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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
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.
RequirementsCompetition 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
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
Internal and External Structure
Internal StructureABS for Payload
Polycarbonate for motor housing
Carbon rods
Master MoldProcess 1 and 2
High density foamPrimer
Complete ToolProcess 3 and 4
Carbon Fiber ToolCarbon Fiber Part
Carbon Fiber Nose Cone and Fins
Design Specifications:Shape: Tangent OgiveLength: 15”Base Length: 4”
Justification for Design:Low Mach NumberLower Coefficient of Drag
Material:High Density FoamCarbon Fiber
Justification for Material:Lightweight overallIncreased Strength and Durability
Design Specifications:Four Fins TrapezoidalRounded Leading Edge
Justification for Design:Lightweight MaterialDurable and High ImpactHigh Thermal Resistance
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
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
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
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
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California State University, FullertonCSUFTRES.COM - [email protected]