Answer:
Step-by-step explanation:
Given:
P = 6.35 atm
= 1.01 × 10^5 × 6.35
= 6.434 × 10^5 N/m^2
As = 975 cm^2
D = 3.8 g/cm^2
M = 320 kg
Since the propellant volume is equal to the cross sectional area, As times the fuel length, the volumetric propellant consumption rate is the cross section area times the linear burn rate, bs , and the instantaneous mass flow rate of combustion, ms gases generated is equal to the volumetric rate times the fuel density, D
ms = D × As × bs
ms ÷ bs = M/L
M/L = 3.8 × 975
= 3705 g/cm
= 3.705 × 10^6 kg/m^3
Pressure = mass × g/area
= mass/length × time^2
t = sqrt(3.705 × 10^6/6.43 × 10^5)
= 2.4 s