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tritonrocketclub / Propulsion

All propulsion work for TRC will be committed here.
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Nozzle Design Optimization #1

Open cmflannery opened 8 years ago

cmflannery commented 8 years ago

The design of the nozzle has been scaled up from previous designs used by TRC, without proper justification. The current design of the nozzle needs to be justified. Issue tickets should be opened against features of the nozzle and closed once they are properly justified.

Bslieu99019 commented 8 years ago

Important Links

  1. 8-inch Motor Calcs
  2. Nozzle wiki
Bslieu99019 commented 8 years ago

Aluminum 6061T-6 Carrier Calculations:

Hoop stress w/ FS = 2.0 => 12.8 ksi

Thermal Stress w/ 300 F & FS = 2 => 31.7 ksi (various with temperature) Aluminum Melting point = 1080 - 1205 °F

Tensile Strength Aluminum = 40 kpsi Minimum thickness w/ FS = 2: 0.133125 inches

Ultimate Bursting Pressure = 3000 psi Yield Bursting Pressure = 2666.67 psi Maximum Pressure Experienced = 710 psi

jacquelynfirst commented 8 years ago

I worked on the aluminum carrier with Ryan and this is what we found so far. We got a thermal stress of about 55,000psi with a temp estimate of 430 degree F change. Also Hoop stress was 7,114psi with factor of safety of 5.6.

Happy Halloween!

dtt005 commented 8 years ago

Best diameter for diverging section = 5.618in Optimum Expansion Ratio = 6.177 Pressure experienced of aluminum skirt at exit plane = 16.546PSI (12.589% higher than atmospheric pressure) Temperature experienced of aluminum skirt at exit plane = Chamber temperature is giving Bill Lieu a headache right now. No value for now...