Auburn University USLI. FRR Presentation

Transcription

1 Auburn University USLI FRR Presentation

2 Airframe Jonathan Leonhardt

3 Vehicle Dimensions Total Length of inches Inner Diameter of 5 inches Outer Diameter of 5.5 inches Estimated mass of 31.3 ounces

4 Clipped Delta Easy to manufacture Proven design Performs well during sub sonic flight

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9 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

10 Braided Tubes Body tube support structure Motor tube structure Manufactured at Auburn University

11 Stability Margin Static stability margin of 2.32 Calibers CG is inches from nose cone CP is inches from nose cone

12 Section Mass (lb) Percentage Structure % Recovery % Grid Fins % Electronics % Motor % Ballast Total %

13 Motor Selection Motor has been changed to Loki L-1482

14 Predictions with Loki L Simulated altitude of 5367 feet (AGL) Thrust to weight ratio is 11:1 Provides rail exit velocity 44.3 ft/s

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16 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 Average Thrust 339 lbs 340 lbs Maximum Thrust 407 lbs 382 lbs Burn Time 2.6 s 2.49 s

17 Requirements Verification Summary (Launch Vehicle) Subscale launch and successful recovery Completed Full scale launch and successful recovery Incomplete

18 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 2 nd, 2016

19 Recovery Adam Wolinski

20 Recovery Overview

21 Parachutes Three parachutes required Drogue Circular inches Payload Main Hemispherical inches Booster Main Hemispherical inches Both mains will have a spill hole

22 Parachutes Construction Gores Ripstop nylon Tear resistant weaving

23 Parachutes Payload Main deployed with Tender Descender by Tinder Rocketry

24 Attachment Hardware Nylon Slotted Pan Head Machine Screws Steel U-Bolts Quick Links

25 Shock Cord 1 inch tubular nylon Excellent tensile strength Low weight The Auburn team has worked with this material before

26 Electronics Altimeters Two Altimeters Altus Metrum Telemega Altus Metrum Telemetrum Taoglas FXP MHz ISM Antenna

27 CO 2 Ejection System Increased Safety Better reliability at higher altitudes Lowered risk of equipment and parachute damage

28 CO 2 Ejection System Redesigned Auburn s Custom System Three 12g cartridges for redundancy

29 Payload Fairing Lindsey Batte

30 PLF Final Design Overview Purpose: Deploy Drogue/Main Parachute Design Elliptical Design 13 Inches Tall in. Wall Thickness 1 8

31 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

32 Shear Bracket

33 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

34 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

35 PLF Design Evolution PLF Version 1 4 Horizontal 10-lb sheer pins Inner seal only 0.3 grams of black powder PLF Version lb vertical sheer pins Inner seal 0.5-in outer seal 0.3 grams of black powder PLF Version 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

36 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

37 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.

38 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.

39 PLF Testing: Full Scale Testing Test: Aquila II and Aquila IV Test Article: PLF v.1, PLF v.3 Results: Motor CATO Conclusion None

40 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

41 Aerodynamic Analysis Payload Gabriel Smith

42 Overview Mission: To collect data on aerodynamic protuberances Secondary mission: Assist the rocket to the one mile height requirement through aerodynamic braking

43 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 Mass Diameter (inner/outer) 8.85 in lb. 5/5.125 in

44 WAFLE Deployment

45 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 Span Height 5.91 in 2 in 0.77 in

46 Arduino Arduino Uno will control the WAFLE subsystems Control calculations and predict height of the rocket through acceleration input. Operating/ Analog I/O Digital I/O Input Voltage (V) 5 / / 0 14 / 6

47 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) x 2 x

48 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 Acceration Altitude Voltage (V) Tolerance (g) Tolerance (ft) 3-5 ± 16 ± 3

49 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 MHz

50 Outer fairing Aerodynamic fairing that reduces aerodynamic loading on servos and grid fin base. Made from filament wound carbon fiber. Fairing Span Fairing Length Fairing Height 2 in 4.1 in 1 in

51 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

52 Simulation Results Variable Drag Estimate of Fins (at Max Velocity, 45 degrees) Drag Estimate of Fins (at Max Velocity, 90 degrees) Drag Estimate of Rocket (at Max Velocity) Drag Estimate of Rocket and Fins (at Max Velocity, 45 degrees) Drag Estimate of Rocket and Fins (at Max Velocity, 90 degrees) Max Acceleration (at Max Velocity with Fins, 45 degrees) Max Acceleration (at Max Velocity with Fins, 90 degrees) Value lbf lbf lbf lbf lbf ft/s^ ft/s^2

53 Safety Austin Phillips

54 Educational Outreach Noel Cervantes

55 Project Overview Cassandra Seelbach

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