The following measurements were made in a sea level test of a solid
propellant rocket motor:
Burn duration
Initial mass before test
40 Sec
1210 kg
Mass of rocket motor after test
215 kg
Average thrust
62,250 N
Chamber pressure
7.00 MPa
Nozzle exit pressure
0.070 MPa
Nozzle throat diameter
0.0855 m
Nozzle exit diameter
0.2703 m
Determine the $\dot{m}$, $V_2$, $C^*$, $C$, and $I_s$ at sea level, and $C$ and $I_s$ at 1000 and
25,000 m altitude. Assume an invariant thrust and mass flow rate and
negligible short start and stop transients.
[OR]
Determine the flight characteristics of an electrical propulsion rocket for
raising a low satellite orbit. Data given:
$I_s$
= 2000 s
F
= 0.20 N
Duration
= 4 weeks
Payload mass = 100 kg
$\alpha$
= 100 W/kg
$\eta$
= 0.5