Piedmont Student Launch Team Piedmont Virginia Community College - - PowerPoint PPT Presentation

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Piedmont Student Launch Team Piedmont Virginia Community College - - PowerPoint PPT Presentation

Apr 17, 2023 359 likes •774 views

Piedmont Student Launch Team Piedmont Virginia Community College Presentation Team Branson Shane Andrew Oxford Jesse Oxford Hernandez DiMarco Requirements Team Lead & Launch Payload Manager PM Vehicle Lead Lead 2 Overview

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SLIDE 1

Piedmont Student Launch Team

Piedmont Virginia Community College

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SLIDE 2

Presentation Team

Jesse Oxford Team Lead & PM

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Andrew Oxford Requirements Manager Branson Hernandez Launch Vehicle Lead Shane DiMarco Payload Lead

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SLIDE 3

Overview

  • Launch Vehicle
  • Flight Statistics
  • Payload

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  • Test Plans
  • Project Plan

○ Requirements ○ Timeline

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SLIDE 4

Launch Vehicle Design

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SLIDE 5

Key Design Features

  • Custom Shaped Fins
  • Transition
  • Custom Rail Guides
  • Separates into Two Independent Sections

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SLIDE 6

General Dimensions

  • Landing Weight: 33.6 lb
  • Total Length: 112 in.

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  • Maximum Diameter: 8 in.
  • Fin Span: 18 in.
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SLIDE 7

Airframe Materials

Material Parts

G12 Fiberglass Airframe G10 Fiberglass Fins, Bulk plates ABS Nosecone/Payload Capsule Nylon Rail Guides Basswood Transition Aluminum Tailcone Motor Retainer

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SLIDE 8

Full Assembly

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SLIDE 9

Booster Section

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SLIDE 10

Fins

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SLIDE 11

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Launch Rail Guides

  • Custom Design
  • Through-the-Wall Style Mounting
  • Aerodynamic Shape
  • 3D Printed Nylon
  • Keyhole Slot
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SLIDE 12

Transition

  • 4 in. to 8 in. Diameter
  • Includes an 17 in. Long Coupler
  • Inner Structure Will Take the Majority
  • f the Flight Forces
  • Transition is Permanently Attached to

the Payload Bay

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SLIDE 13

Nosecone/Payload Bay

  • Rounded Shape to Prevent

Sticking in the Ground

  • Built into the Payload Capsule

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SLIDE 14

Parachutes

  • Booster Parachute

○ 84 in. Diameter ○ Recovery Harness Length: 12 ft

  • Payload Parachute

○ 48 in. Diameter ○ Recovery Harness Length: 6 ft

  • Coefficient of Drag: 2.2!
  • Ripstop Nylon
  • Nomex Blast Protector

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SLIDE 15

Recovery Electronics

  • RRC3 Sport Altimeter: 2
  • Jolly Logic Chute Release: 4
  • Black Powder Ejection Charges: 4

○ 2.3 g At Apogee ○ 3.0 g 1 s After Apogee ○ Two 3.6 g 2 s After Apogee

  • Eggfinder Mini Transmitter

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Jolly Logic Chute Release RRC3 Sport Altimeter

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SLIDE 16

Attachment

  • 1/2 in. Kevlar Recovery Harness
  • Swivels and Quick Links
  • Dual Attachment Points

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Quick Link U-Bolt Swivel

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SLIDE 17

Flight Statistics

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SLIDE 18

Model

  • Simulations Done in

RockSim and OpenRocket

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Rocket Statistic Value Launch Vehicle Mass (lb) 37.7 Payload Mass (lb) 6 CG Location (in.) 62.1 CP Location (in.) 83.94 Static Stability Margin 2.76 Coefficient of Drag 0.41

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SLIDE 19

Model - Motor

  • AeroTech L1420

○ Acquired from Previous Years

  • Thrust-to-Weight Ratio:

○ 7.3:1

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SLIDE 20

General Statistics

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Statistic Value Rail Exit Velocity (ft/s) 74.3 Stability Margin at Rail Exit 2.05 Apogee (ft) 5,049

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SLIDE 21

Drift

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5 mph 10 mph 15 mph 20 mph Booster Section Drift (ft) 324 648 972 1,296 Payload Section Drift (ft) 314 629 943 1,258

  • Worst Case Drift:

○ Apogee Parachute Deployment: ■ Booster Section: 10,908 ft ■ Payload Section: 9,071 ft

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SLIDE 22

Flight Stability

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  • Stable Above 2 calibers

throughout flight

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SLIDE 23

Velocity & Kinetic Energy - Landing

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Section Mass (oz) Velocity (ft/s) Kinetic Energy (ft-lbf) Payload 164 17.93 51.2 Booster 272 13.2 46.0

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SLIDE 24

Subscale

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SLIDE 25

Details

  • 1:2 Scale
  • High Power, launched on an Aerotech H135W
  • Dual recovery
  • 1,575 ft apogee

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SLIDE 26

Payload

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SLIDE 27

UAV

  • Quadcopter Design
  • Remotely Piloted
  • Housed within a Capsule
  • 8.25 in. Long x 6.75 in. Wide 2.81
  • in. Tall

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SLIDE 28

UAV Electronics

  • All-in-one Flight Controller
  • 21 A 32-bit Bl-Heli ESCs
  • 200 mW Video Transmitter
  • FrSky 16-channel Radio receiver
  • 1080P FPV Camera

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SLIDE 29

UAV Propulsion

  • 1,400 mAh 4S LiPo battery
  • 2,200 KV Motors
  • 5 in. Folding Tri-blade Propellers

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SLIDE 30

Deployment System - Overview

  • The UAV is Housed in a Capsule
  • The Dual Bay Doors Act as a Righting

Mechanism

  • The Nosecone is Integrated into the

Capsule

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SLIDE 31

Deployment System - Ejection

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Estimated 0.14 g Black Powder Charge

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SLIDE 32

Deployment System - Opening/Righting

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SLIDE 33

Launch Vehicle Interfaces

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  • 6 #4-40 Shear Pins
  • Acts as the Nosecone
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SLIDE 34

Ground System Interfaces

  • Acts as GPS Tracker for the Payload

Section

  • 915 MHz, 100 mW Transceiver
  • FrSky X-lite radio controller
  • 5.8GHz 150 channel receiver(FPV video

receiver)

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SLIDE 35

Test Plans

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SLIDE 36

Key Tests

  • Ejection Tests
  • Battery Life

○ Avionics ○ Payload

  • UAV Range

○ Flight ○ Transmitter

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SLIDE 37

Project Plan

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SLIDE 38

Requirements Status

  • Requirements Reviews Have

Been Done

  • Remaining Verification Through

Testing and Flights

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SLIDE 39

Timeline Changes and FRR

  • Subscale Flight
  • Full-Scale Flight

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SLIDE 40

Thank You

Questions?