NU FRONTIERS Northeastern University Rover Deployment Experiment - - PowerPoint PPT Presentation

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NU FRONTIERS Northeastern University Rover Deployment Experiment - - PowerPoint PPT Presentation

Sep 18, 2023 96 likes •498 views

NU FRONTIERS Northeastern University Rover Deployment Experiment Agenda Overview of Vehicle Properties Stability Analysis Launch Vehicle Sections and Systems Booster Stage Interstage system Payload Recovery

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NU FRONTIERS

Northeastern University

Rover Deployment Experiment

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Agenda

  • Overview of Vehicle Properties
  • Stability Analysis
  • Launch Vehicle Sections and Systems

○ Booster Stage ○ Interstage system ○ Payload

  • Recovery

○ Drogues ○ Mains

  • Electronics
  • Rover
  • Subsystem Test
  • Updates

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Overview of Vehicle Properties

Length 148 inches Maximum Diameter 6.17 inches Weight 47.375 pounds Body Tube Material G12 Fiberglass Fins 4 Rectangular, G10 Fiberglass Motor Cesaroni L1115 Classic Reloadable Number of Avionics Bays 2 Number of Altimeters 6 Number of Main Parachutes 2 Number of Drogue Parachutes 1

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Stability and Ascent Analysis

  • Center of Gravity = 85.881 inches
  • Center of Pressure = 111 inches
  • Stability = 3.35 cal

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  • Thrust to weight: 5.3
  • Rail exit velocity: 70 ft/s
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Launch Vehicle Sections and Systems

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Nose Cone Section

  • Composed of Fiberglass with an Aluminum tip
  • Houses a 72 inch elliptical Main Parachute
  • Mass: 5.47 lbs

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Payload Section

  • Houses Upper Avionics Bay and Payload
  • Mass: 15.67 lbs with motor

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Lower Avionics Section

  • Houses Lower Avionics Bay, 1 Main and Drogue Parachute
  • Mass: 8.75 lbs

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Booster Section

  • 4 Trapezoidal Fins
  • Centering Rings

○ ¼” Plywood

  • Motor Mount

○ 75mm Blue Tube

  • Aero Pack Motor Retainer
  • Mass: 7.76 lbs

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Fin Properties

  • 4 G10 Fiberglass fins
  • Trapezoidal
  • Mounted through wall
  • Key slots in centering rings

○ Tabs on fins

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Motor Properties

Cesaroni L1115 Classic

Loaded Mass 4404.00 g Burnout Mass 1928.00 g Total Impulse 5015.00 Ns Maximum Thrust 1713.25 N Average Thrust 1119.00 N ISP 213.60 s Burntime 4.48 s

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Lower Avionics Bay Parachutes Subsystem Electronics

  • Components

○ 4 x StratoLogger Altimeter ○ 2 x Digikey Keylock Switches ○ 4 x 9 Volt Batteries ■ Held in custom 9V battery holders ○ 1 x XBEE Pro XSC (S3) GPS Unit

  • 3D Printed Housing

○ ABS 40% Infill ○ Threaded inserts to reinforce holes ○ Verified on subscale

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Upper Avionics Bay Parachutes Subsystem Electronics

  • Components

○ 2 x StratoLogger Altimeter ○ 1 x Digikey Keylock Switches ○ 2 x 9 Volt Batteries ■ Held in custom 9V battery holders

  • 3D Printed Housing

○ ABS 40% Infill ○ Threaded inserts to reinforce holes ○ Verified on subscale

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Test Plan and Procedures

  • Internal Design/Safety Review Board

○ Successful ground ejection tests ○ Wiring Continuity Audits ○ Simulation Audits ○ Detailed design review including full disassembly

  • Launch Day Checklists
  • Range Safety Officer Launch Vehicle Checks
  • Internal Post Launch Forms
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Payload

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Rover

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  • Vex motor locomotion
  • Custom designed wheels and body
  • “Fanning” solar panels
  • Solenoid latching system
  • Dynamic support strut
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Pneumatic Ejection System

  • CO2 ejection system connected to pneumatic components

○ CO2 cartridge ○ Regulator ○ Valve ○ Speed Controller

  • Polyester bellows clamped to bulkheads
  • Forward bulkhead slides freely along steel rods
  • Rear and pneumatic base bulkhead epoxied and set screwed, respectively
  • Electronics mounted below pneumatics
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SLIDE 18

Payload Electronics Bay

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  • Arduino Nano
  • 2x 7.4V 1000mAh LiPo
  • GY-521 Accelerometer and Gyroscope
  • Adafruit Ultimate GPS Breakout
  • Sunfounder PCA9685 Servo Driver
  • DS1307 Real Time Clock (RTC)
  • Custom designed PCB
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Recovery

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Drogues and Mains

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Parachute Subsystem

  • 42 inch drogue parachute

○ Octagonal Nylon, Sunward

  • Two 72 inch main parachutes

○ Classic Elliptical, Fruity Chutes

  • ⅜” -16 Eye Bolts with 1 ½” Washers
  • Swivels
  • ¼” Kevlar Shock Cord

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Launch Procedure and Separations

  • Apogee of 5302 ft
  • 3 Flight Events

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1st Flight Event

  • Launch Vehicle reaches an apogee of 5302 feet
  • The Booster and the Lower Avionics Sections separate, and 48 inch

drogue parachute is deployed

  • Launch Vehicle falls at 60.15 ft/s

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2nd Flight Event

  • Occurs at 800
  • The Nose Cone and the Payload Sections separate, and 72 inch main

parachute is deployed. Launch Vehicle still tethered.

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3rd Flight Event

  • Occurs at 775 or shortly after flight event 2
  • The Payload and the Lower Avionics Sections separate, and 72 inch main

parachute is deployed. Launch Vehicle separates into two independent sections.

  • Upper sections fall at 16.00 ft/s, Lower sections fall at 15.66 ft/s
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Shock Cord

  • ¼” Kevlar Shock Cord
  • Strong yet also slightly elastic
  • Attached to Eye Bolts
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Recovery System - Kinetic Energy

  • 75 ft-lb Landing Maximum Competition Requirement

○ All sections meet requirements

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Section Parachute Data (CD * A) Kinetic Energy (ft * lb) @ Apogee Kinetic Energy (ft * lb) @ Landing Nose-Cone Upper Main 307.41 21.75 Payload Upper Main 881.33 62.36 Main Avionics Bay Drogue + Lower Main 492.11 33.37 Payload Drogue + Lower Main 675.32 45.77

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Recovery System - Lateral Drift

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  • 2,500 foot Lateral Drift Maximum Competition Requirement

○ All sections meet requirement

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Wind Speed Maximum Lateral Drift of Two Independently Falling Sections No Wind 8 feet 5-mph 525 feet 10-mph 1,125 feet 15-mph 1,782 feet 20-mph 2,490 feet

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Electronics

Recovery, Motor, Nose Cone, and Accelerometer

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Recovery Electronics

Power 4 Volts to 16 Volts, nominal 9 Volt battery Current Consumption 1.5 milliamp Launch Detect 160 feet to 300 feet AGL, default 160 feet Main Deploy Altitude 100 feet AGL to 9,999 feet AGL Maximum Altitude 100,000 feet MS Altitude Resolution 1 feet up to 38,000 feet MSL < 2 feet to 52,000 feet MSL < 5 feet to 72,000 feet MSL Measurement Precision +/- (0.1% reading + 1 foot) typical Flight Data Logged Altitude, temperature, battery voltage Recording Time Per Flight Over 18 minutes Operational Temperature

  • 40°C to +85°C (-40°F to +185°F)

Sample Rate 20 samples per second Cost $54.95

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Payload Ejection System Electronics Bay

  • XBee Pro XSC (S3)
  • XBee Breakout Board
  • Antenna
  • 2x 1000mAh 7.4V LiPo
  • Arduino Nano V3
  • XBee Explorer Dongle (Ground Station)
  • MPU 6050
  • LIS 331

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Communication System

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Telemetry

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  • The Adafruit GPS Breakout Board gets position data → Arduino Nano V3
  • Arduino Nano V3 → XBee
  • XBee → XBee Explorer Dongle at Ground Station
  • Data stored and read out on Computer

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Data Flow

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Subscale Tests

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Subscale Design

  • Scaled down version of full scale airframe and recovery system
  • Approximately 2:3 Scale
  • Motor: J449
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Subscale Ground Ejection Tests

  • Coordinated with Northeastern University Campus Police
  • Secured pedestrian-free area prior to test
  • All successful, proof of ejection charge calculations
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Subscale Launch

  • December 16th, 2017
  • Maryland Delaware Rocketry Association

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Church Hill, MD

  • Temperature: -5°C Low, 7°C High
  • Weather: Scattered Clouds
  • Launch Angle: Approximately 5°

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Subscale Launch Results

  • All recovery systems performed as planned
  • Launch Vehicle Successfully recovered
  • Apogee: 2,313

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Thank you for listening!

QUESTIONS?

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