University of Florida Rocket Team Critical Design Review Presentation

University of Florida Rocket TeamCritical Design Review

Presentation

Outline

OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work

Design Overview

Total Length: 164.56 inchesTotal Mass: 76 lbsTarget Altitude: 10,000 ft

Outline

OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work

Airframes

Rolled with 6 oz E-class Fiberglass7 wraps; approximately 0.07 in wall thickness5 airframes: Upper, UEB, Middle, Lower

Extension, Lower

Upper Airframe

Houses the piston and main parachute32.5 inches longSeparation occurs above it, at nosecone

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

Middle Airframe

Houses the baffles and drogue parachuteSeparation occurs below itLength: 20 inchesLocation of upper launch lug

Lower Airframe

Lower extension connects to coupler and lower airframe

Internal components assemble as one pieceLower extension length: 24 inchesLower Airframe length: 32 inches

Motor Centering and Thrust Transfer

Fins

Tapered sweptHeight: 6 inchesRoot chord: 11 inchesTip chord: 3.5 inchesG10 fiberglassSame attachment

method as subscale

Outline

OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work

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

Outline

OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsFuture Work

Stability Characteristics

Rail Exit Velocity = 72.5 ft/sec

Thrust to Weight Ratio = 7.6

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)

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)

Outline

OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work

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

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

Attachment Scheme

Parachute Manufacturing

Ripstop nylonGore designNylon upholstery

threadNylon shroud lines

Parachute Testing

Charge Baffle

Two discs with non overlapping circular patters of holes

Cools gasses from ejection charges and removes particulates

Used to protect drogue parachute

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

Outline

OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work

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

Camera Module

Camera Integration

Electronics Mapping

Centering Rings Bulk Head

Motor Tube Strain GagesTemperature Compensation

Strain Gages

Boost System Analysis

𝐹 𝑔 (𝑡 )+𝐹𝐷(𝑡 )

𝐹𝑇1(𝑡 )

Von Mises Strain

URES Strain

Triboelectric Effect Analysis Payload

Triboelectric Effect Capacitive Sensing Technique Experimental Setup Payload Objectives

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.

Capacitive Sensing Technique

Theory C = Q/V σ = Q/A Voltage

measurement circuit

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

Payload Objective

Obtain nose cone map of voltage vs. time Calculate charge buildup Relate to friction models from

computational fluid dynamics simulation data

Outline

OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work

Electronics

Power Inputs Communications and data processing Recovery Lower Bay Image processing Boost systems analysis

Power

Provides power to entire Upper Electronics Bay

Inputs

Communications and Data Processing

ODROID Communications board

Recovery

Lower Bay

Handles image processing Midway point for Boost Systems Analysis

Image Processing

Boost Systems Analysis

Outline

OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work

Testing

Recovery Testing Parachute Testing Complete

Structural Testing Compression and Shear Stress Testing Complete Subscale Testing Complete

Electronics TestingMotor TestingPayload Testing

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

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

Outline

OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work

Future Work

Manufacture full scale Update mass estimatesAcquire travel fundingFull scale Launch, April 5th