NASA SL - NU FRONTIERS. PDR presentation to the NASA Student Launch Review Panel
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1 NASA SL - NU FRONTIERS PDR presentation to the NASA Student Launch Review Panel 1
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 Requirement Compliance Plan STEM Outreach Questions 2
3 Launch Vehicle Overview Materials Airframe, Nosecone and Coupler - G12 Fiberglass (Madcow Rocketry) Fins - G10 Fiberglass Centering Rings and Bulkheads - Birch Plywood Length inches Mass kg 3
4 Launch Vehicle Overview 4
5 Launch Vehicle Overview - Material Alternatives Fiberglass Carbon Fiber Pros: Strength, durability Cons: Heavy, toxic Pros: Strength, durability Cons: Heavy, toxic, expensive Blue Tube (Galvanized Cardboard) Pros: Light, cheap Cons: Low strength, susceptible to environment 5
6 Nose Cone Section: Dimensions and Materials Shape: 5:1 Ogive (~30 inches long) Materials: G12 Fiberglass Weight: 2.3 pounds 6
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
8 Payload Section 8
9 Payload Section - Dimensions 9
10 Lowe Avionics Bay Section Contains Lower Avionics Bay Drogue Parachute Lower Sections Main Parachute 10
11 Lowe Avionics Bay Section - Dimensions 11
12 Booster Section Includes Motor Fins 12
13 Booster Section- Dimensions 13
14 Motor Selection - L1395-BS Projected Apogee: 5,370 feet Total Impulse: 4, N-s Thrust to Weight:
15 Motor Selection - Alternatives Motor Burn Time Max (s) Acceleration (Gs) Apogee Total Impulse Mass with (ft) (N*s) Fuel (g) Mass without Fuel (g) L1395-B S-P L2375WT-P L1115-P L1350-C S
16 Ascent Analysis CP: 112 inches from tip of nose cone CG: inches from tip of nose cone Exit velocity off 144 inch Rail: 74 feet/s Thrust to Weight (L1396-BS Motor):
17 Launch Procedure and Separations 17
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
19 Recovery System - Parachutes Parachute CD A(in2) Manufacturer 48 Nylon Parachute Sunward Group Ltd 72 Iris Ultra Light Parachute Fruity Chutes Fruity Chutes Iris Ultra Light Parachute 19
20 Recovery System - Kinetic Energy 75 ft-lb Maximum Competition Requirement Section Mass Total (lb) Parachute Data (CD * Kinetic Energy (ft * lb) A) Nose-Cone 5.63 Nose Cone Main Main Avionics Bay 5.29 Drogue + Booster Main Booster Section 8.01 Drogue + Booster Main Payload 12.8 Drogue + Booster Main
21 Recovery System - Lateral Drift 2,500 foot Lateral Drift Maximum Competition Requirement Launch Vehicle Drift Calculations Using OpenRocket Simulation Software, 10 Simulation Average 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 21
22 Payload Mechanics Self-righting design 6 Pneumatic tires Solar panel fan Deployable counter-torque Opened by servo motor Actuated by servo motor 3D printed body 22
23 Payload Electronics Arduino Sensor Suite Accelerometer Upright detection GPS Rover location XBEE Telemetry Ground station signal Motor Control Lithium Ion Battery 23
24 Full Scale Payload Electronics 24
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
26 Payload Design Process The team utilized the following decision matrix to choose a rover design path to pursue 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% 26
27 Requirement Compliance Plan Project Lead Safety Officer Launch Vehicle Technical Lead Payload Mechanical Technical Lead Payload Electrical Technical Lead 27
28 STEM Outreach 28
29 Questions 29
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