Sustainer and Its Cross-Section View
The 3-d drawings for the sustainer and its cross-section view can be found below.
Figure 1: Sustainer.
Figure 2: Cross-section view of the sustainer.
Thrust Curve
Here, the thrust curve for the sustainer can be found.
Figure 3: Sustainer thrust curve.
Motor Specifications and the Nozzle
This is an M1329 motor, with a total impulse of 5.8 kNs.
The average pressure is 660 psi with a peak pressure of 825 psi.
With a mass of 6.5 lbs, the propellant contributes to more than 49% of the mass of the whole motor, which is 13.22 lbs.
Lastly, the expansion ratio for our booster is 19.75.
The nozzle has a throat diameter of 0.675 in and an exit diameter of 3.0 in. The throat length is 0.1 in.
The divergence and convergence half angles are 15.0 and 60.0 degrees, respectively. A close-up 3-d drawing of the nozzle can be found below.
Figure 4: Cross-section view of the sustainer nozzle.
Grains
The propellant used in both motors of the rocket is the Cherry Limeade.
As far as the sustainer motor is concerned, there are a total of 3 grains. From the top end of the motor up to the nozzle, these grains are ordered as follows:
- Bates: This grain has a core diameter of 0.75 in, with an outer diameter of 2.56 in and a length of 8.0 in. It has a mass of 2.285 lbs.
- Bates: This grain has a core diameter of 0.85 in, with an outer diameter of 2.56 in and a length of 8.0 in. It has a mass of 2.224 lbs.
3. Finocyl: This grain has a cire diameter of 0.85 in, with 4 fins. Each fin has a width of 0.20 in and a length of 0.65 in. The outer diameter of the grain is 2.56 in with a total length of 8.0 in. It has a mass of 1.968 lbs.
Simulator Files
For reference, the motor simulation file can be found here: 5.8KNs_M1300_24in.ric