Our Project


The Payload

Our project this year centers on airflow and its relation to the rocket. By collecting data from both pressure sensors during flight and while in a wind tunnel, we will be able to observe discrepancies betwixt the two. As wind tunnels, which are unable to accurately reflect parts of actual rocket flight (such as fast changes in speed), are frequently used in order to test commercial rockets, any possible differences which appear in the collected data could be useful. To further explore potential problems of using only wind tunnels for testing, we will secure various obstacles onto the rocket similar to those found on commercial rockets, such as fuel lines or electronic boxes. Pressure sensors will be placed around these obstacles to collect the data.

The Vehicle

Structural System

The structural system consists of 4” and 6” diameter fiberglass tubing. Two sets of four fins made of G10 fiberglass will be attached with through the wall construction to the motor mounts in either stage.

Entire Vehicle

Figure 1: A two dimensional schematic of the entire rocket with center of gravity and center of pressure indicated (the rocket is shown in the liftoff configuration).

Vehicle Parameters

Length [in]

Weight [lbs]

Diameter [in]

Motor Selection

Stability Margin [calibers]

Thrust To Weight Ratio

158 in.

37.45

6

K1275N

2.98

6.27
Table 1: The rocket’s dimensions, stability and propulsion (at liftoff)


Figure 2: A three dimensional schematic of the entire rocket

Letter

Part

Letter

Part

A

Nosecone

H

Payload Bay

B

Main Parachute

I

Payload Electronics

C

Sustainer
 E-Bay

J

Drogue Parachute

D

Fins

K

Motor Mount

E

Transition

L

Main Parachute

F

Booster
E-Bay

M

Payload Electronics

G

Fins

N

Motor Mount
Table 7: Rocket sections and parts

Sustainer

Figure 3: A two dimensional schematic of the sustainer part of the rocket

Sustainer Parameters

Length [in]

Weight [lbs]

Diameter [in]

Motor Selection

Stability Margin (calibers)

Thrust To Weight Ratio

94

12.67

4

J540R

4.74

8.88
Table 8: The dimensions of the sustainer, stability margin and propulsion


Figure 4: A three dimensional schematic of the sustainer

Flight Sequence


Figure 5: Flight sequence of the rocket from liftoff to touchdown 1. First stage burn. 2. Stage separation. 3. Booster coasts to its apogee and deploys main parachute. 4. Booster lands safely. 5. Second stage motor burn. 6. Sustainer reaches apogee, deploys drogue parachute 7. Sustainer descends under drogue parachute to 500ft. 8. Main parachute deploys, slowing rocket to safe landing speed of 15-20 fps. 9. Sustainer lands safely.