NASA USLI Flight Readiness ReviewUniversity of Alabama in Huntsvil le
Charger Rocket Works
March 13, 2019
Agenda
Introductions and Team Overview
Mission Objectives
Changes Since CDR
Vehicle Overview
Payload Overview
Program ManagementSafety
Testing and Verification
Outreach
Budget
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 2
IntroductionsZachary Ruta, Program Manager
Hope Cash, Safety Officer
Marcus Shelton, Chief Engineer
William Hankins, Vehicle Lead
Colton Connor, Payload Lead
Tanner Schmitt, Deputy Safety Officer
Brooklyn Kirkwood, Vehicle Safety Lead
Connor Gisburne, Payload Safety Lead
Dr. David Lineberry, Faculty Advisor
Jason Winningham, NAR/TRA Mentor, Level III Certified
Bao Ha, Graduate Student Teaching Assistant
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 3
Mission Statement
The objective of the Charger Rocket Works (CRW) team is to construct a safe and successful Level 2 high
powered rocket with deployable unmanned air vehicle as a payload through applying engineering
judgement and skills. Additionally, CRW will engage with the community in STEM education events and
promoting rocketry to diverse groups.
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 4
Mission Objectives
Vehicle: The rocket will deliver the payload to an altitude of approximately 4800 ft., descend safely and within the Mission Performance Requirements set by NASA, and be recovered in a reusable state.
Payload: The payload will deploy from the rocket, fly to a target location, and drop a beacon on target zone all while meeting the desired NASA requirements for the USLI competition.
Safety: Comprehensive safety methods will be implemented in all aspects of fabrication, testing, and launches of hardware using in-depth analysis and written procedures and checklists.
Outreach: The CRW team will meet a minimum of 200 students through hands-on activities as per the request of NASA and will promote STEM and rocketry to diverse groups.
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 5
Vehicle
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Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 7
Vehicle Overview
Parameter Value
Vehicle Length 124in
Body Tube Diameter 6in
Vehicle Weight 50.095lb
Motor Selection L1420R
Predicted Apogee 4982ft
Wednesday, March 13, 2019
Vehicle Overview
1
2 4
Pre-Launch
Launch
5
Drogue Deployment at Apogee
Main Deployment
3
Landing Rocket assembled Rocket placed on pad
Drogue deployment charge at apogee
Backup drogue deployment charge at apogee plus 1 sec
Motor ignited Vehicle accelerates
Main parachute deployment at 600 ft AGL
Backup main deployment at 550 ft AGL
Payload deploys Rocket recovered
UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 8
Vehicle Changes since CDR
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 9
Key Switch has been added to nose cone such that nosecone avionics can be powered on externally
Conserves battery life and ensures signal will not be lost during flight
Tracker bracket redesigned to allow more mounting surface for the avionics
Is now a 3D printed part
3D printed component infill increased from 25% to 35% to increase strength
Nose Cone and Body Tube
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 10
Body tube cut from 60in G12 fiberglass tube via wet-saw
Metal tipped 4:1 ogive nosecone purchased from Madcow
Bulkhead and key switch holes hand drilled
Upper Airframe Bulkheads
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 11
Upper airframe bulkhead functions as recovery retention system and payload attachment bulkhead
Drogue parachute attaches to upper airframe bulkhead via eyebolt
Nosecone Bulkhead functions as nosecone avionics and payload attachment bulkhead
Diameter: 6 in
Aluminum thickness: 0.25 in
Fixed to body tube with six #4-40 screws
CNC machined from 6061-T6 Aluminum
Nosecone Bulkhead
Upper Airframe Bulkhead
Coupler Coupler 13 in. long with 1 in. switch band cut from excess body tube G12 fiberglass bulkhead holes drilled using 3D jig and drill press SPST key switches used to power avionics on pad Keys not removable when system powered off Key locks printed to prevent accidental powering during transport to pad
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 12
Lower Body Tube
Cut from a 60in G12 fiberglass tube on a wet-saw
Fin slots cut using plunge router
Holes for bulkhead and fin can were hand drilled
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 13
Aft Bulkhead
Functions as recovery retention system
Main parachute attached via eyebolt
Diameter: 6 in
Aluminum thickness: 0.25 in
Fixed to body tube with 6 #4-40 screws
CNC machined from 6061-T6 Aluminum
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 14
Fins and Fin Can
Fins:
Adjusts CP for stability
G10 fiberglass sheet
Cut with wet saw
Through-wall mounting
Installed with eight #4-40 bolts per fin
Fin Can:
3D printed in-house with PLA
Fixed to airframe with eight #4-40 bolts
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Thrust Plate
Transfers force from motor
CNC machined from 0.190 in. 6061-T6 Aluminum
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 16
Retention Ring
Load Path:Boost phase
Motor case
Thrust plate
Body tube
Coast phase
Retention ring retains motor
Wednesday, March 13, 2019
3D printed from ABS plastic
Retained the motor during coast phase of the flight
Attached to the fin can using 2 #4-40 screws
UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 17
Recovery System
Drogue ParachuteFruityChutes CFC-181 in. tubular nylon, 50 ft.Terminal Velocity: 83.1 ft/s
Main ParachuteFruityChutes IFC-1441 in. tubular nylon, 50 ft.Terminal Velocity: 11.2 ft/s
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 18
Avionics
Two Stratologger CF
Drogue: Apogee / Apogee + 1s
Main: 600 ft. / 550 ft.
Inertial Measurement Unit (IMU):
Features accelerometer, gyroscope, magnetometer, and pressure sensor
Located in nose cone
Featherweight Raven3 altimeter
Records pressure (altitude), acceleration, and temperature
Located in nose cone
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 19
GPS Tracking
XBee-Pro S3B Radio Transmitter with Antenova GPS
Located in nose cone
Powered by CR123 lithium ion battery
Used with success on previous CRW flights
Transmitting frequency: 902 to 928 MHz
Transmits to distances up to six miles away
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 20
Mass Statement and Margin
Wet Mass: 50.095 lbm
Burnout Mass: 39.995 lbm
Difference from CDR estimates: 2.874%
Some 3D prints strengthened with greater infill percentage
Added nose cone tracker and avionics assembly
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 21
Flight Profile
Predicted Apogee: 5012 ft.
Max Velocity: 582 ft/s
Max Acceleration: 249 ft/s2
Velocity off Rail: 57.6 ft/s
Thrust to Weight Ratio: 6.91
Time of Flight: 99.7 s
Time to Apogee: 18.4 s
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Flight Profile
Variable Wind Speeds:5 MPH: 5009 ft.
10 MPH: 5021 ft.
15 MPH: 5006 ft.
20 MPH: 4963 ft.
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Trajectory Verification
Rocksim: 5012 ft.
OpenRocket: 4963 ft.
RASAero II: 4999 ft.
Custom Code: 4982 ft.
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Trajectory Verification
Variables:Motor Impulse (±1%)
Rocket Mass (±0.25 lbf)
CD Error (±0.04)
Temperature (±15 oF)
Wind Speed (±2 MPH)
Normal Distribution
Average: 4982.7 ft.
27.5% fall outside CRW Requirement
0% fall outside SLI Requirement
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Stability Margin
CP location: 91.1 in.
CG location: 77.2 in.
Stability Margin: 2.25
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Kinetic Energy
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Vehicle Component Mass [lbm] Kinetic Energy [lbf-ft]
Upper Airframe 17.56 34.20
Coupler 4.35 10.47
Lower Airframe 15.85 30.87
Descent Time
Vehicle Flight Demonstration:Total descent time: 80s
Apogee was 5017 ft.
Competition Launch:Expected descent time:
78.5s
Apogee Target: 4982.7 ft.
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Drift Analysis
Total descent time: 80.0 s
Drift under 20 MPH: 2340 ft.
Assumes:
Apogee occurs over launch pad
Wind is 1D and constant
Parachute opening times are considered
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Vehicle Demonstration Flight
February 9, 2019 at 12:37pm
Mean Temperature: 42 °F
Party Cloudy
Winds: 9 MPH NNE
Predicted Apogee: 4664 ft
Aerotech L1420 used
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Vehicle Demonstration Flight
Apogee reached: 5017 ft
Drogue deployed at apogee
Main deployed at 600 ft AGL
Descent velocity
83.1 ft/s under drogue
11.2 ft/s under main
Drift from rail to landing: 924 ft
Time to apogee: 18.3 s
Time of descent: 80 s
Rail to landing drift: 924 ft
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 31
Vehicle Demonstration Flight
Predicted apogee was low due to inaccurate drag coefficient
Raven3 accelerometer resolution was too low to accurately estimate drag coefficient
Estimated drag coefficient equal to 0.375 using Rocksim
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y = 3E-05x + 34.378R² = 0.6311
0
10
20
30
40
50
60
0 50000 100000 150000 200000 250000 300000 350000 400000
Acc
ele
rati
on
(ft
/s2)
Velocity2 (ft2/s2)
0
1000
2000
3000
4000
5000
0 20 40 60 80 100 120
Alt
itu
de
(ft
)
Time (s)
Preflight
Actual
Payload
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Beacon Release
Use video feed to confirm location
Send command to release beacon
Payload Concept of Operation
Wednesday, March 13, 2019
UAV Flight
Vehicle Landing
Pre-Flight
Wait for affirmation to deploy
Check for GPS lock Check for Ground
station connection Check video
feedback
Autonomous flight to the FEA (100 ft Ascent, flight to the GPS location of FEA)
Piloted landing on to the FEA Fail safe return to last way point when
communication loss
Payload Deployment2 Send command to fire black
powder charges
Piston: Pushes the deployment sheath and the nose cone out of the body tube
Deployment sheath: Houses the UAV and unfolds to allow UAV to fly when pushed out of the body tube by piston
1
3
4
5
6 Piloted flight away
front the FEA
Fly away
UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 34
Changes since CDRMounting plates printed from PLA instead of machined aluminum
UAV operates under one battery instead of two
Deployment sheath has a carbon fiber beam instead of aluminum
Added spring steel
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 35
Upper and Lower Mounting Plates
Mounting plates printed out of PLA
Heat-set inserts to reduce amount of hardware
PLA reduces weight compared to aluminum
Act as UAV structureAll electronics and brackets connect to the
platesUpper mounting plate dimensions are
5.125 x 9.7 inchesLower mounting plate is 2.25 x 5.5 inches
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 36
Battery Bracket
Bent from aluminum sheet metal
Attaches to the upper mounting plateLocated at the bottom of the UAV
Encases the undercarriage of the UAVHouses most electronics and wiring
Bracket is 2.5 x 6 inches
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 37
Power Switch
Turns off UAV during vehicle flightCuts radio transmission to the
UAV
Reduces power loss by UAV
Normally closed switch powers on after deployment as the arm unfolds
Pressing of the arm against the switch powers of the UAV
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 38
Arm Spring System
Located on the side of the upper mounting plate
Spring system is activated when UAV is deployed
Arms are pulled apart when they are clear of the sheath
Stopping posts align the arms for flightSpring helps lock the arms into
place
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 39
Beacon Release System
Located on the back of the UAV
Beacon holder restricts horizontal movement Solenoid restricts vertical movement
Solenoid fires, releasing beacon from the UAV on command
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 40
UAV Electronics
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Flight Computer
Electronics Speed Controllers
Beacon Release Solenoid
FPV Video System
Telemetry Transceiver
Deployment Controller
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 42
Latch solenoid
Externally accessible power switch
Enclosed radio receiver and controller
Payload Integration with Vehicle
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 43
Ground Systems Interface
Mission Planner, an open source ground controls software used to establish telemetry and command the UAV
A joystick mapped to throttle, pitch, roll, yaw to fly the UAV
Failsafe for low battery, communication loss and GPS loss in place
Easily accessible command option for landing, arming , disarming and beacon release mapped to buttons on the UAV controller (joystick)
Camera link established through Ethernet connection to GrandStream encoder
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Payload Demonstration Flight Plans
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 45
Payload Demonstrate Flight – March 9
Objective is to retain payload and deploy the UAV
No plans to fly UAV off of sheath
Plan to verify connection between UAV and ground station through live telemetry; this will also verify that the sheath unfolds, that the arms move to the correct position, and that the UAV receives power
Plan to verify ability to command the UAV by using UAV controller to release beacon while on the sheath
Safety
Safety Committee Focus for FRR
Final Safety Training
Additional Hazard Analysis of Environmental Concerns
Updated Mitigation Verifications for Risk and Hazard Assessment
UAV SOP Development for Demonstration and Testing
Development and Implementation of Full Scale Launch SOP
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 47
Safety Training
Wednesday, March 13, 2019
Number Training Topic Date
- CPR/AED/First Aid 10/4/18 – 10/19/18
1 Basic Emergency Procedures 10/18/18
2 Black Powder Testing and Motor Safety 10/30/18
3 Outreach Safety 11/1/18
4 Sub-Scale Launch Safety 11/15/18
5 Test and Demonstration Safety 1/22/19
6 Full-Scale Launch Safety 2/7/19
7 Basic Lab Safety 2/14/19
8 UAV Safety 2/21/19
9 UAV Laws and Regulations 3/5/19
UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 48
Environmental Hazards
Environment vs System
Surrounding Land
Weather
Crowd
System vs Environment
Pollution/Litter
Surrounding Land
Airspace
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 49
Checklists and SOPs
Wednesday, March 13, 2019
Vehicle UAV
Sub-Scale Black Powder Demonstration Deployment Controller Demonstration
Sub-Scale Launch Thrust Test
Shock Cord Tensile Test Hover Demonstration
Fin Can Stress Demonstration Flight Range Demonstration
Kinetic Energy Drop Demonstration Deployment Ejection Demonstration
Black Powder Demonstration Field Deployment and Flight
Full-Scale Prep and LaunchLaboratory Checklist: LiPo Battery Charging
Procedure
UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 50
Final Launch SOP Notes
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Section Titles
Red Triangle for
Immediate Safety Note
PPE Reminder
Sections to be Conducted in
Parallel
Red Procedure
Note Reminder
Effect of Missing a
Step
Signatures at Completion of Section
Full Scale SOP: Pre-Launch
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 52
Pre-Travel Preparation Procedures
At Field Procedures
Upper Airframe Assembly Checklist
Ejection Charge Installation
Motor Installation
Final Checkout
Pad Checklist
Nosecone Checklist
Piston Checklist
UAV ChecklistPayload Integration
Checklist
Coupler Checklist
Lower Airframe Assembly Checklist
Recovery Checklist
Drogue Installation (Upper Airframe)
Main Installation (Lower Airframe)
Post-Flight Checklist
UAV FLIGHT OPS
Final Checklist
Full Scale SOP: UAV Deployment
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 53
Post-Flight Checklist
Hand Over of Operations to Payload
Red Team
Deployment Checklist
UAV Flight Checklist
Final UAV CloseoutEmergency Landing
Procedures
Program Management
Testing Overview
6 Vehicle TestsRecovery Charge Tests
Sub Scale and Full Scale Flight Demonstrations
Recovery Harness Tensile Stress Test
Drogue Deployment Kinetic Energy Test
5 Deployment TestsTwo Electronic Tests
Payload Ejection Test
Orientation Test
Integrated Deployment Test
6 Payload TestsTwo Electronic Component Tests
One Propulsion System Thrust Test
Three Flight Tests
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 55
Vehicle Testing ProgressTest Name Description Status Outcome
Subscale Recovery
Charge Test
Verify black powder deployment
charges adequate to deploy
parachutes
Complete Successful
Subscale Flight Test Complete Successful
Full-Scale Recovery
Charge Test
Verify black powder deployment
charges adequate to deploy
parachutes
Complete Successful
Recovery Harness Stress
Test
Determine if the shock chord will
maintain structure at flight
loading
Complete Successful
Drogue Deployment
Drop Test
Determine if deployment system
shear pins remain intact during
flight loading
Complete Successful
Fin Can Stress Test
Determine if flight forces would
cause damage to removable fin
can
Complete Successful
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 56
Deployment Testing Progress
Test Name Description Status Outcome
Deployment Electronics
Test
Verify deployment electronics
function as commanded.Complete Successful
E-Match Deployment
Test
Verify deployment electronics
successfully ignite e-match.Complete Successful
Deployment Black
Powder Test
Verify deployment black powder
charge can successfully deploy
dummy mass
Incomplete
Deployment
Orientation Testing
Verify sheath can orient payload
on a variety of landing
orientations
Incomplete
Integrated Deployment
Test
Test deployment ejection and
payload orientation with payload.Incomplete
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 57
Payload Testing Progress
Test Name Description Status Outcome
FPV TestTest image quality, transmission
range of FPV Camera.Complete Successful
Telemetry Range TestVerify telemetry transmits at
required distancesComplete Successful
Integrated Propulsion
Test
Test thrust level of payload in its
flight configurationPartially Complete Partially Successful
Flight TestTest tethered and free flight of
vehicleIncomplete
Flight Endurance Test
Ensure payload has sufficient
power to meet requirements for
flight.
Incomplete
Flight Range TestingEnsure payload can fly required
distance with sufficient battery.Incomplete
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 58
Testing Spotlight – Deployment Test
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 59
Tested Deployment Ejection System
Stepped up charges from 0.5 to 1 to 1.5 to 2.25 grams of black powder
Ejected the deployment sheath fully, but caused damage to deployment system
Wednesday, March 13, 2019
Requirement
NumberRequirement Description Compliance Verification Plan Verification Status
NASA-5.5 Teams will abide by all rules set forth by the
FAA.
All applicable FAA regulations are accessible to the
team. The Safety Officer and Team Leadership are
responsible for ensuring CRW is in compliance with all
applicable FAA regulations.
Lists of the applicable FAA regulations are available to the team on the
CRW online sharing site. Team Leadership ensures all applicable FAA
regulations have been considered when in the design phase of the
project.
Inspection complete
UAH-V-01 The vehicle shall reach an apogee of 4800
feet within ± 250 feet
Simulations were used to predict an achieved altitude of
4806 feet. The subcale test flight was used to refine the
simulations.
Analysis
The team will use simulations and hand calculations to confirm that
vehicle will reach the required height.
Complete
The simulations predict the launch vehicle will
reach 4806 feet.
UAH-V-02 There shall be redundant, increasing black
powder charges in the event of initial
recovery system deployment failure.
Multiple increasingly powerful black powder charges
will be installed in the recovery system.
Analysis
The launch vehicle will incorporate redundant black powder charges.
Incomplete
The subscale rocket incorporated redundant black
powder charges. The full-scale rocket is awaiting
assemblly.
Requirement Verification & Compliance
UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 60
Verified using the method below
Validated through testing, demonstration, analysis, or inspection
Example displayed below
Outreach Events
Wednesday, March 13, 2019
Event DateStatus:
PurposeAnticipated Number of Individuals
St. Francis Borgia Regional High School
Oct. 12 Completed Present Rocketry Basics 37
Girls Science… Nov. 3 CompletedPresent about Friction and
Rocketry Basics166
First Lego League Nov. 10 CompletedInteraction with parents
and students72
Interactive Rocketry at Lexington High School
Nov. 28 Completed Present Rocketry Basics 174
Interactive Rocketry at Elkhorn Crossing School
Dec. 11 Completed Present Rocketry Basics 147
Eagle River High School Dec. 12 Completed Interaction with Students 26Canyon Crest Academy Dec. 20 Completed Engineering Design Activity 29
Science Olympiad Feb. 14 Completed Interaction with students 56UAH’s Take Your Daughters … Feb. 18 Completed Rocketry Basics Activity 90
Hewitt Trussville High School Feb. 22 CompletedPresent rocketry basics &
Open Rocket212
Ramsay High School Mar. 11 Planned Present rocketry basics 75Total Impacted 1,084
UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 61
Funding Status
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 62
Funding sources have not changed since CDR
New funding status displayed to the right
$550.00 refund to UAH USLI Foundation
Projected vs. Actual Expenditures
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 63
Wednesday, March 13, 2019
Future Events
UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 64
Deployment Re-TestingMarch 07 (Huntsville, AL)
Hover Test March 07 (Huntsville, AL)
Payload Demonstration Flight March 09 (Huntsville, AL)
Remaining Flight Testing March 11 – March 15
Questions
Appendix
Deployment Testing ProgressTest Name Update (12 March, 2019)
Deployment Black Powder Test Added 1 inch joint reinforcement to
add surface area of epoxy bond
between piston bulkhead and piston
shoulder. Settled on 2 gram black
powder charge.
Issues with solenoid, investigating
causes.
Deployment Orientation Testing Deployment testing has been
completed. The test was successful.
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 67
Payload Testing ProgressTest Name Update (12 March, 2019)
Integrated
Propulsion
Test
Test thrust level of payload in its flight configuration
Flight Test Tethered flight testing has begun. UAV has adequate
thrust to lift off. Problems with commanded take off
has prevented sustained hover.
Wednesday, March 13, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS 68