Design and Development of a Cost-Effective Reloadable Motor …
447
Table 1 Specification of
motor
Parameter
Values
Motor class
G158
Thrust time, s
0.99
Total impulse, Ns
156.20
Specific impulse, s
141.92
Maximum thrust, N
688
Average chamber pressure, MPa
15.7
Launch mass, g
225
Empty mass, g
125
Length of the motor, mm
185
Diameter of the motor, mm
33.02
Based on the above variations, the specifications of the motor were selected as
shown in Table 1.
2.5 Rocket Modelling and Flight Simulation
The components of the rocket were modelled and assembled in Open Rocket Simulator software. The rocket was modelled to have the least drag co-efficient and
maximum stability (without making it overstable). To improve the stability, material
was added at the nose and the fin areas without affecting the drag co-efficient much.
The total drag co-efficient of the rocket was found to be 0.94 and its stability was
1.55 cal well within the acceptable range of is 1.5–2 cal. The component analysis for
drag characteristic is as shown below (Fig. 4).
Fig. 4 3D model of the model rocket
447
Table 1 Specification of
motor
Parameter
Values
Motor class
G158
Thrust time, s
0.99
Total impulse, Ns
156.20
Specific impulse, s
141.92
Maximum thrust, N
688
Average chamber pressure, MPa
15.7
Launch mass, g
225
Empty mass, g
125
Length of the motor, mm
185
Diameter of the motor, mm
33.02
Based on the above variations, the specifications of the motor were selected as
shown in Table 1.
2.5 Rocket Modelling and Flight Simulation
The components of the rocket were modelled and assembled in Open Rocket Simulator software. The rocket was modelled to have the least drag co-efficient and
maximum stability (without making it overstable). To improve the stability, material
was added at the nose and the fin areas without affecting the drag co-efficient much.
The total drag co-efficient of the rocket was found to be 0.94 and its stability was
1.55 cal well within the acceptable range of is 1.5–2 cal. The component analysis for
drag characteristic is as shown below (Fig. 4).
Fig. 4 3D model of the model rocket