446
Ravikiran et al.
Fig. 2 Drawing and 3D model of the nozzle
(L dn ) of the nozzle were determined to be 9.9 mm and 48.1 mm, respectively. Figure 2
shows the drawing and the 3D model of the nozzle created using SOLIDWORKS.]
Inorder to analyze the pressure, temperature and velocity distribution within the
nozzle, a 2D finite element model of the nozzle was created in ANSYS. The inlet
gauge pressure was fixed at 6.3 × 10
5 Pa and the outlet gauge pressure was fixed at
0 Pa. Further to analysis, the nozzle was fabricated out of aluminium using the CNC
machining process.
2.4 Evaluation of Motor Performance
Inorder to evaluate the motor performance and establish its specifications, the Meteor
software was used. By specifying the type of propellant, nozzle dimensions and grain
dimensions as input parameters, the time-varying thrust, mass flow rate, KN and
chamber pressure curves were generated alongside the total thrust time. Figure 3
shows the results of the analysis.
Fig. 3 Variation of KN (65 g), chamber pressure, mass flow rate and thrust with burn time
Ravikiran et al.
Fig. 2 Drawing and 3D model of the nozzle
(L dn ) of the nozzle were determined to be 9.9 mm and 48.1 mm, respectively. Figure 2
shows the drawing and the 3D model of the nozzle created using SOLIDWORKS.]
Inorder to analyze the pressure, temperature and velocity distribution within the
nozzle, a 2D finite element model of the nozzle was created in ANSYS. The inlet
gauge pressure was fixed at 6.3 × 10
5 Pa and the outlet gauge pressure was fixed at
0 Pa. Further to analysis, the nozzle was fabricated out of aluminium using the CNC
machining process.
2.4 Evaluation of Motor Performance
Inorder to evaluate the motor performance and establish its specifications, the Meteor
software was used. By specifying the type of propellant, nozzle dimensions and grain
dimensions as input parameters, the time-varying thrust, mass flow rate, KN and
chamber pressure curves were generated alongside the total thrust time. Figure 3
shows the results of the analysis.
Fig. 3 Variation of KN (65 g), chamber pressure, mass flow rate and thrust with burn time