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Auburn University USLIFRR Presentation
AirframeJonathan Leonhardt
Vehicle Dimensions• Total Length of 75.125 inches• Inner Diameter of 5 inches• Outer Diameter of 5.5 inches• Estimated mass of 31.3 ounces
Clipped Delta• Easy to manufacture• Proven design• Performs well during sub sonic flight
Material selection• Carbon Fiber▫ High strength to weight
• HIPS 3D printed plastic▫ Ease of manufacturing
• Braided carbon fiber▫ Lighter than a solid carbon fiber structure
Braided Tubes• Body tube support structure• Motor tube structure• Manufactured at Auburn University
Stability Margin• Static stability margin of 2.32 Calibers• CG is 43.25 inches from nose cone• CP is 57.16 inches from nose cone
Section Mass (lb) Percentage
Structure 10.8 34.5%
Recovery 4.51 14.4%
Grid Fins 3.00 9.58%
Electronics 1.52 4.85%
Motor 7.90 25.24%
Ballast 5.00 15.97
Total 31.3 100%
Motor Selection• Motor has been changed to Loki L-1482
Predictions with Loki L - 1482• Simulated altitude of 5367 feet (AGL)• Thrust to weight ratio is 11:1• Provides rail exit velocity 44.3 ft/s
Motor Specifications
Manufacturer Loki Aerotech
Motor Designation L1482 L1520T
Diameter 2.95 in 2.95 in
Length 19.6 in 20.9 in
Impulse 3882 N-s 3769
Total Motor Weight 7.78 lbs 8 lbs
Propellant Weight 4.05 lbs 3.925
Average Thrust 339 lbs 340 lbs
Maximum Thrust 407 lbs 382 lbs
Burn Time 2.6 s 2.49 s
Requirements Verification Summary(Launch Vehicle)
• Subscale launch and successful recovery –Completed
• Full scale launch and successful recovery –Incomplete
Full Scale Flight Tests• Flight 1 : Failure (Altitude and recovery failure)• Flight 2 : Failure (Motor CATO)• Flight 3 : Failure (PLF Failure)• Flight 4 : Failure (Motor CATO)• Flight 5 : Launch April 2nd , 2016
RecoveryAdam Wolinski
Recovery Overview
Parachutes• Three parachutes required▫ Drogue – Circular – 22.11 inches▫ Payload Main – Hemispherical – 52.56 inches▫ Booster Main – Hemispherical – 39.84 inches
• Both mains will have a spill hole
Parachutes• Construction▫ Gores
• Ripstop nylon▫ Tear resistant weaving
ParachutesPayload 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
• Taoglas FXP240 433 MHz ISM Antenna
CO2 Ejection System• Increased Safety• Better reliability at higher altitudes• Lowered risk of equipment and parachute damage
CO2 Ejection System• Redesigned Auburn’s Custom System• Three 12g cartridges for redundancy
Payload FairingLindsey Batte
PLF Final Design Overview• Purpose: ▫ Deploy Drogue/Main
Parachute• Design▫ Elliptical Design▫ 13 Inches Tall
▫ 18
in. Wall Thickness
PLF Component Overview• Vertical Sheer Pin Brackets
(Next Slide): ▫ Prevent premature separation
during flight ▫ Holds 4 vertical sheer pins
• Charge Bay:▫ Contains black powder charge
that will induce separation ▫ Location chosen to produce
largest moment▫ Lined with Fiberglass
• Ribs ▫ Ensure structural integrity of
the fairings▫ Aerodynamic Seal:
▫ Paraffin wax seal along all seams
Shear Bracket
PLF: Partial Deployment• Side A: ▫ Lip (inner/outer) Configuration on next slide
▫ Plugged half of the Charge Bay
• Side B:▫ Recessed▫ Open half of the Charge Bay▫ Outer Lip Contoured▫ Wax Seal
PLF Design Changes• Inner Lip (0.25 in) ~
Unchanged• Outer Lip (0.5) ~ Doubled • 4 Shear Brackets ~ +2• Kevlar Charge Chamber • 0.4 grams of BP ~ +0.1 grams• Wax to make the PLF air tight
PLF Design EvolutionPLF Version 1• 4 Horizontal
10-lb sheer pins
• Inner seal only
• 0.3 grams of black powder
PLF Version 2• 2 10-lb
vertical sheer pins
• Inner seal• 0.5-in outer
seal • 0.3 grams of
black powder
• 2 10-lb vertical sheer pins
• 2 25-lb vertical sheet pins
• Inner seal
• 1.0-in outer seal
• Paraffin wax seal on all seams
• 0.4 grams of black powder
PLF Version 3
PLF Testing: Charge Bay Strength Test• Test Article: ▫ Charge Bay
• Reason:▫ Determine the “Breaking
point” of the charge chamber structure
▫ Conclusion:▫ The charge bay will not be
damaged even when filled to capacity
PLF Testing: Ground Testing• Test Articles:
▫ PLF v.1, PLF v.2, PLF v.3• Reason:
▫ Ensure that the charge will effectively separate the fairing halves.
▫ Conclusion▫ Each version of the PLF
was able to successfully deploy on the ground.
PLF Testing: Full Scale Testing• Test: Aquila I• Test Article:
▫ Static Full-Scale nose cone
• Results:▫ The rocket remained
stable throughout the flight
▫ Conclusion▫ The aerodynamic design
of the PLF performs well in transonic conditions.
PLF Testing: Full Scale Testing• Test: Aquila II and
Aquila IV• Test Article: ▫ PLF v.1, PLF v.3
• Results:▫ Motor CATO
▫ Conclusion▫ None
PLF Testing: Full Scale Testing• Test: Aquila III• Test Article:
▫ PLF v.2• Results:
▫ PLF deployed prematurely at Mach 0.6.
▫ Conclusion▫ Air broke through the
outer/inner seals at the stagnation point forcing the fairings to deploy.
▫ Need better aerodynamic seal
Aerodynamic Analysis Payload Gabriel Smith
OverviewMission:• 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:• Grid fins• Arduino• Servos• 10-DOF IMU• RF Tracker• Outer Fairing
Height 8.85 in
Mass 2.5275 lb.
Diameter (inner/outer) 5/5.125 in
WAFLE Deployment
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
Length 5.91 in
Span 2 in
Height 0.77 in
Arduino• Arduino Uno will control the
WAFLE subsystems• Control calculations and
predict height of the rocket through acceleration input.
Operating/ Input Voltage
(V)
Analog I/O Digital I/O
5 / 7-12 6 / 0 14 / 6
Servos• Savox SV-1270TG 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
Torque
(kg/cm)Size (cm) Weight (g)
35.07 4.0 x 2 x 3.7 56
10-DOF IMU• 10 DOF IMU Breakout records
acceleration and rotation in the x,y,and z axis as well as barometric pressure and temperature.
• Primary sensor for the WAFLE sensor
Operating Voltage (V)
AccerationTolerance (g)
Altitude Tolerance (ft)
3 - 5 ± 16 ± 3
RF Tracker• RC-HP Transmitter will act as
the tracking for the WAFLE system and the booster section.
• A CR2032 battery with a life span of 1 week
• Transmitting frequency of 222.450 MHz
Outer fairing• Aerodynamic fairing that
reduces aerodynamic loading on servos and grid fin base.
• Made from filament wound carbon fiber.
Fairing Span 2 in
Fairing Length 4.1 in
Fairing Height 1 in
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▫ 1:5 Scale Test▫ 3:5 Scale Test ▫ Full Scale Test
Simulation ResultsVariable Value
Drag Estimate of Fins (at Max Velocity, 45 degrees)
53.16 lbf
Drag Estimate of Fins(at Max Velocity, 90 degrees)
13.45 lbf
Drag Estimate of Rocket (at Max Velocity)
96.94 lbf
Drag Estimate of Rocket and Fins (at Max Velocity, 45 degrees)
150.11 lbf
Drag Estimate of Rocket and Fins (at Max Velocity, 90 degrees)
110.39 lbf
Max Acceleration (at Max Velocity with Fins, 45
degrees)-185.19 ft/s^2
Max Acceleration (at Max Velocity with Fins, 90
degrees)-136.19 ft/s^2
SafetyAustin Phillips
Educational OutreachNoel Cervantes
Project OverviewCassandra Seelbach
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