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Application of Emerging Techniques and Technologies in Rocket EngineeringTitan Rocket Engineering SocietyAdrian Iniguez, Pablo Vazquez , Sara Martinez, Raul Perez, Christian Fascio, Jeff Lopez, Irvin Medina

Hello we are the Titan rocket engineering society , my name is Adrian and I am team captain - pablo vazquez recovery

And today we will be talking about our senior design project

Adrian Iniguez () - Make One SlideDesign 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.

The goal is the senior design team was to design build and launch a rocket to 100000 ft with a scientific payload to compete in the intercollegiate rocket engineering competition

Our focus was on creating and interdisciplinary team that would use new and emerging manufacturing techniques

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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/sEngineering 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

3 main competition requirements Reach 10000 ft Carry a 10lbbpayload Relaunch able after recovery

Additional engineering requirements Lightweight Low drag Apply new emerging manufacturing texnologies #

Schedule: Milestones Compete, June 14-19, 2016

Prototype Testing April 19, 20162nd Progress Report February 5, 2016Manufacture February 2, 20161st Progress Report December 4, 20153rd Progress Report May 6, 2016Systems Integration/ Finalize Assembly, May 5, 2016Test Launch, May 14th, 2016Bring Home the Gold June 19, 2016Research/Design November 5, 2015Identify Systems October 1, 2015

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Internal and External Structure

Internal StructureABS for PayloadPolycarbonate for motor housingCarbon rodsMaster MoldProcess 1 and 2High density foamPrimerComplete ToolProcess 3 and 4Carbon Fiber ToolCarbon Fiber Part

Carbon Fiber Nose Cone and Fins

Design Specifications:Shape: Tangent OgiveLength: 15Base 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 Impulse1,157 lb-sFuel Weight 8.6 lb304 Stainless Steel Nozzle/ Forward ClosureManufacturing Motor Housing1 Grain Burn Test

Talking Points-Rocket Fuel is made from common items -Stump Remover-Sugar(dextrose)The mixing procedure is done in house and takes approximately 4 hours per grain Housing , nozzle , and forward closure are made at the CSUF Machine shop-The combination of fuel and Nozzle dimensions yield a an exit Mach Number of 2.95Fuel Potassium Nitrate Dextrose8.6 lb fuel mass Total Impulse: 1,160.7 lb-sAverage Thrust: 590.8 lb. Specific Impulse: 134.6 sec Nozzle 304 Stainless steelCasing Aluminum 6061

Oxidizer fuel ratio (O/F) is 65/35 pertaining to 65% potassium nitrate and 35% dextrose. The propulsion will utilize the Bates system where each propellant grain is stacked on top of each other inside the motor casing. Each grain has a length of 5.0 inches, I.D .75, O.D 2.56, for a total of 6 grains (8.6 lbs total grain mass). The outer surface of each grain will be inhibited with lightweight cotton soaked with polyester styrene resin (fiberglass resin) and will form a single layer around each grain. This material is the most effective heat resistant inhibitor that will protect the outer surface of the grain from burning and protect the motor casing.The motor casing, made of 6061 T6 Aluminum with a length of approximately 35.2 and I.D2.75, O.D 2.95 will house the propellant grains. Similarly to an inhibitor it will contain a casing liner to provide thermal protection. The non-COTS solid rocket motor has a total impulse of 5,162.7 lb and a specific impulse of 134.6 seconds with an expected maximum chamber pressure of 1200 psi. The performance of the rocket candy motor classifies the designed motor as a level M motor. The process of casting propellant grain involves a 65/35 Kn/DX mixture totalling to 765 grams. The batch is mixed continuously in a student built mixing machine (consists of D.C motor and cement mixer) for 1hr per 100 gram batch. Ex. 200 grams of mixture, then you mix for 2 hours. Dump the mixture in a pot at a temperature of 210 degrees Fahrenheit. Mix the mixture and elevate the temperature for 5 minutes until mixture has turned viscous and pale white color. If mixture turns yellow then it is due to caramelization and high heating temperature. Pour the liquified mixture in the mould and with a plunger press down on the mixture to eliminate air bubbles and voids in the mixture. Allow the casting process for approximately 30 min to 1 hr.

Payload

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

-Payload is an atmospheric monitoring system -Consists of a linear actuator, airtight vial, rasberry 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 gas) levels throughout descent-GoPro will record video throughout flight-Real Time GPS Tracking through ( BRB GPS Transmitter) BRB=Big Red Bee#

Recovery System

Dual Deploymentlow drift/low impact3D PrintingHarness Material: KevlarHigh tensile strength (352,000 psi)Flame resistant (800-900F Decomp. Temp)Low stretch (4.1% Break Elongation)Mathematical Sewing PatternHemispherical Shape Adopted from recent SOYUZ TMA-18M spacecraft descent Ground Testing Parachute deployment: Successful

Descent profile:75ft/s then 30ft/s. Drift

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