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 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, in
2
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
IGNITION 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 +110
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
Effective Ratio of Specific Heats (chamber) 1.16
(Nozzle Exit) 1.21
CURRENT STATUS Production
BC1355B 4/91
16.522, Space Propulsion Lecture 9
Prof. Manuel Martinez-Sanchez Page 3 of 3