![Page 1: University of Florida Rocket Team Critical Design Review Presentation](https://reader034.vdocuments.net/reader034/viewer/2022051421/56816728550346895ddbc395/html5/thumbnails/1.jpg)
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