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  3. a classical hybrid rocket propulsion system has the following characteristics...

Question: a classical hybrid rocket propulsion system has the following characteristics...

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A classical hybrid rocket propulsion system has the following characteristics: Propellant: LOX/HTPB Burn time: 20s Initial Chamber Pressure:600 psi initial mixture ratio: 2 initial nozzle exit area: 10 fuel grain outside diameter: 12 in Grain geometry: single cylinder case bonded initial htpb temp: 65 degrees F Determine: Initial and Final Thrust, specific impulse, propellant masses, and useful propellant Vacuum ambient conditions, Port diameter at t=20s equals the fuel grain outside diameter, Rf, c* efficiency is 0.95, and Constant oxidizer mass flow rate. From a chart Cf=1.7 k=1.152 c*=5912 ft/s

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