IGNITION TRAIN Components S&A/etA/TBi/pyrogen igniter Minimum Firing Current per Detonator, amperes 5.0 Circuit Resistance per Detonator, ohms 1.0 No, of detonators and tbis Squib or Tbi compatible WEIGHTS Ibm Total Loaded 103.7 Propellant 90.9 Case Assembly 5.64 Nozzle assembl Igniter Assembl 0.68 Internal Insulation 2.34 Liner 0.14 Miscellaneous 0.28 Total Inert(excluding igniter propellant) 12.80 Burnout 12.30 Propellant Mass Fraction 0.87 TEMPERATURE LIMITS Operation 40to+110°F Storage 40to+110°F PROPELLANT Propellant Designation and Formula TP-H-3082 AP-70 A|-16% CTPB Binder-14%/ PROPELLANT CONFIGURATION Type Internal burning 8-point star Web. it Web fraction %/o Silver fraction %o Propellant Volume, in3 1446 Volumetric Loading Density 92 Web Average Burning surface Area, in 345 Initial Surface to throat Area ratio 316 PROPELLANT CHARACTERISTICS Burn Rate at 1000 psia, in /sec 0.301 Burn rate Exponent 0.31 Density Ibm/i 0.0628 Temperature Coefficient of Pressure, %o/F Characteristic Exhaust Velocity, ft/sec 5025 Adiabatic Flame Temperature, F 16.522, Space Propulsion Lecture 9 Prof. Manuel martinez-Sanchez Page 2 of 3IGNITION TRAIN Components Minimum Firing Current per Detonator, amperes Circuit Resistance per Detonator, ohms No. of Detonators and TBIs Squib or TBI compatible S&A/ETA/TBI/pyrogen igniter 5.0 1.0 2 WEIGHTS, lbm Total Loaded 103.7 Propellant 90.9 Case Assembly 5.64 Nozzle Assembly 3.72 Igniter Assembly 0.68 Internal Insulation 2.34 Liner 0.14 Miscellaneous 0.28 Total Inert (excluding igniter propellant) 12.80 Burnout 12.30 Propellant Mass Fraction 0.87 TEMPERATURE LIMITS Operation 40 to +110°F Storage 40 to +110°F PROPELLANT Propellant Designation and Formula TP-H-3082 AP-70% Al-16% CTPB Binder-14% PROPELLANT CONFIGURATION Type Web, In. Web Fraction, % Silver Fraction, % Propellant Volume, in.3 Volumetric Loading Density Web Average Burning Surface Area, in.2 Initial Surface to Throat Area Ratio Internal burning, 8-point star 4.187 62 2 1446 92 345 316 PROPELLANT CHARACTERISTICS Burn Rate at 1000 psia, in./sec 0.301 Burn rate Exponent 0.31 Density, lbm/in.3 0.0628 ° Temperature Coefficient of Pressure, %/ F 0.10 Characteristic Exhaust Velocity, ft/sec 5025 ° Adiabatic Flame Temperature, F 5662 16.522, Space Propulsion Lecture 9 Prof. Manuel Martinez-Sanchez Page 2 of 3