NASA s Student Launch Initiative : Seniors 8 Juniors 2 Sophomores 6 Interdisciplinary 2 Preliminary Design Review Payload: Fragile Material Protection Freshman 5 1
Agenda 1. Team Overview 2. 3. 4. I. Airframe II. Electronic Payload III. Main Payload IV. Recovery V. Propulsion 5. 6. 2
Objectives Compete a high powered rocket that meets all specified criteria Reach an altitude between 5,125 ft. & 5,375 ft. Field a successful payload that produces useful vibration reduction data Transmit all data wirelessly to ground station 3
Team Structure 4
Airframe Objectives Remain intact Reusable Protect internal components 5
Airframe 6
Dimensions and Subsections 7
Weight Breakdown Total Weight: 35.19 lb 8
Decision Matrix Nosecone Shape Option Cost Drag Ogive Δ О Elliptical О Δ Conical О X 9
Decision Matrix Fin and Nosecone Material Option Cost Strength Ductility Carbon Fiber X О О Fiberglass О Δ Δ ULTEM X О О 10
Decision Matrix Body Tube Option Cost Strength Ductility Carbon Fiber X О О Fiberglass Δ Δ Δ Blue Tube О X X 11
Decision Matrix Bulkhead Material Option Cost Strength Weight Aluminum X О Δ Plywood O X O Fiberglass Δ Δ Δ 12
Altimeter (Electronic Payload) Objectives Accurately measure apogee Retrieve flight data wirelessly Be able to track the rocket with GPS Waterproof compartment 13
Altimeter Selection Decision Matrix Altimeter Option Cost GPS Ability Data Acquisition Altus TeleMega Δ O O Altus TeleMetrum O O Δ 14
Altimeter (Electronic Payload) Altus TeleMega Located in nosecone GPS and Apogee Easy to retrieve the data Detailed flight data can be used to compare to OpenRocket/Rocksim 15
Altimeter Mounting 16
Altimeter Mounting 5 O.D. 17
Payload Objectives NASA Given: Protect unknown fragile object Envelop of 3.5 in dia. and 6 in length May not add nor remove material Team Created: Reduce impact force by 50 percent Create valid mathematical model Reduce acceleration by 35 percent 18
Main Payload 19
Decision Matrix Payload Option Cost Force Reduction Acceleration Reduction Parallel Spring System Single Mounted Cylinder with Support Material Series and Parallel Spring System Δ X O O X X Δ O O 20
Conceptual Design Concentric cylinder design Series and Parallel spring design Wire rope isolators for 360 vibration coverage Easily removable Variable fill design 21
Mathematical Design Payload M 3 x 3 k 2 c 1 Housing M 2 x 2 k 1 c 2 Rocket M 1 x 1 F 22
ሶ ሶ ሶ Team Overview k 1 x 2 k 1 x 2 c 1 x 1 ሶ c 1 x 2 k 2 x 2 w 3 c 2 x 2 M 1 M 3 ΣF y = 0 = M 1 xሷ 1 = F + k 1 x 2 x 1 F k 1 x 2 w 2 + c 1 ( xሶ 2 ሶ c 1 x 2 x 1 ൯ k 2 x 3 c 2 xሶ 3 ΣF y = 0 = M 3 xሷ 3 = w 3 + k 2 x 2 x 3 + c 2 ( xሶ 2 ሶ x 3 ൯ M 2 k 1 x 1 ΣF y = 0 = M 2 xሷ 2 = w 2 + k x 2 x 1 c 1 xሶ 2 xሶ 1 + k 2 x 3 x 2 + c 2 ( xሶ 3 ሶ c 1 xሶ 1 x 2 ൯ 23
Mathematical Model Inputs Thrust curve Impact force Parachute deployment force Spring constant (k) values Damping coefficient (c) values Outputs Relative position graph Relative velocity graph Relative acceleration graph Relative force calculation 24
Recovery 25
Recovery - Objectives Two parachutes Drogue at apogee Main at low altitude 75 ft-lb f maximum Kinetic Energy Independent electronics Redundant altimeters Lockable arming switches Separate batteries Shear pins Tracking equipment and transmission 26
Recovery Dual-Deployment Reduce ground track during descent Drogue parachute at apogee Main parachute at 1000 feet http://www.arsabq.org/new_participants.htm 27
DROGUE MAIN 28
DROGUE CHUTE MAIN CHUTE BOW BULKPLATES 36 ELECTRONICS BAY 96 AFT BULKPLATES 25 35 29
Recovery Electronics Fully redundant, independent systems Black powder ejection charges Mounted to plywood sled 30
31 Team Overview Main Parachute Drogue Parachute On/Off Switch Primary Altimeter Primary Battery Primary Main Igniter Primary Drogue Igniter Primary Main Charge Primary Drogue Charge On/Off Switch Backup Altimeter Backup Battery Backup Drogue Igniter Backup Main Igniter Backup Drogue Charge Backup Main Charge PRIMARY CIRCUIT BACKUP CIRCUIT
Recovery Strength Aluminum bulkplates Steel U-bolts Tubular nylon tether 400 lbf max force 32
Decision Matrix Recovery Altimeter Option Cost Feature Set Power Draw PerfectFlite Stratologger CF O O Δ AltusMetrum EasyMini Δ Δ О Entacore AIM3 X O О http://www.perfectflite.com/slcf.html 33
Decision Matrix Recovery Harness Option Cost Strength Elasticity Elastic O X X Tubular Kevlar X O Δ Tubular Nylon Δ Δ О http://onebadhawk.com/1-tubular-nylon--2-loop.html 34
Decision Matrix Drogue Parachute Option Cost Descent Rate Max Force 24 Fruity Chutes Classic Elliptical O Δ X 36 Fruity Chutes Classic Elliptical O O Δ 48 Fruity Chutes Classic Elliptical Δ Δ О http://fruitychutes.com/parachute_recovery _systems/classic_elliptical_chutes.htm 35
Decision Matrix Main Parachute Option Cost Impact Max Force 72 Fruity Chutes Iris Ultra O X O 84 Fruity Chutes Iris Ultra O Δ Δ 96 Fruity Chutes Iris Ultra Δ O Δ http://fruitychutes.com/parachute_recovery _systems/iris_ultra_parachutes.htm 36
Recovery - Wind Speed (mph) Lateral Distance (ft) 0 7 5 576 Section Nose Cone & Payload Mass (lb) Kinetic Energy (ft-lbf) 9.19 20.9 10 1296 Recovery Bay 4.32 12.66 15 2087 20 3046 Booster 10.03 29.4 37
Propulsion Objectives The vehicle should attain an apogee between 5,125 feet and 5,375 feet The vehicle should remain below Mach 1 The motor mount should withstand propulsion forces and remain reusable for any following flights 38
Decision Matrix Centering Rings Option Cost Strength Weight Plywood O X О G10 Fiberglass Δ О О Aluminum Δ О X 39
Decision Matrix Motor Mount Design Option Cost Against Regulations Cluster Motor Mount O Δ X Single Motor Mount X Δ O 40
Motor Mount Design Inner Tube Blue Tube Bulkhead Aluminum 6061 T6 Centering Rings Aluminum 6061 T6 Bulkhead Centering Rings Inner Tube and Motor 41
Exploded Motor Mount Design 42
Manufacturer Cesaroni Technology Animal Motor Works AeroTech Inc Make L800 L1080BB-P L850W Total Impulse 3731 Ns 3686 Ns 3695 Ns Altitude 5428 ft 5330 ft 5379 ft Type Reloadable Reloadable Reloadable Max Thrust 1024 N 1258 N 1185 N Weight(Empty) 3.79 lb 4.13 lb 3.54 lb 43
Down-Selected Motor Manufacturer Make Total Impulse Altitude Type Max Thrust Weight (Empty) AeroTech L850W 3695 Ns 5379 ft Reloadable 1185 N 3.54 lb Level 2 motor Motor Selection Criteria: Altitude No K class Impulse Thrust Reloadable More design flexibility 44
Decision Matrix Fin Shape Option Stability Ease of Manufacturing Likelihood of Damage Clipped Delta Δ О Δ Trapezoidal X Δ О Tapered Swept О Δ X 45
Fins Root Chord: 11.5 in Tip Chord: 5.8 in Height: 7.5 in Surface Area: 63 in 2 46
Predicative Altitude Assurance Plan Verify four methods produce similar C d values Verify software ability to predict sub-scale altitude 1/2 Scale CFD Data Wind Tunnel Data OpenRocket Altitude Prediction Rocksim Altitude Prediction Test Flight Data Verify four methods produce similar C d values Verify software ability to predict full-scale altitude Full Scale CFD Data Wind Tunnel Data OpenRocket Altitude Prediction Rocksim Altitude Prediction Test Flight Data Altitude Prediction 47
Altitude Prediction: OpenRocket Software Program uses a model for the atmospheric conditions and for the wind Assumptions: Ideal Gas Wind speed uniaxial Earth is flat Wind turbulence based off wind farms Uses Runge-Kutta 4 48
Altitude (ft) Team Overview Predicted Altitude 6000 Altitude 5,379 feet Over estimate because: Software simulation Uncertainty in weight Plan to add ballast 5000 4000 3000 2000 1000 0 0 20 40 60 80 100 120 140 160 180 Time (s) 49
Altitude (ft) Team Overview Rocksim Predicted Altitude Altitude 5,368 ft Percent Difference of 0.2% Based off of OpenRocket as original value 6000 5000 4000 3000 2000 1000 0 0 20 40 60 80 100 120 140 160 180 Time (s) 50
Basic Rocket Information Max Velocity and Acceleration 592 ft/s and 208 ft/sec^2 Mach Number 0.53 Thrust to Weight Ratio 5.61:1 Rail Exit Velocity 69.2 ft/s 51
Stability Stability: 3.69 cal. 69.92 in. 90.46 in. 52
Testing Plan Wind Tunnel Testing Parachute Testing Payload Testing Recovery/ Test Ejection Half Scale Model Full Scale Model 53
Overview and Requirements Officer Designation Checklists Certification and Liability Monitor Rules and Regulations 54
Personnel Hazard Analysis Black Powder Fire Rocket Propellant Major Severity Handheld Tools Low Likelihood Craft/Exacto Knives Heavy Machinery Epoxy Fumes High Likelihood Minor Severity Dust Particles *Full Analysis can be seen in PDR Report* 55
Failure Modes and Effects Analysis Motor Mishandling/ Accidental Ignition Launch Failure Main Parachute Deployment Failure Major Severity Excessively Tight Coupler Low Likelihood Drogue Parachute Deployment Failure Instability During Flight High Likelihood Payload not Secured Properly Altimeter/Electronics Malfunction Minor Severity *Full Analysis can be seen in PDR Report* 56
Environmental Consideration Analysis Rocket Motor Ignition Major Severity Water Low Likelihood Debris from Rocket Strong Winds High Likelihood Humidity Epoxy Fumes Minor Severity Dust Particles *Full Analysis can be seen in PDR Report* 57
General Risk Assessment Major Severity Limited Resources Tight/Minimal Budget Low Likelihood Mismanagement of Time Increase in Regulations Underestimation of Scope of Work High Likelihood Minor Severity *Full Analysis can be seen in PDR Report* 58
Education Outreach Activities Engage 200 Students in STEM-related Activities Emphasis on Middle School Students Activities NTI STEMFest Hydraulic Robotic Arms Snap Circuits Engineering Rocks Egg Drop Competition Webelos Day Tennis Ball Launcher Optimization 59
Schedule: Reporting 60
Schedule: Design Phase 61
Budget 1% 3% Itemized Cost + Contingency Based on Risk 10% Item Forecasted Amount Pie Chart Color Operating $300.00 11% 26% Travel / Lodging $2,730.00 Launch Pad $220.00 Aerodynamics (Body) $1,400.00 Propulsion $2,500.00 Main Payload $500.00 6% 5% 2% Electronic Payload $670.00 Recovery $1,150.00 13% Scale Model $1,050.00 $100.00 Total $10,620.00 23% 62
Thank you for your time! Questions? 63