1. Application of Emerging Techniques and
Technologies in Rocket Engineering
Titan Rocket Engineering Society
Adrian Iniguez, Pablo Vazquez , Sara Martinez, Raul
Perez, Christian Fascio, Jeff Lopez, Irvin Medina

2. Design Goals
-Design, Build, and Launch a
rocket that can reach a target
altitude of 10,000 ft. and
design a payload that performs
a scientific function
-Implement new design and
manufacturing methods and
technology
-Reduce the amount of
commercially bought items
used in the final design.

3. Requirements
Competition Requirements
-Design should reach a target altitude of 10,000 ft.
-Payload must be 10lb.
-Payload must not affect trajectory
-Structure must house payload
-Structure must be reusable
-Deployment of 1st parachute must reduce speed to 75-100 ft/s
-Deployment of 2nd parachute must reduce speed to 30 ft/s
Engineering Requirements
-Design should reduce the amount of drag
-Must house payload without affecting center of mass
-Recovery system must deploy parachute upon apogee
-Design must be lightweight

4. Schedule: Milestones
● Compete, June 14-19, 2016
● Prototype Testing April
19, 2016
● 2nd Progress Report
February 5, 2016
● Manufacture February 2,
2016
● 1st Progress Report
December 4, 2015
● 3rd Progress Report
May 6, 2016
● Systems Integration/
Finalize Assembly, May
5, 2016
● Test Launch,
May 14th, 2016
● Bring Home the
Gold June 19, 2016
● Research/Design
November 5, 2015
● Identify Systems
October 1, 2015

5. Internal and External Structure
Internal Structure
ABS for Payload
Polycarbonate for motor
housing
Carbon rods
Master Mold
Process 1 and 2
High density foam
Primer
Complete Tool
Process 3 and 4
Carbon Fiber Tool
Carbon Fiber Part

6. Carbon Fiber Nose Cone and Fins
Design Specifications:
Shape: Tangent Ogive
Length: 15”
Base Length: 4”
Justification for Design:
Low Mach Number
Lower Coefficient of Drag
Material:
High Density Foam
Carbon Fiber
Justification for Material:
Lightweight overall
Increased Strength and
Durability
Design Specifications:
Four Fins
Trapezoidal
Rounded Leading Edge
Justification for Design:
Lightweight Material
Durable and High Impact
High Thermal Resistance

7. Propulsion
● Total Impulse
○ 1,157 lb-s
● Fuel Weight
○ 8.6 lb
● 304 Stainless Steel Nozzle/ Forward Closure
Manufacturing Motor Housing 1 Grain Burn Test

8. Payload
Payload Items
● Payload is an atmospheric monitoring
system
○ Consists of a linear actuator, airtight
vial, raspberry pi, two power sources ,
and GoPro
● Rails allow the placement and removal of
the payload to be done quickly
● Linear actuator will activate after apogee and
drogue parachute deployment to seal a
sample of air.
● Gas sensor will measure propane , hydrogen,
and LPG (liquified petroleum
● GoPro records video footage on
ascent/descent
● Real Time GPS Tracking through ( BRB
GPS Transmitter) BRB=Big Red Bee

9. Recovery System
• Dual Deployment
– low drift/low impact
• 3D Printing
• Harness Material: Kevlar
– High tensile strength (352,000 psi)
– Flame resistant (800-900°F Decomp. Temp)
– Low stretch (4.1% Break Elongation)
• Mathematical Sewing Pattern
• Hemispherical Shape
– Adopted from recent SOYUZ
TMA-18M spacecraft descent
• Ground Testing
– Parachute deployment: Successful

10. Results and Discussion
Predicted Simulation Results:
Altitude: 9983.89 ft.
Max Velocity: 769.51 ft./s
Mach Number: 0.78
Static Margin: 1.67
Total Cd: 0.45
What these results mean:
We reached a competitive altitude for IREC
Velocity and safety values are within acceptable parameters

12. Launch with Us
California State University, Fullerton
CSUFTRES.COM - CSUFTRES@GMAIL.COM