Project NOVA
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- Marjory Sybil Moody
- 5 years ago
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1 Project NOVA
2 Our Mission Design a Rocket Capable of: Apogee of 5280 ft Deploying an autonomous Rover
3 Vehicle REILLY B.
4 Vehicle Dimensions Total Length of 108 inches Inner Diameter of 6 inches Outer Diameter of 6.25 Inches Estimated Mass of 39.9 lbs
5 Material Selection Carbon Fiber High strength to weight ratio Rated highest in team trade study 3D braided carbon fiber Lighter than a solid carbon fiber tube while still providing necessary strength Used to create an Open-Architecture Composite Structure (O-ACS)
6 Clipped-Delta Fins Easy to manufacture Proven design Performs well in subsonic flight Team experience
7 Ogive Nose Cone Low Coefficient of Drag Easy to manufacture Rated highest by team trade study Commonly used in professional and hobby rocketry
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11 Stability Margin Static Stability Margin of 2.26 Calibers CG located inches from nose cone CP located inches from nose cone
12 Motor Selection and Performance Predictions Initial motor selection is a Aerotech L1420R Simulated altitude of 6034 ft (AGL) Thrust-to-weight ratio is 8:1 Provides a rail exit velocity of 53 ft/s
13 Aerotech L1420R Thrust Curve
14 Aerotech L1420R Motor Specifications Manufacturer Motor Designation Diameter Length Total Impulse Total Motor Weight Propellant Weight Propellant Type Average Thrust Maximum Thrust Burn Time Aerotech L1420R 2.95 in 17.4 in 1038 lb sec 10.1 lb 5.69 lb Solid 326 lbf 374 lbf 3.18 sec
15 Testing Plans 2:3 Subscale Materials Testing
16 Subscale Testing Plans 1:2 Scale 11.4 lbs Loki - J820-P motor selection
17 Materials Testing
18 Recovery BEN C.
19 Recovery Overview Unemployed Upper Main Parachute Drogue Parachute Nosecone Upper Main Parachute Stage 2: Apogee Drogue Deploys Lower Main Parachute Upper Section Stage 3: 750 ft - Mains Deploy Stage 1: Launch Lower Section
20 Parachutes Three parachutes required Drogue Circular 31 inch diameter Upper Main Hemispherical inch diameter Lower Main Hemispherical 34.3 inch diameter Both Main parachutes will have a spill hole
21 Parachutes Construction Gores Ripstop nylon Tear resistant weaving
22 Parachutes Upper Main parachute deployed with Jolly Logic Chute Release System
23 Attachment Hardware onylon Slotted Pan Head Machine Screws osteel U-Bolts oquick Links oinsulated Carbon Fiber Altimeter Board
24 Shock Cord o1 inch tubular nylon oexcellent tensile strength olow weight
25 Electronics - Altimeters Two altimeters Altus Metrum Telemega Altus Metrum Telemetrum Two Jolly Logic Chute Releases
26 Electronics - Altimeters
27 Black Powder Ejection System oeffective oreliable otested olow volume
28 Black Powder Ejection System Ideal Gas Law PV = nrt P = pins * F / A N = * F * L (grams) Charge cups
29 Recovery Testing o Wind tunnels o Ejection o Materials
30 Deployable Rover DAVID T.
31 Goal Rover will be housed in rocket body until being remotely activated when it will travel at least five feet from the rocket and deploy solar panels.
32 Mechanical 3D printed Lightweight Design easily changed
33 Body Top and bottom sections Onyx
34 Solar Panel Deployment Accordion design Fits with rover body
35 Treads 2 Drive Wheels 2 Idle Wheels 2 Treads for Traction Onyx
36 Electrical Arduino Uno 3 Motors 1 Motor Shield 2 XBee Communication Devices (Respective Attachments) 2 9V Batteries
37 Control Arduino Uno
38 Motors Pololu Micro Metal Gearmotor 1000:1 Gear Ratio 125 oz-in at Stall Torque
39 Communication Xbee Pro Up to 1 Mile Communication Distance Two-Way Communication
40 Altitude Control TANNER O.
41 Design New path this year Previous drag implemented fins Current iteration will be completely internal with drag plates
42 Internal Plate Drag System (IPDS)
43 Bottom-Up View
44 Electronics Arduino Uno Adafruit 9-DOF IMU AndyMark NeveRest 40
45 Considerations Drag plates must deploy simultaneously Plates must not deploy during motor burn Rocket is stable
46 Safety COREY RATCHICK
47 Officer Overview o Worked previously with safety and recovery o Briefs team, updates and supplies MSDS, ensures availability of PPE o Creates checklists to ensure proper safety protocols and consistency
48 Team Liaisons Liaisons have been established with each team to effectively and efficiently monitor all components of the project. o Jake R. with Recovery o Ruth A. with Systems o Alex D. with Vehicle Body o Rhett R. with Rover o Sydney F. with Testing
49 Testing BRYCE G.
50 Completed Testing Materials testing All materials used in structural components of the rocket Tension, compression and three point bend Ground separation testing for subscale Electronics interference Battery duration tests
51 Planned Testing Subscale and Full Scale launches Ground separation testing for full scale Checking electronics for interference on full scale Rover ability to cross rough terrain Rover ability to deploy from any orientation Drag measurements on altitude control system plates
52 Educational Outreach KATHERINE M.
53 Educational Outreach Events Drake Middle School 7th Grade Rocket Week: Spring, 2018 Samuel Ginn College Engineering Day: February 23, 2018 Boy Scout and Girl Scout events: Spring 2018 Auburn Junior High Engineering Day: November 9, 2017
54 Project Timeline Funding Budget
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