Download to read offline
Uploaded byPrakul Mittal
Cdr final(propulsion) (1)
The document provides details of the hybrid rocket motor design for Space Concordia's entry in the 9th Intercollegiate Rocket Engineering Competition. The hybrid motor uses HTPB fuel and nitrous oxide oxidizer and is designed to reach an altitude of 10,000 feet. Key specifications discussed include the grain design, motor dimensions, injector design, and nozzle parameters.
Engineeringâ—¦
Cdr final(propulsion) (1)
- 1. 9th Intercollegiate Rocket Engineering Competition Critical Design Review SPACE CONCORDIA ROCKETRY DIVISION FEB 13TH, 2014
- 2. Competition Overview •IntercollegiateRocket Engineering Competition (IREC) ◦ June 26th-28th, 2014 ◦ Green River, Utah ◦ International schools •Last year’s winners • Basic: Polytéchnique (2nd win) • Advanced: New Mexico Institute of Mining and Technology
- 3. Hybrid Motor Rocket Customized HTPB-N2O Hybrid Motor capable of reaching 10,000 ft. Initial Fixed values Chamber Pressure 400 psi (Iterated 300 to 450 psi) Altitude 10,000 ft. Specific Impulse (Isp) 200 (Iterated till 260) Burn time, Tb 10 sec Average Thrust 1000 N Booster ratio 3.32
- 4. Ballistics Values _____________________________________________________________________________________________________________________________________________________________________________________________________________________________ Mass flow rate 0.4846 Kg/s Mass of Propellant 3.243 Kg (HTPB) Chamber temperature, Tc 2031 K Characteristics Exhaust velocity, C* 1361 m/s Exhaust Velocity, C 1963 m/s Pressure at exit 15.267 psi Burning rate 3.1 mm/s O/F ratio 2.1
- 5. Grain Design Grainlength 524.21 mm Inner diameter 34.6 mm Outer diameter 94 mm Burn Area 0.057 m2 Port Area 0.00094 m2 Web thickness 30.99 mm Density (HTPB) 930 Kg/m3
- 6. Motor Dimensions ______________________________________________________________________________________________________________________________________________________________________________________________________________________________ Motor Dimensions 630 mm X 98 mm Thrust Chamber 585.77 mm X 1.27 mmX 98 mm Casing thickness 1.27 mm (0.05 in AL 6060-T6) Thrust Chamber Material AL 6061-T6 Designed Pressure 800 psi
- 7. Liquid N2O Injector __________________________________________________________________________________________________________________________________________________________________________________________________ Material 17-4 Stainless Steel Dimensions 26 mm OD X 4 mm thick) Orifices type Short tube ( 5 holes X 2 mm dia.) Discharge Coefficient 0.86 Bulkhead Dimensions 94 mm dia. X 0.635 mm thick (AL alloy)
- 8. Nozzle parameters __________________________________________________________________________________________________________________________________________________________________________________________________ Inlet Diameter 32.2 mm Throat Diameter 21.9 ~ 22 mm Exit Diameter 43.92 mm ~ 44 mm Converging Half Angle 22` Diverging Half Angle 12` Expansion Ratio 4.095
- 9.
- 10.