Да, красавец конечно
Интересно, что там за топливо. ПХА при очень большом давлении горит медленно, может поэтому так?
STAR 4G
This STAR motor was developed and tested in January 2000 under a NASA Goddard Space Flight Center program for a low-cost, high mass fraction orbit adjust motor for use in deploying constellations of very small satellites (nanosatellites). The first static test of the STAR 4G prototype motor was conducted 8 months after program start. The motor is designed to operate at high chamber pressure and incorporates a noneroding throat insert to maximize specific impulse.
MOTOR DIMENSIONS
Motor diameter, in................................................4.45
Motor length, in. ...................................................5.43
MOTOR PERFORMANCE (70°F VACUUM)
Burn time/action time, sec ...........................10.3/10.8
Ignition delay time, sec ......................................0.035
Burn time average chamber pressure, psia.......2,185
Maximum chamber pressure, psia ....................2,600
Total impulse, lbf-sec............................................595
Propellant specific impulse, lbf-sec/lbm.............275.6
Effective specific impulse, lbf-sec/lbm...............269.4
Burn time average thrust, lbf...................................58
Maximum thrust, lbf ................................................69
NOZZLE
Initial throat diameter, in. .....................................0.15
Exit diameter, in. ..................................................1.13
Expansion ratio, initial.......................................56.8:1
WEIGHTS, LBM
Total loaded .........................................................3.30
Propellant ............................................................2.16
Heavyweight Nano ESA ......................................0.17
Case assembly ....................................................0.49
Nozzle assembly .................................................0.46
Total inert.............................................................1.12
Burnout ................................................................1.07
Propellant mass fraction ......................................0.65
TEMPERATURE LIMITS
Operation ..................................................... 40º-90°F
Storage ...................................................... 40º-100°F
PROPELLANT DESIGNATION........... TP-H-3399
CASE MATERIAL..........Graphite-epoxy composite
PRODUCTION STATUS.................. Development