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ERAU ISDC 2009
 

ERAU ISDC 2009

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Presentation from the International Space and Development Conference 2009 in Orlando, FL.

Presentation from the International Space and Development Conference 2009 in Orlando, FL.

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    ERAU ISDC 2009 ERAU ISDC 2009 Presentation Transcript

    • Liquid Bi-Propellant Rocket Development for Lunar Lander
      Presenters:
      Sarah Baber – Impulse Rocketry Technology, Project Manager 2008-2009
      Johann Schrell – Team Cynthion, Project Manager & Performance Director 2007-2008
      1
    • The Challenge
      Northrop Grumman Lunar Lander Challenge
      Tasked in 2007 with creating design for viable university entry
      Design the propulsion system for a separately designed lunar lander vehicle
      Must be capable of propelling vehicle:
      Minimum 50 meters vertical
      Minimum 100-120 meters translation
      Minimum 90 seconds hover
      Into a soft landing
      Propulsion was designed around these requirements and the requirements of the vehicle designers
      Team acted as subcontractor to vehicle designers
      2
    • The Teams
      Two years, two teams
      Team Cynthion 2007-2008
      Worked from requirements set forth by vehicle designers and competition
      Developed detailed designs and analysis
      Completed manufacture of parts
      Impulse Rocketry Technology 2008-2009
      Worked from requirements set forth by competition
      Developed detailed designs and analysis
      Completed manufacture and assembly of all engine components
      Completed detailed design and assembly of test equipment and feed system
      Teams consisted of undergraduate aerospace engineering seniors
      3
    • Learning Experience
      Real-world engineering environment
      Design process
      Team interaction
      Customer interaction
      Outsourcing
      Communicating with Machinists
      Research Skills
      Engineering Software
      MatLab
      Catia CAD
      NEiNastran FEA
      STAR CCM+ with CFD
      NASA CEA Thermochemical analysis
      LabView
      4
    • Economics
      Common materials
      No exotic materials means a cheaper solution
      Simple machining
      Components designed for ease of manufacture to cut machining costs
      Non-aerospace grade parts
      Components purchased from suppliers such as McMaster
      Components purchased rated high for large operating safety margins
      Money saved and reliability maintained
      Common propellants
      High performance achieved without exotic costly propellants and storage equipment
      5
    • Propellants
      Propane
      Pros:
      Readily available, stable, must be pressurized to ignite without open flame or spark, inexpensive
      Cons:
      Difficult to arrange for a high pressure certified tank to be filled, flammable when in unconfined space as a gas, little rocketry data available
      Methanol
      Pros:
      Readily available in jugs, easy to fill a high pressure tank, stays liquid at standard atmosphere
      Cons:
      Flame spreads on ground if leaked, volatile if ingested or inhaled, little rocketry data available
      Nitrous Oxide
      Pros:
      Readily available from race shops, self pressurizes, lots of data available, stable, non-toxic, non-cryogenic
      Cons:
      Difficult to purchase pure N2O (most has SO2 additive), not as capable as LOX or peroxide
      6
    • Team Cynthion
      The Engine
      Approx 1000 lbf max thrust
      Fuel: Liquid Propane (C3H8) Oxidizer: Nitrous Oxide (N2O)
      Common grade materials
      Designed for restart and throttle capability
      Full regenerative cooling system for thermal protection
      7
    • Team Cynthion
      Performance
      8
    • Team Cynthion
      Analysis
      Highest stresses in cooling jacket CFD confirms flow velocity
      9
    • Team Cynthion
      Components and Materials
      Chamber
      Copper
      Nozzle
      Copper
      Cooling Sleeve
      Low Carbon Steel
      Injector Plate and Oxidizer Dome
      Stainless Steel
      Connector Plates
      Low Carbon Steel and Copper
      Fuel Intake Manifold
      Brass
      10
    • Team Cynthion
      Unique Design Aspects
      Cooling Jacket
      Single Channel Full Jacket
      Less Time and Money for Manufacturing
      Fewer Welding/Braising Points
      Allows Side Injection
      Low Voltage Glow Plug Ignition
      Weight savings on power systems
      Safer operation
      11
    • Impulse Rocketry Technology
      The Engine
      Approx 850 lbf max thrust as designed
      Approx 250 lbf max thrust as built for subscale testing
      Fuel: Methanol (CH3OH) Oxidizer: Nitrous Oxide (N2O)
      Common grade materials
      Designed for restart and throttle capability
      Ablative and regenerative cooling system for thermal protection
      $3500 manufacturing and testing budget
      12
    • Impulse Rocketry Technology
      Performance
      13
    • Impulse Rocketry Technology
      Components and Materials
      Chamber
      Low Carbon Steel
      Nozzle
      Graphite
      Nozzle Holder
      Low Carbon Steel
      Injector Plate
      Low Carbon Steel
      Connector Plate
      Low Carbon Steel
      Gasket Rings
      Copper
      Ablative
      ITC Ceramic Coatings
      14
    • Impulse Rocketry Technology
      Stress Analysis
      15
    • Impulse Rocketry Technology
      Unique Design Aspects
      Chamber Cooling Jacket (Similar to Cynthion)
      Graphite Converging Diverging Nozzle
      Using off the shelf products wherever possible
      ITC Paint
      Nuts, Bolts, and Washers
      Spark Plug
      Feed System Plumbing
      Impinging Oxidizer Injectors
      Modular parts for easy alteration
      16
    • Application of Work
      Implications outside the student project environment.
      Affordable small propulsion systems for soft landers
      Space privatization
      X-prize
      Low complexity systems
      Easy troubleshooting
      Quick installation
      Less training required for technicians
      Low toxicity household name chemicals as propellants
      Safe handling
      Environmentally friendly combustion relative to solids, hypergolics, and Kerosene based fuels
      17
    • Praise and Questions
      Thanks to all that have made this project possible
      Dr. Eric Perrell, ERAU
      Dr. Geoffrey Kain
      Dr. Frank Radosta, ERAU
      Bill Russo, ERAU
      Rich Hedge, ERAU
      Michael Potash, ERAU
      Mohammad Naraghi, ERAU
      Advanced Machining, New Smyrna, FL
      Questions and discussion
      18