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 alabama mobile alabama frr

University of South AlabamaMobile, AlabamaFRR

Team Members

Tim Morgan

Alex Scruggs

David Shaw

Andy Mosley

Joseph McCreary

Nick Hall


Launch vehicle general dimensions

Launch Vehicle General Dimensions

  • Length = 118.3 “

  • Diameter = 4”

  • Mass = 13.5 oz.


Launch vehicle components

Launch Vehicle Components

  • Nose Cone

    • Plastic

    • 3.9 “ Diameter

    • 16.75 “ Long


Launch vehicle components1

Launch Vehicle Components

  • Body Tube

    • Phenolic Tube

    • 4 “ Diameter

    • 101.64 “ Long


Launch vehicle components2

Launch Vehicle Components

  • Stabilizer Fins

    • G-10 Fiberglass

    • Thickness: .098 “

    • Root: 6”

    • Span: 6”

    • Sweep: 1.5”

    • Tip Cord: 3”


Launch vehicle components3

Launch Vehicle Components

  • Motor Mount and Retention

    • AeroPack

    • AeroPack Retention


Launch vehicle components4

Launch Vehicle Components

  • Motor

    • AeroTech

    • K270W

    • Max Thrust : 695 N

    • Avg. Thrust : 466 N


Simulated flight results

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

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

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

Recovery

  • Dual Deployment

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


Recovery1

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

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

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 Flight Test

  • Full Scale Rocket

  • Launched on AeroTech K700

  • Altitude: 6257’

  • Full Scale Scale Payload


Dual deployment avionics test

Dual Deployment Avionics Test

  • Flight Tests Completed January 9th

  • Perfect Flight 15k Altimeter

  • Drogue deployed at 6044’ main at 400’


Ejection charge amount test

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

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 instrumentation vaisala hmp 50 humidity and temperature 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 instrumentation g whiz hcx flight computer p n 09140

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

Payload Configuration


Integration feasibility

Integration Feasibility

  • Created to be Interchangeable

  • Integration is simple

  • Can be installed into rocket in 30 seconds


Payload safety and verification

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

Launch System


Outreach

Outreach


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