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

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 ● Launch Vehicle ● Test Plans ● Flight Statistics ● Project Plan ○ Requirements ○ Timeline ● Payload 3

Launch Vehicle Design 4

Key Design Features ● Custom Shaped Fins ● Transition ● Custom Rail Guides ● Separates into Two Independent Sections 5

General Dimensions ● Maximum Diameter: 8 in. ● Landing Weight: 33.6 lb ● Fin Span: 18 in. ● Total Length: 112 in. 6

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 7

Full Assembly 8

Booster Section 9

Fins 10

Launch Rail Guides ● Custom Design ● Through-the-Wall Style Mounting ● Aerodynamic Shape ● 3D Printed Nylon ● Keyhole Slot 11

Transition ● 4 in. to 8 in. Diameter ● Includes an 17 in. Long Coupler ● Inner Structure Will Take the Majority of the Flight Forces ● Transition is Permanently Attached to the Payload Bay 12

Nosecone/Payload Bay ● Rounded Shape to Prevent Sticking in the Ground ● Built into the Payload Capsule 13

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 14

Recovery Electronics ● RRC3 Sport Altimeter: 2 ● Jolly Logic Chute Release: 4 Jolly Logic Chute Release ● 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 RRC3 Sport Altimeter 15

Attachment ● 1/2 in. Kevlar Recovery Harness ● Swivels and Quick Links Quick Link ● Dual Attachment Points Swivel U-Bolt 16

Flight Statistics 17

Model Rocket Statistic Value Launch Vehicle Mass (lb) 37.7 ● Simulations Done in Payload Mass (lb) 6 RockSim and OpenRocket CG Location (in.) 62.1 CP Location (in.) 83.94 Static Stability Margin 2.76 Coefficient of Drag 0.41 18

Model - Motor ● AeroTech L1420 ○ Acquired from Previous Years ● Thrust-to-Weight Ratio: ○ 7.3:1 19

General Statistics Statistic Value Rail Exit Velocity (ft/s) 74.3 Stability Margin at Rail 2.05 Exit Apogee (ft) 5,049 20

Drift 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 21

Flight Stability ● Stable Above 2 calibers throughout flight 22

Velocity & Kinetic Energy - Landing Section Mass (oz) Velocity (ft/s) Kinetic Energy (ft-lbf) Payload 164 17.93 51.2 Booster 272 13.2 46.0 23

Subscale 24

Details • 1:2 Scale • High Power, launched on an Aerotech H135W • Dual recovery • 1,575 ft apogee 25

Payload 26

UAV ● Quadcopter Design ● Remotely Piloted ● Housed within a Capsule ● 8.25 in. Long x 6.75 in. Wide 2.81 in. Tall 27

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 28

UAV Propulsion • 1,400 mAh 4S LiPo battery • 2,200 KV Motors • 5 in. Folding Tri-blade Propellers 29

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 30

Deployment System - Ejection Estimated 0.14 g Black Powder Charge 31

Deployment System - Opening/Righting 32

Launch Vehicle Interfaces ● 6 #4-40 Shear Pins ● Acts as the Nosecone 33

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) 34

Test Plans 35

Key Tests ● Ejection Tests ● Battery Life ○ Avionics ○ Payload ● UAV Range ○ Flight ○ Transmitter 36

Project Plan 37

Requirements Status ● Requirements Reviews Have Been Done ● Remaining Verification Through Testing and Flights 38

Timeline Changes and FRR ● Subscale Flight ● Full-Scale Flight 39

Thank You Questions?