16.522, Space Propulsion Prof. Manuel martinez-Sanchez Lecture 9: Some Examples of Small Solid Propellant Rockets for In-space Propulsion The sTAR 13B incorporates the lightweight case developed for the staR 13 with the propellant and nozzle design of the earlier TE-M-516 apogee motor. The motor case has been stretched 2. 2 inches to provide for increased propellant loading the motor has been used to adjust orbit inclination of a satellite from a Delta laun MOTOR PERFORMANCE (70 F Vacuum) Burn Time/Action Time, sec 148/161 Ignition Delay Time, sec 0.02 Burn Time Average Chamber Pressure, psia 823 Action Time Average Chamber Pressure, psia 787 Maximum Chamber Pressure, psia 935 Total Impulse, Ibf-sec 26,040 Propellant: Specific Impulse, Ibf-sec/lbl 286.6 Effective Specific Impulse, Ibf-sec/Ibm Burn Time Average Thrust, Ibf 1708 Action Time Average thrust, ibf 1577 Maximum thrust ibf 2160 SPIN CAPABILITY, rpm 120 CASE 6A1-4V Titanium Minimum Ultimate Strength, psi 165,000 Minimum Yield Strength, psi 152,000 Hydrostatic Test Pressure, psi 1330 Yield pressure, psi Hydrostatic Test Pressure/Maximum Pressure 1.05 Nominal thickness in 0.035 NOZZLE Exit Cone material Vitreous silica phenolic Throat insert material ATJ Graphite Initial Throat Area, in2 Exit diameter in 8.02 Expansion Ratio, Initial/Average 49.8/41 Expansion Cone Half Angle, deg TyI Fixed Number of nozzles LINER Density Ibm/in 0.045 16.522, Space P pessan Lecture 9 Prof. Manuel martinez Page 1 of 316.522, Space Propulsion Prof. Manuel Martinez-Sanchez Lecture 9: Some Examples of Small Solid Propellant Rockets for In-space Propulsion The STAR 13B incorporates the lightweight case developed for the STAR 13 with the propellant and nozzle design of the earlier TE-M-516 apogee motor. The motor case has been stretched 2.2 inches to provide for increased propellant loading. The motor has been used to adjust orbit inclination of a satellite from a Delta launch. MOTOR PERFORMANCE (70 ° F Vacuum) Burn Time/Action Time, sec 14.8/16.1 Ignition Delay Time, sec 0.02 Burn Time Average Chamber Pressure, psia 823 Action Time Average Chamber Pressure, psia 787 Maximum Chamber Pressure, psia 935 Total Impulse, lbf-sec 26,040 Propellant: Specific Impulse, lbf-sec/lbm 286.6 Effective Specific Impulse, lbf-sec/lbm 285.7 Burn Time Average Thrust, lbf 1708 Action Time Average Thrust, lbf 1577 Maximum Thrust, lbf 2160 SPIN CAPABILITY, rpm 120 CASE Material 6Al-4V Titanium Minimum Ultimate Strength, psi 165,000 Minimum Yield Strength, psi 152,000 Hydrostatic Test Pressure, psi 1330 Yield Pressure, psi 1394 Hydrostatic Test Pressure/Maximum Pressure 1.05 Nominal Thickness, In. 0.035 NOZZLE Exit Cone Material Vitreous Silica Phenolic Throat Insert Material ATJ Graphite Initial Throat Area, in2 1.14 Exit Diameter, In. 8.02 Expansion Ratio, Initial/Average 49.8/41.0 Expansion Cone Half Angle, deg 17 Type Fixed Number of Nozzles 1 LINER Type TL-H-304 Density, lbm/ in. 3 0.045 16.522, Space Propulsion Lecture 9 Prof. Manuel Martinez-Sanchez Page 1 of 3