NASA SL - NU FRONTIERS PDR presentation to the NASA Student Launch - - PowerPoint PPT Presentation

▶
nasa sl nu frontiers
SMART_READER_LITE
LIVE PREVIEW

NASA SL - NU FRONTIERS PDR presentation to the NASA Student Launch - - PowerPoint PPT Presentation

Dec 28, 2023 168 likes •474 views

NASA SL - NU FRONTIERS PDR presentation to the NASA Student Launch Review Panel 1 Agenda Launch Vehicle Overview Requirement Compliance Plan Nose Cone Section STEM Outreach Payload Section Questions Lower

slide-1
SLIDE 1

NASA SL - NU FRONTIERS

PDR presentation to the NASA Student Launch Review Panel

1

slide-2
SLIDE 2

Agenda

  • Launch Vehicle Overview
  • Nose Cone Section
  • Payload Section
  • Lower Avionic Bay Section
  • Booster Section
  • Motor Selection
  • Acent Analysis
  • Launch Procedure and Separations
  • Recovery System
  • Payload Mechanical
  • Payload Electronics
  • Deployment Protocol

2

  • Requirement Compliance Plan
  • STEM Outreach
  • Questions
slide-3
SLIDE 3

Launch Vehicle Overview

  • Materials

○ Airframe, Nosecone and Coupler - G12 Fiberglass (Madcow Rocketry) ○ Fins - G10 Fiberglass ○ Centering Rings and Bulkheads - Birch Plywood

  • Length - 149 inches
  • Mass - 20.1 kg

3

slide-4
SLIDE 4

Launch Vehicle Overview

4

slide-5
SLIDE 5

Launch Vehicle Overview - Material Alternatives

  • Fiberglass

○ Pros: Strength, durability ○ Cons: Heavy, toxic

  • Carbon Fiber

○ Pros: Strength, durability ○ Cons: Heavy, toxic, expensive

  • Blue Tube (Galvanized Cardboard)

○ Pros: Light, cheap ○ Cons: Low strength, susceptible to environment

5

slide-6
SLIDE 6

Nose Cone Section: Dimensions and Materials

  • Shape: 5:1 Ogive (~30 inches long)
  • Materials: G12 Fiberglass
  • Weight: 2.3 pounds

6

slide-7
SLIDE 7

Nose Cone Section: Avionics Bay and Parachute

  • Nose Cone Avionics Bay

○ Two Perfectflite Stratologgers ○ One XBEE Pro XSC (S3) GPS Unit ○ Powered by 9V Duracell Batteries

  • At 800 feet, ignites separation charge and falls independently on 48 inch

nylon parachute

○ Attached with kevlar cord ○ ¼”-20 eyebolt mount

7

slide-8
SLIDE 8

Payload Section

8

slide-9
SLIDE 9

Payload Section - Dimensions

9

slide-10
SLIDE 10

Lowe Avionics Bay Section

  • Contains

○ Lower Avionics Bay ○ Drogue Parachute ○ Lower Sections Main Parachute

10

slide-11
SLIDE 11

Lowe Avionics Bay Section - Dimensions

11

slide-12
SLIDE 12

Booster Section

  • Includes

○ Motor ○ Fins

12

slide-13
SLIDE 13

Booster Section- Dimensions

13

slide-14
SLIDE 14

Motor Selection - L1395-BS

  • Projected Apogee: 5,370 feet
  • Total Impulse: 4,874.96 N-s
  • Thrust to Weight: 7.08

14

slide-15
SLIDE 15

Motor Selection - Alternatives

15

Motor Burn Time (s) Max Acceleration (Gs) Apogee (ft) Total Impulse (N*s) Mass with Fuel (g) Mass without Fuel (g) L1395-B S-P 3.34 7.69 5370 4895 4323 1848 L2375- WT-P 2.07 12.2 5446 4905 4161 1840 L1115-P 4.47 7.32 5519 5017 4404 2010 L1350-C S 6.95 3.17 4655 4280 3571 1546

slide-16
SLIDE 16

Ascent Analysis

16

CP: 112 inches from tip of nose cone CG: 93.816 inches from tip of nose cone Exit velocity off 144 inch Rail: 74 feet/s Thrust to Weight (L1396-BS Motor): 7.08

slide-17
SLIDE 17

Launch Procedure and Separations

17

slide-18
SLIDE 18

Recovery System - Avionics Bays

  • Nose Cone Avionics Bay

○ 3D Printed ABS Fixture ○ Deploys 48” Main Nose Cone Section Nylon Parachute at 800 feet ○ Two Perfectflite Stratologger Altimeters ○ One XBEE Pro XSC (S3) GPS Unit ○ Powered by 9 Volt Duracell Batteries

18

slide-19
SLIDE 19

Recovery System - Parachutes

19

Parachute CD A(in2) Manufacturer 48” Nylon Parachute 0.8 1564.4 Sunward Group Ltd 72” Iris Ultra Light Parachute 2.2 6840 Fruity Chutes

Fruity Chutes Iris Ultra Light Parachute

slide-20
SLIDE 20

Recovery System - Kinetic Energy

75 ft-lb Maximum Competition Requirement

20

Section Mass Total (lb) Parachute Data (CD * A) Kinetic Energy (ft * lb) Nose-Cone 5.63 Nose Cone Main 26.299 Main Avionics Bay 5.29 Drogue + Booster Main 50.644 Booster Section 8.01 Drogue + Booster Main 74.911 Payload 12.8 Drogue + Booster Main 76.23

slide-21
SLIDE 21

Recovery System - Lateral Drift

2,500 foot Lateral Drift Maximum Competition Requirement

21

Wind Speed Nose Cone Section Payload/ Lower Avionics/ Booster Sections No Wind 8 feet 8 feet 5-mph 523 feet 486 feet 10-mph 1,137 feet 1,067 feet 15-mph 1,782 feet 1,660 feet 20-mph 2,575 feet 2,421 feet Launch Vehicle Drift Calculations Using OpenRocket Simulation Software, 10 Simulation Average

slide-22
SLIDE 22

Payload Mechanics

22

  • Self-righting design
  • 6” Pneumatic tires
  • Solar panel fan

○ Opened by servo motor

  • Deployable counter-torque

○ Actuated by servo motor

  • 3D printed body
slide-23
SLIDE 23

Payload Electronics

  • Arduino Sensor Suite

○ Accelerometer ■ Upright detection ○ GPS ■ Rover location

  • XBEE Telemetry

○ Ground station signal

  • Motor Control
  • Lithium Ion Battery

23

slide-24
SLIDE 24

Full Scale Payload Electronics

24

slide-25
SLIDE 25

Deployment Protocol

  • Launch Vehicle returns to ground
  • Ground station relays command XBEE -> XBEE
  • Rover deploys from launch vehicle in capsule
  • Spring loaded capsule opens and deploys rover
  • Rover accomplishes task
  • GPS module will relay rover position back to the ground station via XBEE

radio device

25

slide-26
SLIDE 26

Payload Design Process

The team utilized the following decision matrix to choose a rover design path to pursue

26

Goal Tank Treaded Rover 4-Wheeled Rover 2-Wheeled Rover Achievability 15% 20% 15% Obstacle Avoidance 12% 3% 3% Size 9% 12% 27% Durability 20% 16% 30% Total 56% 51% 75%

slide-27
SLIDE 27

Requirement Compliance Plan

27

Project Lead Safety Officer Launch Vehicle Technical Lead Payload Mechanical Technical Lead Payload Electrical Technical Lead

slide-28
SLIDE 28

STEM Outreach

28

slide-29
SLIDE 29

Questions

29