Readiness Review University of Alabama in Huntsville University - - PowerPoint PPT Presentation

University of Alabama in Huntsville

NASA SL Flight Readiness Review

3/5/2018 University of Alabama in Huntsville USLI PDR 1

LAUNCH VEHICLE

University of Alabama in Huntsville USLI PDR 2 3/5/2018

Vehicle Overview

• Vehicle Dimensions

– Diameter: 6” fairing/4” aft – Length: 106 inches – Wet Mass: 41.1 lbs. – Center of Pressure: 66.79 – Center of Gravity: 52.04

• Payload

– Deployable Rover – Autonomous – Retractable solar panels – L12” x H3” x W4” – Weight: 7 lbs.

University of Alabama in Huntsville USLI PDR 3 3/5/2018

Vehicle CONOPS

University of Alabama in Huntsville USLI PDR 4 3/5/2018

• Consists of:

– Nose cone – Fairing – Transition – Forward coupler

• Purposes:

– House and protect rover and deployment piston – Transition between main body tube and fairing

Forw rward Overview

University of Alabama in Huntsville USLI PDR 5 3/5/2018

• 3D printed
• 6 in. tall elliptical shape
• 2 in. shoulder
• Houses solenoid for

retention

• Aluminum bulkhead for

flush contact with rover

Nose Cone

University of Alabama in Huntsville USLI PDR 6 3/5/2018

• Three solenoids with ½
• in. aluminum rods
• Will reliably retain the

rover during flight

• Retract upon receiving

signal after landing

• Makes nose cone

ejection easier

Solenoid

University of Alabama in Huntsville USLI PDR 7 3/5/2018

• Arduino Nano

with XBee

• 5V supply
• Spring assisted

release of 8 oz. load

• Solenoids pull

with 10-25 oz.

Solenoid

University of Alabama in Huntsville USLI PDR 8 3/5/2018

• Houses rover and piston
• G12 fiberglass
• 25.25 in. long
• 6.17 in. outer diameter
• 6.0 in. inner diameter
• Secured to transition with ¼-20 bolts
• Secured to nose cone with solenoid pins

Fairing

University of Alabama in Huntsville USLI PDR 9 3/5/2018

• 6 in. tall coupler section
• 0.25 in. thick aluminum

bulkhead

• Used to push rover out
• f the fairing

Piston

University of Alabama in Huntsville USLI PDR 10 3/5/2018

• 3D printed forward and aft

pieces with sparse in-fill for weight reduction

• 0.25 in. thick aluminum insert
• Threaded inserts with ¼-20 bolts

hold pieces together

Transition

University of Alabama in Huntsville USLI PDR 11 3/5/2018

• 9 in. long
• Sits within aft transition piece
• Secured by threaded rod in

tension between bulkhead and transition insert

• U-bolt attached to aft bulkhead

for main parachute

Coupler

University of Alabama in Huntsville USLI PDR 12 3/5/2018

CENTRAL SUBSYSTEM

University of Alabama in Huntsville USLI PDR 13 3/5/2018

Central Subsystem Overview

• Central Subsystem responsibilities:

– Primary coupler between airframes – Flight Avionics – Ejection System – Tracking and Ground Station – Recovery System

3/5/2018 University of Alabama in Huntsville USLI PDR 14

• Altimeter calculates altitude
• Charges deploy recovery system
• Carbon fiber protects avionics from RF interference
• Aluminum bulkheads serve as protection from ejection

charges

• Redundant charges/circuits

Coupler

3/5/2018 University of Alabama in Huntsville USLI PDR 15

• Change: Switches rotated 270deg
• Interfaces with forward and aft sections via

removable rivets and shear pins, respectively

• Interfaces with recovery system via U-bolts

Coupler

3/5/2018 University of Alabama in Huntsville USLI PDR 16

AFT SUBSYSTEM

University of Alabama in Huntsville USLI PDR 17 3/5/2018

Aft ft Overview

University of Alabama in Huntsville USLI PDR 18

• Components

– Lower Recovery Bulkhead – Fin Can Assembly – Fins (x4) – Rail Buttons/Standoffs – Thrust plate – Motor case retention

3/5/2018

• 42 in. section of G-12 Fiberglass tube

– Cut to length with wet saw

• Fin slots cut using wooden jig guided router
• Fin Can retention holes drilled using 3-D

printed template

Aft ft Body Tube

University of Alabama in Huntsville USLI PDR 19 3/5/2018

• 6061T-6 Aluminum

– Machined in-house using CNC

• Pocketed to reduce weight
• U-Bolt for lower recovery
• Secured to Aft Airframe using four 4-40 bolts
• Dimension

– 3.9 in. dia.

Aft ft Recovery ry Bulkhead

University of Alabama in Huntsville USLI PDR 20 3/5/2018

• Trapezoidal Fin set (x4)
• G-10 Fiberglass

– Wet sawed in house

• Change since CDR

– L1420 Flight: 3.5 in. height – L1520 Flight 3.25 in. height

Fins

University of Alabama in Huntsville USLI PDR 21 3/5/2018

• 3-D printed in-house

– ABS plastic

• Attached to aft using

24x 4-40 bolts

• 4 bolts holding each

each fin in place

• Dimensions

– 9.75 in. length, 3.9 in.

• uter dia.,

2.9 in. inner dia.

Fin Can

University of Alabama in Huntsville USLI PDR 22 3/5/2018

• Press fits in the bottom did not stay in plastic
• 6 motor retention/thrust plate holes

– 4 holes now 4-40 through holes, secured with nuts – 2 remaining holes tapped for larger screws

Fin Can Change

University of Alabama in Huntsville USLI PDR 23 3/5/2018

• 6061T-6 Aluminum

– Machined in-house

• Take motor thrust load

– Not transferred to ABS plastic

• Dimensions

– 4.016 in. outer dia. – 3.9 in. inner lip dia. – 0.125 in. lip

Thrust Ring

University of Alabama in Huntsville USLI PDR 24 3/5/2018

• 3-D printed from ABS plastic in-house
• Held to fin can using two 6-32 screws
• Retains motor into

Aft body tube

• Dimensions

– 4.016 in. outer dia. – 3.48 in. dia. Inner lip – 0.25 in. lip

Motor Retention Ring

University of Alabama in Huntsville USLI PDR 25 3/5/2018

• Large Airfoiled 1515 Rail Buttons

– Commercially Available

• Attached to Aft Airframe
• 3-D printed Standoffs

– Accommodate for reduced aft airframe (4 in. dia.)

Rail Buttons

University of Alabama in Huntsville USLI PDR 26 3/5/2018

RECOVERY SYSTEM

University of Alabama in Huntsville USLI PDR 27 3/5/2018

Recovery ry System

• Drogue Parachute Deployment:

– Deployment at apogee – Fruity Chute CFC-18 (Cd = 1.5) – Shock Cords: ½ in. Kevlar (50 ft.) – Connected between aft bulkhead in lower airframe and avionics bay housing. – Descent speed under drogue: 100.18 ft./s

• Main Parachute Deployment:

– Deployment at 600 ft. above ground level – Fruity Chute 96” Iris Ultra (Cd = 2.2) – Shock Cords: ½ inch Kevlar(50 ft.) – Connected between fairing bulkhead and avionics bay housing. – Descent speed under main: 15.51 ft./s

University of Alabama in Huntsville USLI PDR 28 3/5/2018

• Full Scale Charge Testing
• Full Scale Flights

Recovery ry System Tests

University of Alabama in Huntsville USLI PDR 29 3/5/2018

• Required that each individual section will have a maximum

kinetic energy of 75 ft-lbf

• Terminal velocity under drogue: 100.18 ft./s
• Terminal velocity under main: 15.51 ft./s
• Upon landing the vehicle will be broken into three major

components tethered together

Kinetic Energy

University of Alabama in Huntsville USLI PDR 30

Vehicle Section Mass (lbm.) KE (ft-lbf) Fairing 18.06 67.46 Coupler 6.79 25.36 Aft 8.93 33.36

3/5/2018

Drift Analysis

Universit y of Alabama in Huntsvill e USLI PDR

31

• CRW Drift Model

– Assumes:

• Apogee is directly above the launch rail
• The parachute does not open immediately
• The drift distance stops once a component

lands

• Horizontal acceleration is solely based on

relative velocity

• Drogue parachute is negligible once the

main is fully deployed

UAH SLI PDR

Vrelative Wind Speed (mph) mph 5 mph 10 mph 15 mph 20 mph RASaero Drift Distance (ft.) 0.023 544.3 1088.5 1625.8 2153.6 CRW Model Drift Distance (ft.) 543.2 1088.4 1624.9 2153.1

3/5/2018

• CRW Monte Carlo Analysis

– Varies coefficient of drag and apogee – Cases run at constant 0, 5, 10, 15, and 20 mph winds

Drift Analysis Cont.

University of Alabama in Huntsville USLI PDR 32

Largest Drift at ~685 ft. Largest Drift at ~2738 ft.

3/5/2018

• Ground station written in MATLAB

– Receives GPS sentences – Writes raw data and parsed data to separate files – Sends signal to rocket to deploy payload – The rover will transmit all saved sensor data to the ground station – Ground station will save rover data for post processing

Ground station

University of Alabama in Huntsville USLI PDR 33 3/5/2018

• System
• CRW uses a circuit for tracking and payload deployment

– consists of an Xbee Pro S3B RF module, a Teensy MCU, and an Adafruit MTK339 GPS Chip

• Xbee transmits GPS coordinates to a receiver connected to the

ground station laptop.

• Str

Structure In Integration

• 3D printed mount to secure tracker and its essentials within the

transition section of the rocket.

• Three axis security and battery retention to ensure

components are kept in tact

GPS Tracking

University of Alabama in Huntsville USLI PDR 34 3/5/2018

Deployment Electronics

University of Alabama in Huntsville USLI PDR 35

• Payload Deployment

Electronics Schematic

– Arduino-like MCU – Xbee Pro S3B RF Module – Adafruit GPS Module – Hot Wire

3/5/2018

• Operated remotely from ground station
• Teensy MCU receives signal to power hot wire

– Hot wire cuts fishing line holding piston spike in place – Releases spike and punctures CO2 cartridge to deploy rover

Deployment Electronics

University of Alabama in Huntsville USLI PDR 36 3/5/2018

Recovery ry Avio vionic ics Su Subsystem

• 2 PerfectFlite StratoLoggerCF altimeters; each with a

9V battery and SPDT momentary activation switch

• 4 Safe Touch terminals, E-matches, and black powder

charges

• Full

ll red edundancy in in avio ionic ics and ign ignit itio ion

Avionics

University of Alabama in Huntsville USLI PDR 37 3/5/2018

• Normally Closed SPDT Pull Pin

Microswitch – Prevents detonation during assembly – Helps preserve battery life

• Primary Drogue charge fired at

apogee – Secondary fired one second after

Avionics

University of Alabama in Huntsville USLI PDR 38

• Primary Main fired at 600 ft.

– Secondary fired at 550 ft.

• Primary charges are roughly 3.0g

for main and 2.25g for drogue Secondary charges are 0.5 g larger than primary

3/5/2018

SIM IMULATIONS

University of Alabama in Huntsville USLI PDR 39 3/5/2018

• Coefficient of Drag poorly translated from

subscale to full scale

– Full-scale Test Flight 1 – 6,893 ft.

• Resulting apogee broke 5600 ft. waiver
• Motor changed

to Aerotech L1520T

Motor Change

University of Alabama in Huntsville USLI PDR 40 3/5/2018

Motor Description

• Aerotech L1520T-PS
• Burn Time: 2.4s
• Max Thrust: 396.85 lbf
• Average Thrust: 352.45 lbf

University of Alabama in Huntsville USLI PDR 41 3/5/2018

• Wet Mass – 41.1 lbs.
• Dry Mass – 32.6 lbs.

Mass Budget

University of Alabama in Huntsville USLI PDR 42

Component Name Weight (lb.) [All weights include hardware] Fairing Section Nose Cone 2 Nose Cone Electronics 1 Fairing Body Tube 3.21 Rover 7 Inner Transition 1 Piston Bulkhead 0.693 CO2 System 0.312 Transition Bulkhead 1.34 Piston 0.811 Transition 0.566 Tracker 0.191 Forward Coupler 0.59 Forward Coupler Bulkhead 0.356 Forward Airframe Forward Body Tube 1.846 Main Parachute 1.6 Shock Cord 0.356 Av Bay Assembly 3.02 Aft Airframe Aft Body Tube 2.42 Fins (x4) 0.955 Drogue Parachute 0.183 Shock Cord 0.301 Aft Bulkhead 0.281 Fin Can 0.776 Motor Retention Ring/Thrust Plate 0.296 Motor Case 2.226 Total 31.1 Ballast 1.5 Ballasted Total 32.6

3/5/2018

Flight Prediction

University of Alabama in Huntsville USLI PDR 43 Apogee – 5116 ft. @ 18.1 sec. Main Deployment – 59.7 sec. Motor Burnout – 2.6 sec. Recovery – 121 sec. 3/5/2018

• OpenRocket Simulation (wind)

Fli light Prediction (W (Win ind)

University of Alabama in Huntsville USLI PDR 44 3/5/2018

• RASaero Simulation (wind)

Fli light Prediction (W (Win ind)

University of Alabama in Huntsville USLI PDR 45 3/5/2018

Stability Margin

University of Alabama in Huntsville USLI PDR 46

Burnout – 3.2 cal. Rail Exit – 2.52

3/5/2018

Monte Carlo Sim imulation

3/5/2018 University of Alabama in Huntsville USLI PDR 47

Measure Value (ft.) Mean 5509.18 Median 5505.9

• Std. Dev.

167.65 Max Altitude 6203.08

• Min. Altitude

4930.77

• 1-D method of analysis
• Cd = 0.34
• Varied conditions
• Cd ± 5
• Vehicle mass ± 2.5
• Prop. mass ± 5
• Case mass ± 2.5

Launch Conditions for Flight 1 Date February 24th, 2018 Location Samson, AL Wind ~6 mph Temperature 89°F Motor Aerotech L1420R Launch Angle 2° Projected Altitude 5626 ft. Actual Altitude 6893 ft.

Full-scale Flight Test 1

University of Alabama in Huntsville USLI PDR 48

• Apogee at 23.5 seconds
• Resulted in Motor Change
• Not a qualifying fly
• Nose Cone detached during main parachute deployment

3/5/2018

Full-scale Flight Test 1

University of Alabama in Huntsville USLI PDR 49

Key Flight Components Wet Mass (lb) Stability Margin (cal.) T/W Cd 41.2 2.44 11.1 0.34

3/5/2018

Full-scale Flight Test 2

University of Alabama in Huntsville USLI PDR 50

Launch Conditions for Flight 2 Date March 3rd, 2018 Location Samson, AL Wind ~6 mph Temperature 80°F Motor Aerotech L1520T Launch Angle 0° Projected Altitude 5131 ft. Actual Altitude 4736 ft.

• Apogee at 19.3 seconds
• Slight weathercocking (~10°)
• Qualifying flight
• Successful flight and recovery

3/5/2018

Full-scale Flight Test 2

University of Alabama in Huntsville USLI PDR 51

Key Flight Components Wet Mass (lb) Stability Margin (cal.) T/W Cd 40.1 2.76 8.75 0.33

3/5/2018

LAUNCH PROCEDURES

University of Alabama in Huntsville USLI PDR 52 3/5/2018

• Full scale launch procedures have

been implemented and continuously improved

• Minimizes time assembling at field

– Allows team to have safety in terms of time

• Field operations are split between

sub-teams to be done simultaneously

– Verification signatures required for each sub- team’s sections – Step-by-step process that begins with packing and assembling the day before the launch

Launch Day Procedures Overview

3/5/2018 University of Alabama in Huntsville USLI PDR 53

• Loading of energetics is

reserved to the last minute before check out

• Ejection charges and motor

installation will be performed by team mentor

• Safety monitor delegates tasks

and oversees all assembly procedures

Launch Day Procedures

3/5/2018 University of Alabama in Huntsville USLI PDR 54

Pre-Launch Procedure Overview

3/5/2018 University of Alabama in Huntsville USLI PDR 55

Pre Travel

Recovery Harness Preparations Rover Preparation Forward Assembly Procedures

At Field Assembly

Charge Preparation Rocket and Payload Assembly Pack Items for Travel Recovery Electronics Preparations Verify Final Configurations

Check Out and Launch

Motor Installation Charge Installation

Check out with RSO Launch

• Payload

– Risk of payload escaping fairing due to main parachute rapid deceleration. – Risk of Deployment system unintentionally triggered – Risk of Nose Cone retention system triggered unintentionally

• Vehicle

– Weather cocking (SM>2.0)

Safety Concerns

3/5/2018 University of Alabama in Huntsville USLI PDR 56

• Payload

– Switched from shear pins to 0.5 in. aluminum pins powered by solenoids.

• Vehicle

– Ballasted to have lower stability margin closer to 2.4 – New simulations show better altitude results

Mit itigations for r current concerns

3/5/2018 University of Alabama in Huntsville USLI PDR 57

• Fairing Drop Test

– Simulating a deceleration equal to or more than that of the parachute opening

• Results

– Test can produce forces that sheared nylon pins – New retention method have been verified by the test before second flight.

Completed Tests

3/5/2018 University of Alabama in Huntsville USLI PDR 58

• Vibration Tests are changed to Drop test

– Drop test of the Deployment system – Drop test of the solenoid pin system – Drop test of Rover

• Rover Operational test

– Software trials are currently underway – Tests are done as new parts arrive

Future Testing

3/5/2018 University of Alabama in Huntsville USLI PDR 59

PAYLOAD

University of Alabama in Huntsville USLI PDR 60 3/5/2018

• Used for initial test flights
• Foam added to meet proper dimensions of rover
• Tethered to U-bolt in transition and Eyebolt on

Simulator, covered by fairing

Mass Simulator

3/5/2018 University of Alabama in Huntsville USLI PDR 61

• 5 Plates of Aluminum 6061-T6
• Sidewalls 0.25 in. thick
• Base, front, and back plates 0.125 in. thick
• When assembled, 12 x 4 x 3.125 in.
• Assembled using 2-56 and 4-40 steel

screws

• Construction delayed

– McMaster-Carr sent wrong size plates – Machinist and Equipment availability limited

Chassis

3/5/2018 University of Alabama in Huntsville USLI PDR 62

• Spokes – Aluminum 6061-T6

– 0.25 x 0.5 x 5.875 in. – Three 6 ft. long bars cut into 5.875 in. to make 36 spokes

• Hinges – Aluminum 6061-T6

– 0.25 x 0.25 x 0.75 in. – Ordered longer bars and cut to 0.75 in.

• Spoke Feet – 3D printed ABS

– Rectangular hole 0.25 x 0.5 in. – Reprint needed because it did not properly fit due to shrinkage

Wheel Assembly

3/5/2018 University of Alabama in Huntsville USLI PDR 63

• Milled out of 0.25 in. thick Aluminum

6061-T6

• Pocketed excess aluminum to save

weight

• Machinist and equipment availability

delayed construction until after FRR

• Extension springs connected to spoke

and spring on opposite side using braided fishing line

• Diameter: Integrated 5.7 in., Deployed

16 in.

Wheel Assembly

3/5/2018 University of Alabama in Huntsville USLI PDR 64

• 3D printed ABS using Fortus in UAH machine shop
• 11 x 0.75 x 0.25 in.
• Torsion springs fit properly as shown by testing

Stabilizing Arm rm and Hin inge

3/5/2018 University of Alabama in Huntsville USLI PDR 65

• 3D printed using Fortus in UAH machine shop
• Fixed lid bolted to chassis and houses solar panels
• Sliding lid driven by motor with 3D printed gear
• Has been printed, but waiting on solvent bath
• 12 x 4 x 0.5 in. when assembly is closed
• 12 x 7.25 x 0.5 in. when assembly is open

Lid

3/5/2018 University of Alabama in Huntsville USLI PDR 66

• 3D printed ABS using Fortus in UAH machine shop
• 11.5 x 3.75 x 2 in., tight fit in chassis
• Some changes needed:

– One additional support – Holes added for electronics and assembly

Electronics Tray

3/5/2018 University of Alabama in Huntsville USLI PDR 67

• Used for initial testing of motors and other electronics
• Proved functionality of stabilizing arm
• Showed correlation between motors and accelerometer
• Electronics initially tested using breadboards

Hardware in in the Loop Test Model

3/5/2018 University of Alabama in Huntsville USLI PDR 68

• Camera has own SD card, only powered by Arduino
• Solar Panel does not charge battery, but powers LED

Updated Ele lectronics Blo lock Dia iagram

3/5/2018 University of Alabama in Huntsville USLI PDR 69

Updated Power Budget

3/5/2018 University of Alabama in Huntsville USLI PDR 70 Part Current (mA) Voltage (V)

• Adj. Current

(mA) Duty Cycle (%) Time (hr) Capacity (mWh) Arduino Mega 0.17 5.00 0.37 100 2.50 2.13 Camera 350 5.00 756 10.0 2.50 438 GPS 53.0 3.30 173 20.0 2.50 133 IMU 0.35 3.00 1.26 100 2.50 2.63 Press/Temp 0.36 3.30 1.18 17.0 2.50 3315 Wheel Motors 650 12.0 585 20.0 2.50 3510 Lid Motor 360 5.00 778 5.00 2.50 486 Radio Transmit 229 3.30 749 10.0 2.50 189 Radio Idle 44.0 3.30 144 90.0 2.50 327 DataLogger 100 3.00 360 10.0 2.50 75 Power Required 8478 Li-Po Battery 2600 10.8

• 100

1 28080 Safety Factor 3.31

• Changes since CDR:

– Wheel Assembly decreased – Stabilizing arm and lid assembly increased

Mass Budget

3/5/2018 University of Alabama in Huntsville USLI PDR 71

Component Mass (lbm.) Chassis 2.0 Wheel Assembly (2) 2.1 Lid Assembly 0.8 Stabilizing Arm Assembly 0.3 Electronics 1.3 Fasteners & Adhesives 0.5 Total 7.0

Software Flow

3/5/2018 University of Alabama in Huntsville USLI PDR 72

• Written in the Arduino IDE
• Developed in C++
• Incorporates various Adafruit libraries for the chosen sensors
• Using SPI, I2C, and UART to communicate with various sensors

Software Flow

3/5/2018 University of Alabama in Huntsville USLI PDR 73

REQUIREMENTS VERIFICATION

University of Alabama in Huntsville USLI PDR 74 3/5/2018

• Met and documented all NASA Launch Vehicle

Requirements

• Safety requirements require a signoff in the SOPs
• Derived Requirements:

– DV-001: Nose cone must remain attached throughout launch, demonstrated in fairing drop tests and flight test 2 – DV-003: Safely transfer load path from 4 in. to 6 in. body tube, demonstrated from FEA on transition insert and flight tests

• All other requirements can be found in document

Launch Vehicle Requirements Verification

3/5/2018 University of Alabama in Huntsville USLI PDR 75

• E-002 & E-003 – For deployable rover, the rover shall

deploy from the internal structure of the launch vehicle via trigger

• E-004 & E-005 – For deployable rover, the rover shall

autonomously move at least 5 ft from the launch vehicle and deploy the solar panels

• All requirements verified through demonstration –

Operational tests will be done on March 7th and Deployment tests on March 11th

Payload Requirements Verification

3/5/2018 University of Alabama in Huntsville USLI PDR 76

• DP-010 - Rover shall be able to take temperature, pressure

measurements, as well as images – Demonstration verified – The successful operation of the sensors were demonstrated by the preliminary operational test.

• DP-009 – Rover shall be able to retract the lid, covering the

solar panels – Will be verified through demonstration after obtaining lid – The mechanism that opens the lid of the rover will be able to close the lid as well, as demonstrated by the initial

• perational testing March 9th

Payload Requirements Verification

3/5/2018 University of Alabama in Huntsville USLI PDR 77

• DP-012 – Rover shall successfully navigate the

launch field despite weather or physical conditions of the field

– Will be verified through testing & demonstration – Rover will have folding wheels that expand to three times the initial diameter. The wheels will be tested on a variety of surfaces and demonstrated in a full scale flight test on March 9th.

• More verifications found in document

Payload Requirements Verification

3/5/2018 University of Alabama in Huntsville USLI PDR 78

PROGRAM MANAGEMENT

University of Alabama in Huntsville USLI PDR 79 3/5/2018

Timeline

University of Alabama in Huntsville USLI PDR 80 3/5/2018

• Upcoming Milestones

– FRR Presentation (15 March 2018) – Launch in Childersburg (10 March 2018) – Electronics Deployment Testing (7 and 8 March 2018) – Full Rover Testing (5 to 9 March 2018) – Launch Week (4 April 2018)

▪ Dynetics Tour (4 April 2018) ▪ Rocket Fair (6 April 2018) ▪ Competition Launch (7 April 2018)

Timeline

University of Alabama in Huntsville USLI PDR 81 3/5/2018

Budget

University of Alabama in Huntsville USLI PDR 82 3/5/2018

$- $1,000.00 $2,000.00 $3,000.00 $4,000.00 $5,000.00 $6,000.00 Airframe Electronics Recovery Motors Rover Structure Rover Electronics Total Cost

Total Full Scale Budget

Budget Summary Spent Budget Summary Budgeted $- $500.00 $1,000.00 $1,500.00 $2,000.00 $2,500.00 Airframe Electronics Recovery Motors Rover Total

Launch Vehicle On The Pad Budget

Launch Vehicle Spent Launch Vehicle Budgeted

Event Date Type of Engagement Individuals impacted or expected Girl’s Science and Engineering Day September 23, 2017 Direct Interaction 80 AIAA Holy Family School Engineering November 10, 2017 Direct Interaction 64 Cub Scout STEAM Camp December 20-22, 2017 December 27-29, 2017 Direct Interaction 65 FIRST Lego League Alabama State Competition January 20, 2018 Direct Interaction 62 Science Olympiad March 3, 2018 Direct Interaction 34

Outreach

University of Alabama in Huntsville USLI PDR 83 Event Date Type of Engagement Individuals impacted or expected Girl’s Science and Engineering Day September 23, 2017 Direct Interaction 80 AIAA Holy Family School Engineering November 10, 2017 Direct Interaction 64 Cub Scout STEAM Camp December 20-22, 2017 December 27-29, 2017 Direct Interaction 65 FIRST Lego League Alabama State Competition January 20, 2018 Direct Interaction 62 Science Olympiad March 3, 2018 Direct Interaction 34 Total Number 225 3/5/2018

• FIRST Lego League Alabama State

Championship

– Sensor Workshop

▪ Buzzer, flashing LEDs, Light Sensor, Rotary Angle Sensors ▪ Xbee Radios messaging

• Science Olympiad

– Battery Buggy and Mousetrap Vehicle Events

▪ Construction reviews, scoring event, discussion of vehicle runs

Outreach

University of Alabama in Huntsville USLI PDR 84 3/5/2018

Questions?

3/5/2018 University of Alabama in Huntsville USLI PDR 85