university of florida rocket team critical design review presentation
DESCRIPTION
University of Florida Rocket Team Critical Design Review Presentation. Outline. Overview Vehicle Design Motor Choice Flight Dynamics and Simulations Recovery Payloads Electronics Component Testing Future Work. Design Overview. Total Length: 164.56 inches Total Mass: 76 lbs - PowerPoint PPT PresentationTRANSCRIPT
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University of Florida Rocket TeamCritical Design Review
Presentation
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Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work
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Design Overview
Total Length: 164.56 inchesTotal Mass: 76 lbsTarget Altitude: 10,000 ft
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Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work
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Airframes
Rolled with 6 oz E-class Fiberglass7 wraps; approximately 0.07 in wall thickness5 airframes: Upper, UEB, Middle, Lower
Extension, Lower
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Upper Airframe
Houses the piston and main parachute32.5 inches longSeparation occurs above it, at nosecone
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Upper Electronics Bay
L-shaped bay to maximize space
Hatch allows easy access
Aluminum bulkheads for precision
Bay Length: 19.8 inches
Airframe Length: 23.125 inches
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Middle Airframe
Houses the baffles and drogue parachuteSeparation occurs below itLength: 20 inchesLocation of upper launch lug
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Lower Airframe
Lower extension connects to coupler and lower airframe
Internal components assemble as one pieceLower extension length: 24 inchesLower Airframe length: 32 inches
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Motor Centering and Thrust Transfer
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Fins
Tapered sweptHeight: 6 inchesRoot chord: 11 inchesTip chord: 3.5 inchesG10 fiberglassSame attachment
method as subscale
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Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work
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Motor Choice
Cesaroni N2600-SK-P SpecificationsTotal Impulse (lbf*s) 2489Average Thrust (lbf) 584Max Thrust (lbf) 668Burn Time (s) 4.26Launch Mass (lb) 25.3Empty Mass (lb) 10.4
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Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsFuture Work
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Stability Characteristics
Rail Exit Velocity = 72.5 ft/sec
Thrust to Weight Ratio = 7.6
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Altitude versus Time
• Maximum altitude of 10,842 feet• Drogue parachute deployment at 25 seconds (apogee)• Main parachute deployment at 237 seconds, 700 feet of
altitude
0 25 50 75 100 125 150 175 200 225 2500
2500
5000
7500
10000
12500
15000Altitude vs Time
Time (s)
Alti
ttide
(ft)
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Velocity and Acceleration versus Time
• Peak velocity of 955 ft/s at 4 seconds
• Shows drogue and main parachute deployment at 25 and 237 seconds respectively
• Peak acceleration of 269 ft/s2 at 1.5 seconds
• Shows acceleration from drag and gravity up to apogee at 25 seconds
• Constant velocity under drogue, zero acceleration
0 25 50 75 100 125 150 175 200 225 250-100
0
100
200
300
400
500
600
700
800
900
1000Velocity vs Time
Time (s)
Vel
ocity
(ft/s
)
0 5 10 15 20 25 30 35-50
0
50
100
150
200
250
300Acceleration vs Time
Time (s)
Acc
eler
atio
n (ft
/s2)
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Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work
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Recovery
ObjectivesReusable without repairsKinetic Energy each piece is less than 75 ft-
lbfMain and drogue parachute manufactured by
teamGPS tracking deviceCrosswind drift less than 5,000ft
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Recovery System
DrogueDeployment at apogee60 inches in diameterSemi-ellipsoid canopy
shapeCharge baffle ejection
systemDescent velocity: 45.4 ft/s
MainDeployment at 700ft168 inches in
diameterSemi-ellipsoid canopy
shapePiston ejection
systemDescent velocity:
12.5ft/s
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Attachment Scheme
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Parachute Manufacturing
Ripstop nylonGore designNylon upholstery
threadNylon shroud lines
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Parachute Testing
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Charge Baffle
Two discs with non overlapping circular patters of holes
Cools gasses from ejection charges and removes particulates
Used to protect drogue parachute
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Kinetic Energy
Component Descent Rate (ft/s) Mass (slugs) Kinetic Energy (ft-lbf)
Nosecone 12.5 0.0979 7.744Piston 12.5 0.0310 2.457
Upper Airframe 12.5 0.539 42.66Lower Airframe 12.5 0.874 69.14
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Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work
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Ground Scanning System
Ground Scanning System to detect hazards in the landing area
Take an image of landing areaScan for potential hazards in real-timeSend scanned image to Ground Station in
real-time
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Camera Module
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Camera Integration
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Electronics Mapping
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Centering Rings Bulk Head
Motor Tube Strain GagesTemperature Compensation
Strain Gages
Boost System Analysis
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𝐹 𝑔 (𝑡 )+𝐹𝐷(𝑡 )
𝐹𝑇1(𝑡 )
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Von Mises Strain
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URES Strain
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Triboelectric Effect Analysis Payload
Triboelectric Effect Capacitive Sensing Technique Experimental Setup Payload Objectives
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Triboelectric Effect
The triboelectric effect (also known as triboelectric charging) is a type of contact electrification in which certain materials become electrically charged after they come into contact with another different material through friction.
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Capacitive Sensing Technique
Theory C = Q/V σ = Q/A Voltage
measurement circuit
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Experimental Setup
Placement of capacitive sensors Data collection and recovery Precision Analog-to-Digital Converter
(ADC) with 8051 Microcontroller and Flash Memory Texas Instruments - MSC1210Y5PAGT
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Payload Objective
Obtain nose cone map of voltage vs. time Calculate charge buildup Relate to friction models from
computational fluid dynamics simulation data
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Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work
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Electronics
Power Inputs Communications and data processing Recovery Lower Bay Image processing Boost systems analysis
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Power
Provides power to entire Upper Electronics Bay
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Inputs
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Communications and Data Processing
ODROID Communications board
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Recovery
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Lower Bay
Handles image processing Midway point for Boost Systems Analysis
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Image Processing
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Boost Systems Analysis
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Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work
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Testing
Recovery Testing Parachute Testing Complete
Structural Testing Compression and Shear Stress Testing Complete Subscale Testing Complete
Electronics TestingMotor TestingPayload Testing
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Subscale Results
Design Length: 91.13 in. Max. Diameter: 3.2 in. Weight: 15.4 lbs. Stability Margin: 1.36 Predicted Apogee:
1675 ft. Results
Actual Apogee: 1865 ft.
Drogue Deployment: Successful
Main Deployment: Failure
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Status of Requirements Verification
Completed 11 Requirements
Project Plan Safety Requirements Component Testing
In Progress 18 Requirements
Design Analysis Complete Inspection and Testing In Progress
Not Started 25 Requirements
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Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work
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Future Work
Manufacture full scale Update mass estimatesAcquire travel fundingFull scale Launch, April 5th