(Solved): As a new rocket design engineer, you are asked to determine performance parameters for a solid prop ...

As a new rocket design engineer, you are asked to determine performance parameters for a solid propellant engine based on available propellant characterization measurements. The engine operates with a solid propellant with a combustion index n = 0.55 along with a thrust coefficient C of 1.05, and a characteristic velocity C of 2025 m/s. When the unburnt propellant temperature is 15°C and the chamber pressure is 5.5 MPa, the regression rate happens to be 34 mm/s. Consider the throat area as 450 × 106 m² and propellant density as 1350 kg/m³ d) In this problem, If the temperature sensitivity of the burning rate happens to be 0.008/°C and the burning surface area to throat area K is 45, determine the chamber pressure and thrust at the unburnt temperature of 48°C (assuming that Cand C remain almost constant)? Consider the throat area as 375 x 106 m² and propellant density as 1295 kg/m³ e) How does the solution vary with variations in the unburnt propellant temperature of +/- 20 deg (28°C and 68°C). Assume the other parameters are constant. f) How does the solution vary with variations in the unburnt propellant temperature of +/- 20% (n 0.66 and n = 0.44) in combustion index (Assume the other parameters are constant.