Auburn University Student Launch PDR Presentation November 16, 2015
Project Aquila
Vehicle Dimensions Total Length of 69.125 inches Inner Diameter of 5 inches Outer Diameter of 5.25 inches Estimated mass of 384 ounces
Clipped Delta Fins Easy to manufacture Proven design Performs well during subsonic flight
Material Selection Carbon Fiber High strength to weight Basalt High temperature resistance HIPS 3D printed plastic Ease of manufacturing 3D braided carbon fiber Lighter than a solid carbon fiber structure
Stability Margin Static stability margin of 2.27 Calibers CG is 42.2 inches from nose cone CP is 54.1 inches from nose cone
Motor Selection Initial motor selection is an Aerotech L1520T Team has had past success with Aerotech motors Vendor availability, ordered and reserved
Predictions with Aerotech L1520T Simulated altitude of 5861 feet (AGL) Mass increase of 25% has apogee of 5522 feet (AGL) Thrust to weight ratio is 14:1 Provides rail exit velocity 54 ft/s
AeroTech L1520 Thrust Curve
Testing Plan 3:5 Subscale Materials Testing Wind Tunnel Testing
Subscale Test Plans 3:5 scale 12 lbs AeroTech K715G Apogee of 5386 feet
Materials Testing Compression and Tension testing Three point bend testing Load cell testing
Wind Tunnel Testing To determine expected drag forces.
Recovery Overview
Parachutes Three parachutes required Drogue Circular 23 inches Payload Main - Hemispherical Booster Main Hemispherical Payload Main will have a spill hole
Parachutes Construction Gores Ripstop nylon Tear resistant weaving
Parachutes Payload Main deployed with Tender Descender by Tinder Rocketry
Attachment Hardware Nylon Slotted Pan Head Machine Screws Steel U-Bolts Quick Links
Shock Cord 1 inch tubular nylon Excellent tensile strength Low weight The Auburn team has worked with this material before
Electronics Altimeters Two Altimeters Altus Metrum Telemega Altus Metrum Telemetrum Patch Antennae
CO 2 Ejection System Increased Safety Better reliability at higher altitudes Less risk of equipment and parachute damage
CO 2 Ejection System Redesigned Auburn s Custom System Three 12g cartridges for redundancy Cartridges punctured by magnet driven solenoid Explosive free system
CO 2 Ejection System - Electronics Custom built altimeter driven circuit Altimeters trigger a capacitor in parallel with 24V power supply
PLF Design Overview Purpose: Deploy Drogue/Main Parachute Design Elliptical Design 9 Inches Tall 1 8 in. Wall Thickness
PLF Component Overview Pin Connectors (A): Prevent premature separation during flight Charge Bay (B): Contains black powder charge that will induce separation
PLF Component Overview Retaining Clips (A): Secures the fairings to the main body pre-deployment Breaks when separation is induced PLF Tether Lines (B): Secures each individual fairing to the rocket postdeployment
PLF Testing: Subscale Test: 3/5 Subscale Launch Test Article: Subscale Nose Cone Reason: Ensure the Aerodynamic Properties of the fairing meet expectations
PLF Testing: 3-Point Bending Test: Basic Three-Point Bending Test Test Article: Retaining Clips Reason: Determine which material would result in the best performance for the Retaining Clips
PLF Testing: Subscale Test: Charge Deployment Test Article: Charge Bay/Fairing System Reason: Determine the amount of black powder needed to separate the PLF while preventing structural damage to the system or the payload
PLF Testing: Drag Strip Deployment Test: Test PLF deployment at varying speeds that mimic different stages of flight. Test Article: Entire PLF System Reason: Ensure that the PLF will deploy successfully at/near apogee conditions Simulate late deployment Simulate premature deployment
Overview Primary Mission: To collect data on aerodynamic protuberances Secondary mission: Assist the rocket to the one mile height requirement through aerodynamic braking
Wall Armed Fin-Lattice Elevator (WAFLE) The WAFLE is the optimal system designed to accomplish both missions Subsystems: Arduino Servos Accelerometer GPS Outer Fairing Grid fins
WAFLE Overview
WAFLE Deployment
Subsystem Integration
Grid Fin The grid fin is the subsystem that all aerodynamic analysis will be performed on. Grid fin will act as a drag control surface 3D manufactured with HIPS
Grid Fin Dimensions
Arduino Arduino Uno will control the WAFLE subsystems Control calculations and predict height of the rocket through acceleration input.
Servos HS-5685MH Servo will control the actuation of the grid fin. Precise angles under a flight loads can be achieved with this servo. Located on the exterior of the airframe, under the external fairing
Servo Dimensions
Accelerometer ADXL335 Triple-axis Accelerometer will perform the data collection of the acceleration of the rocket and relay to the Arduino Uno.
Outer Fairing Aerodynamic fairing that reduces aerodynamic loading on servos and grid fin base. Made from filament wound carbon fiber.
WAFLE Timeline
Planned Test and Simulations Simulations Computational Fluid Dynamics (CFD) SolidWorks Flow Fortran- Flight and Dynamic model Drag Profile Test Aerodynamic Load Testing Vortex Shedding Testing
Safety Safety Officer: Matthew Austin Phillips Credentials: State Certified Firefighter, Nationally Certified EMT, Hazmat A/O, Level 2 Amateur Rocketeer
Safety Updates Safety briefing and team safety documentation Tool and test equipment verified before use Safety check-offs Testing Construction Flight OSHA certification class for all team members: Spring 2016 New safety equipment in lab Fire extinguisher training for all team members: Fall 2015 Safety documentation links on website
Outreach Events Auburn Junior High School Engineering Day- October 19, 2015 Drake Middle School 7 th Grade Rocket Week Auburn Junior High 9 th Grade Rocket Team Samuel Ginn College Engineering Day Boy Scouts of America: Space Exploration Badge Girl Scouts of America: Space Badge Rocket Day
Project Updates Timeline Budget Funding