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rl-36 pdrlaunch.rit.edu/uploads/1/1/4/2/114234541/pdr.pdf · 2020. 6. 10. · we based our design...

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RL-36 PDR RIT Launch Initiative Propulsion Team

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  • RL-36 PDR

    RIT Launch Initiative Propulsion Team

  • Goal

    To safely and successfully design, manufacture, and test a liquid bipropellant rocket engine to gain experience with liquid rocket design.

  • Overview

    ● Thrust: 36 lbf● Specific Impulse: 248 sec● Fuel: methyl alcohol (CH

    3OH)

    ● Oxidizer: gaseous oxygen (O2

    )● O/F ratio: 1.2

  • Combustion Chamber

    MATLAB Inputs:

    ● Chamber Pressure =300 psi● O/F Ratio =1.2● Chamber Temp =5680 °R● Isp =248 sec● Thrust =36 lbf● Gamma =1.2 (ratio of specific heats of propellants)● G = 32.2 ft/sec^2● L*= 60 in (characteristic chamber length)

  • Combustion Chamber (cont.)

  • Combustion Chamber (cont.)

  • Combustion Chamber BOM

    ● Copper: ~ $250 for 3in x 11in● Steel: ~ $40 for 3in x 11in

  • Cooling System

    ● Low-temperature materials of combustion chamber require active cooling to perform

    ● Cooling system will flood outside of combustion chamber with a continuous flow of water

    ● Electronics monitor temperature of incoming water, determine if cooling system is not keeping pace

  • Cold water enters at the thinnest point of the nozzle neck

    Cooling System

  • Internal geometry ensures water does not immediately move to outflow pipe

    Cooling System

  • Hot water outflows near injector

    Cooling System

  • Brass CAM locks allow quick connection and disconnection from the cooling system

    Cooling System

  • Cooling System

    ● Multiple different cooling systems can be considered based on cost, fire frequency, and fire duration.

    ● Cheapest Option: 5-gallon bucket and an aquarium pump○ Costs less than $25, will need a long time to cool between

    fires● Alternative Options: Active Chiller Systems

    ○ Very expensive, will allow hot fires in excess of 2 years long.

  • Cooling System - Estimated BOM

    Item Cost

    CAMs $50

    Raw Materials $30

    Cooling System Option 1 $60

    Cooling System Option 2 $400

    Miscellaneous $30

  • Injector: Reference Material

    We based our design and calculations from RocketLab’s HOW to DESIGN, BUILD and TEST SMALL LIQUID-FUEL ROCKET ENGINES .

    Differences: Our motor is bigger and more powerful. 30 holes oxidizer holes, rather than 4.

    Manufacturing assembly requires no welding but additional threading.

    Spray Nozzle

  • Injector: Calculations

    Using the formulas given from RocketLabs document, we used Matlab to generate our numbers

  • Injector CAD

  • Injector BOM

    Option 2: Buy Spray Nozzle

    We can buy a Full-Cone Spray Nozzle from McMaster at differing spray angles for 30-40$.

    Option 1: Manufacture Spray Nozzles from stock

    304 Stainless steel stock ¾ in diameter, 1

    foot $12.26 (sourced)

    304 Stainless steel stock 2 ½ in diameter,

    6 inches $35.62 (sourced)

  • Feed System

    Fuel Tank: 12” x 4” ID x 0.25” stainless steel

    Estimated BOM:Fuel Tank $50Nitrogen Tank $0Oxygen Tank $150Pressure Gages $30Check Valves $80Remote Valves $400Pressure Regulators $200Piping $40

    Total: $950

  • Control systems

    ● Provide remote control/monitoring for feed system and engine.

    ● Ensure rapid and consistent operation of procedures.

    ● Help ensure system fails safe.

    ● Still allows for remote manual shutoff of systems.

  • Block diagram

  • Control Systems BOM

    There are potential items left from hybrid testing, must ensure functionality and reassemble components.

    Item Cost

    Sensors $240

    PCB $50

    Electronics $80

    Cabling $40

    Thermocouples $40

    Battery $30

  • Test Stand

    ⅛” Steel shield

    1/2” Plywood

    Engine Interface

  • Test Stand BOM

    ● 80/20: ~$20● Steel: ~$10● Plywood: ~$5● Hardware: ~$5

  • Questions?


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