistant (LaRC) MSA Program Planning & Control Matrix Direct Product Lead Systems Management WBS Mgr 5.2.1 Product Lead Systems Requirements & Design Integration WBS Mgr 5.2.2 Product Lead Operations & Supportability WBS Mgr 5.2.5 Product/Sub-Product Leads (LaRC) Integrated Design & Analysis WBS Mgr 5.2.4 Product Lead (ARC) Avionics Integration & Vehicle Systems Test WBS Mgr 5.2.6 Product Lead (ARC) Crew Safety & Reliability WBS Mgr (ARC) 5.2.7 Product Lead Vehicle Development & Flight Evaluation WBS Mgr 5.2.8 Lead Systems Engineer Cross-Discipline Integration Functions Chief Architect Operability Manager Ares V Vehicle Integration Lead Project Integration
- 4. Integration Control Process Ares Project Control Board (PCB) Ares VICB CE Review Board FS ECB FS ERB US ECB US ERB USE ECB USE ERB Contractor CCB Design Activity (CCB) Contractor CCB As Required CxP Control Board (CxCB) SR&QA Control Board CxP Operations Integration Control Board (OICB) CxP Systems Engineering Control Board (SECB)
- 5. Technical Authority NASA Administrator Deputy Administrator Associate Administrator NASA Chief Engineer MSFC Center Director MSFC Eng Director MSFC Eng Dept/Lab Managers MSFC Eng Division Chiefs MSFC Eng Branch Chiefs MSFC Chief Eng Manager* MSFC Eng Deputy Directors - Senior Eng Management Presence MSFC Project Chief Eng* MSFC Chief Eng Manager’s Staff* Project Manager Program/Project Appeal Engineering Technical Appeal Mission Directorate AA Program Manager MSFC Institutional Eng Center Discipline Leads Independent Reviews Independent Reviews Direct Report Program Authority Technical Authority Senior Eng Presence Organizational Change *
- 6. Ares Integrated Launch Vehicle Responsibilities DAC 2 TR 6 Reference and Design Trajectories Launch SRB Splashdown Maximum Dynamic Pressure Time = 58.6 sec Altitude = 39,669 ft Mach = 1.60 Dynamic Pressure = 767 psf Solid Rocket Booster (SRB) Separation Time = 125. 9 sec Altitude = 188,493 ft Mach 5.84 Max Altitude = 332,903 ft Dynamic Pressure = 16.4 psf) Main Engine Cutoff (MECO) Time = 590.7 sec Burn Duration = 463.8 sec Spacecraft Separation Maximum Axial Acceleration 3.79 g Liftoff Time = 0.6 sec Thrust-to-Weight Ratio = 1.57 Gross Liftoff Mass (GLOM) = 2,043,946 lbm Main Engine Start Time = 126.9 sec Launch Abort System (LAS) Jettison Time = 156.9 sec Altitude = 269,191 ft Mach = 7.14 Upper Stage Impact (Indian Ocean) Time from Single Engine Cutoff (SECO) to Apogee Altitude = 70 nmi – 20.4 x 185,200 m – 11.0 x 100.0 nmi = 21.7 min
- 7. Ares Integrated Launch Vehicle Responsibilities Aerodynamics Wind Tunnel Testing CFD ADAC-2B 1% Force & Moment Testing 255 Runs Completed LaRC Unitary Plan Wind Tunnel Oct 22 – Nov 12, 2007 Boeing Polysonic Wind Tunnel Nov 26 – 29, 2007 299 Runs Completed First Stage/Upper Stage Separation Analyses C p Max Min
- 8. Loads Reference & Design Trajectories Ares Integrated Launch Vehicle Responsibilities Guidance, Navigation & Flight Control
- 9. Systems Integration Lab Ares Integrated Launch Vehicle Responsibilities Communications
- 10. Integrated Ares I Ascent Abort Risk Assessment Model Loss of Mission (LOM) and Loss of Crew (LOC) Probabilities for Ares I Ascent High-fidelity CFD Simulations Ascent Risk Assessments, Hazards Controls, FMEAs Ares Integrated Launch Vehicle Responsibilities Failure 1 Failure 2 Failure 3 Failure 4 Failure 5 Failure 6 Failure 7 Failure 8 Failure 9 Failure 10 Failure 11 Failure 12 Failure 13 Failure 14 Failure 15 Failure 16 Failure 17 Failure 18 Failure 19 Failure 20 Failure 21 Debris Strike Probability Analysis Latitude Longitude Fireball Environment Analysis Blast Overpressure Analysis
- 11. Constellation Inter-Project Interfaces Vehicle Assembly Operation Launch Pad Operation Orion
- 13. Preliminary Design Review Results Excellent support and participation from across the Agency Significant progress from System Definition Review to Preliminary Design Review: Requirements and their flowdown are stabilizing Products were of high quality commensurate with the design phase Excellent incorporation of safety and mission assurance early in the design Areas for increased emphasis exist: Incorporation of thrust oscillation mitigation into design Environments and staging events have design challenges Interface control and control of analytical models Maturation of integrated test planning Improve fidelity of critical risk mitigation plans Emphasize incorporating additional operability into design Unanimous agreement from the PDR Board that Ares I is ready to proceed to CDR
- 14. 7614 . SMDC_Briefing . National Aeronautics and Space Administration www.nasa.gov/ares
Editor's Notes
- #2: Ambassador Plus Briefing Script v0608 Welcome, and thank you for taking this time with me. I would like to share with you some of the exciting things being done by your space program.