University of south alabama mobile alabama frr
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University of South Alabama Mobile, Alabama FRR PowerPoint PPT Presentation


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University of South Alabama Mobile, Alabama FRR. Team Members Tim Morgan Alex Scruggs David Shaw Andy Mosley Joseph McCreary Nick Hall. Launch Vehicle General Dimensions. Length = 118.3 “ Diameter = 4” Mass = 13.5 oz. Launch Vehicle Components. Nose Cone Plastic 3.9 “ Diameter

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University of South Alabama Mobile, Alabama FRR

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University of South AlabamaMobile, AlabamaFRR

Team Members

Tim Morgan

Alex Scruggs

David Shaw

Andy Mosley

Joseph McCreary

Nick Hall


Launch Vehicle General Dimensions

  • Length = 118.3 “

  • Diameter = 4”

  • Mass = 13.5 oz.


Launch Vehicle Components

  • Nose Cone

    • Plastic

    • 3.9 “ Diameter

    • 16.75 “ Long


Launch Vehicle Components

  • Body Tube

    • Phenolic Tube

    • 4 “ Diameter

    • 101.64 “ Long


Launch Vehicle Components

  • Stabilizer Fins

    • G-10 Fiberglass

    • Thickness: .098 “

    • Root: 6”

    • Span: 6”

    • Sweep: 1.5”

    • Tip Cord: 3”


Launch Vehicle Components

  • Motor Mount and Retention

    • AeroPack

    • AeroPack Retention


Launch Vehicle Components

  • Motor

    • AeroTech

    • K270W

    • Max Thrust : 695 N

    • Avg. Thrust : 466 N


Simulated Flight Results

  • Max Velocity : 743.04 ft/s

  • Max. Acceleration: 390.76 ft/s^2

  • Max Altitude: 5448ft

  • Rail Velocity: approx. 47.25 ft/s

  • Range Drift: 17 ft (calm)


Stability

  • CP from nose: 89.99”

  • CG from nose: 99.87”

  • Stability Margin: 2.47

  • Thrust to Weight Ratio: 14.29/1


Vehicle Safety and Verification

  • Insured that all components are properly attached in their appropriate locations

  • Created pre-launch checklists to verify all components function properly

  • Tested scale rocket to ensure that all interrelated components function suitably

  • Test were conducted on January 9th


Recovery

  • Dual Deployment

  • Redundant Perfect Flight 15k Altimeters, 9V Power Supplies and Black Powder Deployment Charges


Recovery

  • Main Chute

    • 72 “ Conical with 14” spill hole

    • Decent Rate: approx. 20 ft/s

    • Deployment Altitude: 700 ft.

  • Drogue Chute

    • 18 “ Conical with 2.5” spill hole

    • Decent Rate: approx. 82 ft/s

    • Deployment Altitude: 5277 ft


Recovery System Safety Verification and Testing

  • Conducted test to ensure that the proper amount of black powder will be used

  • Conducted bench test to ensure the proper function of flight computers

  • Field Tested Perfect Flight Altimeters

  • Tests were conducted between December 7th through January 9th


Humidity/Temperature Probe Testing

  • Calibration Equations

  • Recorded Ambient Conditions and Probe Voltage Output Simultaneously

  • Applied Water Vapor to a Glass Vessel to simulate high humidity environments

  • Applied heat to the Glass Vessel to simulate high temperature environments


Full Scale Flight Test

  • Full Scale Rocket

  • Launched on AeroTech K700

  • Altitude: 6257’

  • Full Scale Scale Payload


Dual Deployment Avionics Test

  • Flight Tests Completed January 9th

  • Perfect Flight 15k Altimeter

  • Drogue deployed at 6044’ main at 400’


Ejection Charge Amount Test

  • Off Campus Test

  • Different Packing Methods Tried

  • Different Amounts of Black Powder Tried

  • Different Powder Types Tried

  • 3.5 grains of FFFF in a compressed cardboard tube is the best


Payload

Purpose: Collect Pressure, Temperature and Humidity Data

Implementation: Use G-Whiz HCX Flight Computer to record data from Vaisala HMP 50 Temperature/Humidity Probe


Payload InstrumentationVaisala HMP 50 Humidity and Temperature Probe

Cable colors.

1. Brown +VDC 7 to 28 VDC

2. White +0…. 1/2.5/5 V 0 to 100 %

3. Blue -VDC

4. Black 0... 1/2.5/5 V -40 to +60 °C

  • Accurate

  • 0-5 V Linear Output


Payload InstrumentationG-Whiz HCX Flight Computer P/N 09140

  • Barometric and Acceleration based altitude measuring

  • External Analog Data Storage (0-5 V)

  • Sample Rates up to 500 times per second


Payload Configuration


Integration Feasibility

  • Created to be Interchangeable

  • Integration is simple

  • Can be installed into rocket in 30 seconds


Payload Safety and Verification

  • Pack and Seal Payload Components Safely for Travel to Launch

  • Test All Onboard Batteries, Replace if Necessary

  • Check Ventilation Holes for Proper Air Flow

  • Test All Instrumentation and Onboard Computers Prelaunch

  • Determine That All Payload Wires are Connected Properly

  • Proper Packing and Placement of Parachutes

  • Ensure Chute Cords are Attached Properly and Securely

  • Payload Testing and Calibration Shall be Conducted Weekly from Dec 14-Jan4


Launch System


Outreach


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