Critical Design Review UNIVERSITY OF SOUTH ALABAMA CONNER DENTON, - - PowerPoint PPT Presentation

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Feb 10, 2023 11 likes •151 views

Critical Design Review UNIVERSITY OF SOUTH ALABAMA CONNER DENTON, JOHN FAULK, NGHIA HUYNH, KENT LINO, PHILLIP RUSCHMYER, & ANDREW TINDELL MENTOR : RICHARD KRAMER Final Launch Vehicle Parameters Overall Vehicle Parameters Rocket height:

SLIDE 1

Critical Design Review

UNIVERSITY OF SOUTH ALABAMA CONNER DENTON, JOHN FAULK, NGHIA HUYNH, KENT LINO, PHILLIP RUSCHMYER, & ANDREW TINDELL MENTOR : RICHARD KRAMER

SLIDE 2

Final Launch Vehicle Parameters

 Overall Vehicle Parameters

Rocket height: 94 inches Body diameter: 4 inches Wall thickness: 1/16 inch  Nosecone: Ogive  Fin design: Straight Tapered

SLIDE 3

Key Design Features

 Hazard Detection Camera



capable of spotting hazardous areas through point of view analysis

 Turbine Energy Conversion



n board turbine generator capable of converting energy sufficient for on

board electronics

SLIDE 4

Final Rocket Motor

 AeroTech K550W-18 “White Lightning”  Total Impulse: 346 lb-s  Pre Burn Mass: 3.27 lb  Post Burn Weight: 1.32 lb

SLIDE 5

Rocket Flight Stability

 Flight Stability: 3.6 cal  CP (Simulated): 74.464 inches from nose  CG (Experimental): 60.054 inches from nose

SLIDE 6

Thrust to Weight Ratio

 Thrust to Weight Ratio: 6.15

 Thrust: 396.8 N  Weight: 232 oz. -> 6.577 kg -> 64.52 N

SLIDE 7

Mass Statement & Margin

SLIDE 8

Recovery Parameters

 Drogue Parachute Size: 12 inches  Main Parachute Size: 72 inches  Calculated descent Velocity of Main Parachute: 22.07 ft/s

SLIDE 9

Kinetic Energy Calculations

Phases Nosecone P.A.P Bay Booster Bay Take-off 13.36 ft-lbf 173.62 ft-lbf 252.37 ft-lbf Deployment 117.34 ft-lbf 1525.13 ft-lbf 2216.34 ft-lbf Landing 2.79 ft-lbf 36.26 ft-lbf 52.71 ft-lbf

SLIDE 10

Predicted Drift from Launch Pad

 5mph – 265.82 ft.  10mph – 531.64 ft.  15mph – 797.46 ft.  20mph – 1063.28 ft.

SLIDE 11

Final Payload Design Overview

 Hazard Detection Camera

capable of spotting hazardous areas through point of view analysis

 Turbine Energy Conversion

n board turbine generator capable of converting energy sufficient for
n board electronics

 Aerodynamic Air Scoop System

efficiently control wind path to pass through turbine generator

SLIDE 12

Payload Integration

 Hazard Detection Attachment Scheme  Main Parachute (A): Deploy at approximately 800ft to reduce

drifting distance

 Nosecone (B): Will deploy with main parachute  P.A.P. Bay (C): Houses hazard detection camera, altimeter, and

parachute until apogee

 Booster Bay (D): Houses shock cord, motor, and turbine generation

payload

 Hazard Detection Camera (F): End cap attached to P.A.P. bay

which will allow for unobstructed view of hazard scanning upon descent

SLIDE 13

Interfaces

 Stratologger #1: Will deploy both main designated altitude and drogue at

apogee

 Stratologger #2: Designated as scoring competition altimeter  PixyCam: Hazard detection payload capable of determining position

away from descending vehicle

 Turbine Generator: Generates and logs the amount of current produced

in order to prove that it can be used it further projects to power on board electronics

SLIDE 14

Test Plan

 Altimeters

 Pressure change in a controlled volume environment

 PixyCam

 Ground surveillance calibration

 Subscale Wind Turbine

 Air nozzle  Voltmeter