Critical Design Review University of Alabama in Huntsville Charger - - PowerPoint PPT Presentation
NASA USLI Critical Design Review University of Alabama in Huntsville Charger Rocket Works January 16 th , 2019 Agenda Introductions and Team Overview Mission Objectives Changes since PDR Vehicle Overview Payload Overview
University of Alabama in Huntsville Charger Rocket Works January 16th, 2019
Introductions and Team Overview Mission Objectives Changes since PDR Vehicle Overview Payload Overview Program Management Safety Outreach Budget Requirements Compliance
Wednesday, January 16, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS
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Zachary Ruta, Program Manager Hope Cash, Safety Officer Marcus Shelton, Chief Engineer William Hankins, Vehicle Team Lead Colton Connor, Payload Team Lead Tanner Schmitt, Deputy Safety Officer Jade Kirkwood, Vehicle Safety Lead Connor Gisburne, Payload Safety Lead Dr. David Lineberry, Faculty Advisor Mr. Jason Winningham, NAR/TRA Team Mentor, Level III Certification Bao Ha, UAH Graduate Student Teaching Assistant
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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.
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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-
diverse groups.
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Wednesday, January 16, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS
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Parameter Value Vehicle Length 124 in Body Tube Diameter 6.17 in Motor Selection L1420R Major Vehicle Materials Fiberglass, Aluminum, ABS Plastic Center of Gravity Location 76.13 in Center of Pressure Location 91.14 in
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1 2 4
Pre-Launch Launch
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Drogue Deployment at Apogee Main Deployment
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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
Upper airframe bulkhead redesigned to include payload hardware The main and drogue parachutes positions have been swapped Motor selection changed from 1520T to 1420R Extended lower body tube to accommodate Fin Can spars replaced with the fins Boat Tail converted to motor retention ring
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Bulkheads and thrust plate CNC machined Body tubes, nose cone, and fin material have arrived and are ready for alterations Parachutes have been selected and prepared for launch. One fin can has been printed but had failure point, will be reprinted Second part order ready to be submitted
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The upper airframe contains many important components The drogue parachute The payload bay The nose cone The tracker
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The selected nose cone is a 4:1 ogive nose cone from Madcow Rocketry The exposed length is 26 inches with a 6 inch coupler A blind hole will be tapped into the nose cone’s aluminum tip A threaded rod will be inserted into this hole The threaded rod will be used to secure the nose cone bulkhead, where the tracker and the payload’s deployment sheath attaches
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FEA was conducted to ensure upper airframe (UA) bulkhead could withstand loading FEA results indicate a generally good design, will require some hang testing UA bulkhead attached to upper body tube with six #4-40 bolts Eye bolt mounts through face of UA bulkhead Shock cord is attached to the eye bolt Payload deployment mechanism attaches to UA bulkhead
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2x G10 fiberglass bulkheads per end G12 fiberglass tube (not shown) G12 fiberglass switch band Twin threaded rod load bearing path Forged 1/4-20 eye bolts Redundant main and drogue ejection charges
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Coupler V4 Mk II
Twin redundant Stratologger CF Altimeters 2x SPST key switches control avionics Redundant main and drogue deployment charges Power supplied by 2x 9v lithium batteries
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http://www.perfectflite.com/SLCF.html https://www.digikey.com/p roduct-detail/en/c- k/Y101132C203NQ/CKN115 17-ND/484276 Load transferred from 1/4-20 eye bolts to bulkheads Upper and lower bulkheads are epoxied together From the bulkheads load is transferred through (2x) 1/4-20 304 SS threaded rods Washers and lock nuts used to secure all eye bolts and threaded rods
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Avionics mounted to fiberglass bulkhead suspended on threaded rods Altimeter mounted on standoffs with nylon screws Battery holders mounted with stainless steel screws Quick connectors allow easy removal and assembly of avionics
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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
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The lower airframe contains: The main parachute The motor The fin can assembly
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Fins: Adjusts CP for stability G10 fiberglass sheet Fabricated in-house Through-wall mounting Fin Can: Removed full spars since PDR 3D printed in-house Fixed to airframe with 8 #4-40 bolts
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Previous Current
Changes since PDR: Increased thickness Added cutouts Transfers force from motor Supported by FEA
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Previous Current
Fabricated in-house Retains the motor during the coast phase
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Load Path: Boost Phase Motor case Thrust Plate Body Tube Coast Phase Retention Ring retains motor
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
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25 motors simulated using OpenRocket Velocity off the rail, apogee, and stability off the rail were the three FOM
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Motor Manufacturer # of Grains Velocity off the rail (ft/s) Apogee (ft) Max Velocity (ft/s) Max Acceleration (g's) Stability
(cal) L1520T-P Aerotech 3 65.2 3719 509 7.3 2.82 L1390G-P Aerotech 3 60.2 3915 517 7.0 2.72 L1350-CS CTI 3 61.2 4500 564 6.6 2.80 L1420R-P Aerotech 4 63.4 4817 592 6.9 2.50 L1365M-P Aerotech 4 61.3 4965 594 6.4 2.55 L1395-BS CTI 4 63.3 5302 629 7.3 2.66 L2375-WT CTI 4 80.8 5463 687 11.6 2.73 L1115 CTI 4 62.6 5406 593 7.0 2.63
75mm case Total Impulse: 4603 N∙s Average Thrust: 1420 N Peak Thrust: 1814 N Burn Time: 3.2 s Propellant Mass: 2560 g / 5.6 lbm
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Aerotech L1420R
Projected apogee: 4806 ft Maximum velocity: 592 ft/s Maximum acceleration: 222 ft/s2 Thrust to weight: 7.01 Rail exit velocity: 55.5 ft/s Total flight time: 98.8 s
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Custom-made, two dimensional code showed less than 1% error compared to OpenRocket RASAero II predicted apogee at 500 feet above other codes
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10,000 iterations using the custom- made code Altered vehicle mass, body drag coefficient, and motor impulse Average value: 4831 feet Deviation: 211 feet Of the 10,000 runs, 23% fall 250 feet
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# of Runs (of 10,000) Apogee (ft)
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Stability of 2.43 off the rail Center of Pressure: 91.14 inches from leading edge Center of Gravity: 76.13 inches from nose
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System Component Mass (lbm) Mass Value Origin System Component Mass (lbm) Mass Value Origin Wing Nuts 0.005 SPEC 1/4"-20 Washer 0.004 SPEC 0.25" Button Head Torx Screw 0.001 SPEC 1/4"-20 Lock Nut 0.011 SPEC 0.50" Button Head Torx Screw 0.001 SPEC 1/4"-20 Shouldered Eyebolt 0.064 SPEC 1.25" Button Head Torx Screw 0.003 SPEC 1/4"-20 x 13" Threaded Rod 0.185 SPEC Drogue Parachute and Cord 0.955 MEASURED Battery Holder 0.120 CAD Nosecone Bulkhead 0.301 MEASURED Coupler Outer Bulkhead 0.227 CAD NoseCone 4.188 SPEC Coupler Inner Bulkhead 0.210 CAD Threaded Rod 0.089 SPEC Charge Well 0.009 CAD Tracker 0.031 MEASURED Coupler Body Tube 1.604 CAD Upper Body Tube 4.647 CAD Epoxy Plugs 0.001 CAD TOTAL 10.228 Terminal Block 2x2 0.005 MEASURED Aft Bulkhead 0.339 MEASURED Stratologger CF Altimeter 0.027 MEASURED Retention Ring 0.207 CAD #2-56 Locknut 0.002 SPEC Lower Body Tube 5.433 CAD #2-56 Longnut 0.5" 0.001 SPEC RMS-75/3840 Case with 1420R 10.057 SPEC #4-40 Locknut 0.002 SPEC #4-40 Locknut 0.002 SPEC #4-40 Locknut 0.75" 0.002 SPEC #4-40 Brass Heat Set Insert 0.001 SPEC #4-40 Standoff 0.001 SPEC #4-40 1-3/8" Socket Head Screw 0.004 SPEC #4-40 Pan Head Screw 0.000 SPEC Centering Rings 0.805 CAD Coupler Switch Band 0.101 CAD Fins 0.519 CAD TOTAL 4.653 #4-40 0.375" Socket Head Screw 0.001 SPEC Payload TOTAL 9.225 #4-40 1.00" Socket Head Screw 0.003 SPEC Thrust Plate 0.294 CAD Main Parachute and Cord 2.970 MEASURED TOTAL 23.022 47.129 Lower Airframe Total Mass: Upper Airframe Avionics Coupler
Drogue Parachute FruityChutes CFC-18 Classic Elliptical (CD =1.5) Terminal Velocity: 119 ft/s 30 feet tubular nylon (1”) Deploys at apogee, apogee + 1s Main Parachute FruityChutes IFC-144 Iris Ultra w/ Spectra Lines (CD 2.2) Terminal Velocity: 12.92 ft/s 50 feet tubular nylon (1”) Deploys at 600 ft, 550 ft
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Main Parachute Kinetic Energy
Part Mass KE Upper Airframe 19.80 lbm 46.21 lbf-ft Avionics Coupler 4.26 lbm 11.04 lbf-ft Aft Airframe 15.74 lbm 40.82 lbf-ft
Maximum drift: 2387 ft from launch pad Assumes constant, one-directional wind shear from apogee to touch down Does not account for parachute deployment time and effects
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Current Capabilities 3D printed parts Fin Can Retention Ring Machine Shop Access Bulkheads Thrust Plate Limited Finishing at JRC Readying components for Assembly
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Machine Shop access will be restricted after January 30th Machined part production has been prioritized to manufacture all parts which require the machine shop before January 30th Alternative options for part manufacturing are being considered
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Launched from Birmingham, AL on November 17 Launched at 11:30 a.m. Winds below 7 MPH Temperature averaged 640F 1010 Rail canted 40 N
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Flight Recorder Maximum Altitude Recorded (ft) Primary Stratologger 2047 Secondary Stratologger 2098 Raven3 2151 Average 2099 Standard Deviation 52
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500 1000 1500 2000 2500 10 20 30 40 50 60 70
Altitude (ft) Time (sec)
Primary Secondary
Apogee approximately 400 feet lower than OpenRocket prediction Total flight time ≈ 45 sec Apogee Main Parachute Deployment
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Successful deployment of drogue recovery charge Decent velocity ≈ 85 ft/s
y = -84.609x + 3215.8 R² = 0.9908 y = -85.727x + 3297.9 R² = 0.9863 500 1000 1500 2000 2500 10 12 14 16 18 20 22 24 26
Drogue Successful deployment of main recovery charge Decent velocity ≈ 38 ft/s Expected decent velocity was approximately 32 ft/s
y = -38.124x + 1699.9 R² = 0.9641 y = -37.253x + 1743.7 R² = 0.9058
100 200 300 400 500 600 700 800 900 25 30 35 40 45 50
Main
Max axial acceleration of 28 G’s Max lateral acceleration of 40 G’s
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Burnout Drogue Main Landing
Stratologger data matched against one- dimensional trajectory code. Drag coefficient could not be approximated from results. Possible re-flight in coming month,
Full Scale tests. Assessed accuracy of descent velocity predictions.
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Expected loads and decent rate in recovery far higher than anticipated. Apogee lower than anticipated Refined simulations based on data Flaws when 3D printing parts Redesign of 3D printing parts to minimize effects of flaws Flexing and errors when manufacturing parts Refined jig design and manufacturing methods Lost lock on GPS tracker in flight Developed methods to ensure power to GPS tracker in flight Improved rocket recovery methods if GPS tracker lock is lost
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Beacon Release
Use video feed to confirm location Send command to release beacon
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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 Deployment
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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
Spring mechanism for UAV arm unfolding: now supplemented by limit pins Added additional safety features to deployment controller Buzzer and LED added to relay arm/disarm status Added visible indicators to UAV design Switch to higher-capacity battery 4000mAh to 5000mAh battery Simplified piston latching mechanism COTS option adopted
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Custom retention mechanism COTS latch solenoid Previous Design New Design
Acquired parts Radio Range testing GPS testing FPV imaging testing Motor and speed controller compatibility with flight computer confirmation Q-Ground Control operation Performed material testing for orientation sheath
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Wednesday, January 16, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS
Updated CAD allows for better visualization of electrical component placement
Isometric View Bottom View
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Wednesday, January 16, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS
Upper mounting plate Manufactured from aluminum Main frame of UAV to which all components and brackets are fastened
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Wednesday, January 16, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS
Under Carriage Supports the majority of the UAV electrical components Aluminum
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Battery Brackets Functions as an encasement for the battery and protects the battery from impact with the ground Sheet Metal
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Telemetry Transceiver Bracket Supports and retains the telemetry transceiver Sheet Metal
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Wednesday, January 16, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS
Beacon Holder Bracket Secures the beacon holder to the upper mounting plate Sheet metal
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Wednesday, January 16, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS
UAV Arms Provide distance from the UAV body for the motors to have a larger combined surface area of thrust Carbon Fiber
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Wednesday, January 16, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS
A tension coil spring pulls the cable across arc limiting pins which act as the sheaves
UAV arm UAV arm Limiting pin Limiting pin Spring
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Component Voltage (V) Current (A) Power (W) Duty Cycle Supply Efficiency Power Draw (W) Flight computer 5.0 0.045 0.23 100% 90% 0.25 Camera 7.0 0.38 2.66 100% 90% 2.96 GPS 5.0 0.033 0.17 100% 90% 0.18 LED 5.0 .35 1.75 100% 90% 1.94 Transceiver 5.0 0.1 0.50 100% 90% 0.56 Video transmitter 7.0 0.56 3.94 100% 90% 4.37 Solenoid 11.1 0.25 2.78 1% 100% 0.03 Motors 11.1 50.9 564.99 100% 100% 564.99 Total weighted power draw (W) 575.28 Total battery capacity (WHr) 111 Run time (min) 11.58
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Ground station Video Receiver 2 X Battery (LiPo 3s) Electric Speed Controllers (ESC) Motor + Propeller Flight Computer Camera GPS + Compass Power Module Video Transmitter Telemetry/Controller Transceiver Transceiver 11.1V Solenoid 5V Power line Data line Legend Switch
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Includes 6 major subsystems: Power System FPV System Communication System Beacon Release System Flight Control System Propulsion System Also includes: Indicators Switches
Wednesday, January 16, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS
Schematic Major Components
ZOP Power 11.1V 4000MAH 3S 30C LiPo Battery AUAV power module ACSP5 56
Purpose: Powers all the components
There are two voltage rails 11.1 V of the battery 5V of the power module
Wednesday, January 16, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS
Schematic Major Components
mRo Pixracer R15 mRo GPS u-Blox Neo-M8N 57
Receives commands from the ground station through the communications system Sends signals to the propulsion system to change the direction/speed of the drone Sends signal to Pull the solenoid and release the payload
Wednesday, January 16, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS
Major Components Schematic
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Change horizontal and vertical position of the payload by changing the speed of different motors Change the orientation of payload by varying motor speed and direction across the UAV
Wednesday, January 16, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS
Caddx Turtle Micro Mini FPV Cam Airy Mini 5848 5.8Ghz VTX
Schematic Major Components
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Provides video feedback to the UAV operator Confirm position above FEA Avoid obstacles FPV system is transmits independently and is not controlled by flight computer Only shares the power supply
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Holybro 915MHz Telemetry radio
Schematic Major Components
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Sends Telemetry from the flight computer on flight condition Receives commands on maneuvers through a joystick on the ground station
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Adafruit Push/Pull Solenoid
Schematic Major Components
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Retains the beacon in board until a command is received in the pull position On receiving the command, releases the beacon on to the Future Excursion Area by transitioning to pull position
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Schematic Major Components
Switch: To avoid the necessity to use a heavy switch which is rated to above 100 A pulled by the motors, it is placed parallel to the motors LED is placed parallel to the flight computer as the flight computer being powered is the best indication of UAV being armed
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Component Voltage (V) Current (A) Power (W) Duty Cycle Supply Efficiency Power Draw (W) Flight computer 5.0 0.045 0.23 100% 90% 0.25 Camera 7.0 0.38 2.66 100% 90% 2.96 GPS 5.0 0.033 0.17 100% 90% 0.18 LED 5.0 .35 1.75 100% 90% 1.94 Transceiver 5.0 0.1 0.50 100% 90% 0.56 Video transmitter 7.0 0.56 3.94 100% 90% 4.37 Solenoid 11.1 0.25 2.78 1% 100% 0.03 Motors 11.1 50.9 564.99 100% 100% 564.99 Total weighted power draw (W) 575.28 Total battery capacity (WHr) 111 Run time (min) 11.58
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Assumptions: Power consumed by motor at nominal thrust is used All the components are assumed to have a duty cycle of 100% except the solenoid which is estimated to be powered 1% of the total time The power supplies are assumed to be at 90% supply efficiency
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Video Link Diversity Receiver Biquad and Dipole for both high gain and isotropic radiation pattern Video Converter to convert from NTSC to RTSP Ethernet crossover connection to computer Telemetry/Command Dipole Antenna Transceiver for communication both ways USB connection to computer Joystick to send commands
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Dipole Antenna Dipole Antenna
Signal RX sensitivity (dB) Transmit power (dBm) Rx Antenna Gain (dB) TX Antenna Gain (dB) Link Margin (dB) Rx Antenna Loss (dB) Tx Antenna Loss (dB) Maximum free space loss (dB) Frequenc y (GHz) Range (km)
Telemetry
20 2.15 2.15 12 2 2 125.3 0.915 48 Video
20 9.5 2.15 12 2 2 108.5 5.8 1.4
48 km
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Biquad Antenna
1.4 km
Video Link Telemetry
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QGroundControl Open source Popular among Amateur Drone Operators Ability to stream FPV video Ability to use Joystick over the telemetry radio instead of an RC transmitter/ receiver pair
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Wednesday, January 16, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS
Parameter Value Maximum thrust 7.49 lbf Weight 3.73 lbf Thrust-to-weight ratio 2.0 Nominal throttle point 4.19 lbf Airspeed 30.1 mph Range in 20 mph headwind 1.44 mi Flight time 9.29 min
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Payload contained within upper airframe after landing Upon command from the ground station, the payload is ejected by a black powder charge The semi-rigid sheath surrounding the payload unrolls, reorients the payload right-side-up The payload lifts off of the sheath upon command from the ground station
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Redundant black powder charges Piston deploys complex assembly Payload Orientation sheath Nosecone
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Wednesday, January 16, 2019 UNIVERSITY OF ALABAMA IN HUNTSVILLE | CHARGER ROCKET WORKS
Door latch solenoid Attachment to piston bulkhead Deployment signal controller
Black powder deploys payload Latch secures payload until deployment No transmission from radio
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Arming switch access
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Microcontroller 6V power supply (batteries) 3.3V power supply (buck regulator) XBee radio Latch actuator (solenoid) Dual E-match firing circuits Arming indicator Ground station Controller Transceiver
Power line Data line Legend
12V power supply (boost convertor)
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PCB for Deployment Electronics
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Integrated Payload Tests UAV System Tests Deployment System Tests Cube Retention Test Integrated Deployment Test Radio Range Test FPV Imaging Test Deployment Material Testing Flight Range Test Ejection Test Flight Endurance Test Deployment Software Qualification
Update Risk and Hazard Assessment Emphasis on Personnel and Environment Further analysis into Failure Modes and Effects Detailed Component Description Sheets Evaluating lessons learned from sub- scale launch
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74 Subscale Flight Operating Procedure
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Training Topic Date CPR/AED/First Aid 10/4/18 – 10/19/18 Basic Emergency Procedures 10/18/18 Black Powder Testing and Motor Safety 10/30/18 Outreach Safety 11/1/18 Sub-Scale Launch Safety 11/15/18 Test and Demonstration Safety 1/17/19 Full-Scale Launch Safety 1/31/19
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The Safety Committee continues to use the team’s previously established Risk Assessment Criteria (RAC) Testing and fabrication has resulted in updated hazard and risk assessments with emphasis on: Machine shop use during fabrication Personnel and Environmental Hazards after the sub-scale launch Full reviews of current Hazard and Risk Assessment tables have been conducted by team leadership
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Local launch field conditions for sub-scale were identified as hazardous to personnel during recovery operation Additional hazard analysis resulted from this in order to mitigate future risk to personnel Major hazards analyzed include: Injury resulting from vegetation (scratches, rash, etc.) Injury resulting from insects (stings, bites) Heat Exhaustion, Heat Stroke, Dehydration
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Poison Ivy (Google Images)
Each component of the rocket and payload has a detailed description sheet This sheet includes the basic information of the component: size, weight, material, etc. Each sheet has a specific, detailed FMEA attached for the indicated component Any finite element analysis for a component is also included on the sheet
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Analysis of possible failure modes for each component of the rocket and payload to establish mitigations and prevent failures as part of the Component Description Sheets FMEA is done using a table of severity and likelihood to identify the criticality of each mode The list of FMEA is comprehensive and has been updated as components have changed
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Approved Pending Review (Vehicle) Pending Review (UAV) Black Powder Demonstration Full-Scale Launch UAV Deployment Demonstration Sub-Scale Launch Shock Cord Tensile Test Integrated Propulsion Testing Drop Test Integrated Deployment Testing Ejection Demonstration Flight Endurance Testing Flight Range Demonstration
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Launch Preparation Upper Airframe Assembly Coupler Preparation Lower Airframe Assembly Main Parachute Installation Drogue Parachute Installation UAV Installation Ejection Charge Installation Motor Installation UAV Preparation
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UAV Sheath Deployment UAV Launched Autonomous Flight Piloted Flight Beacon Deployment UAV Systems Check at Ground Station
Awarded 5,000 dollars from ASGC Sub-Scale Vehicle Launch Date (11/17/2018) Arrival of all Full-Scale Vehicle Parts New Team GTA
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Nov. 3 – Girls Science and Engineering Day Activities: Stomp Rockets & CD Hovercrafts Individuals Reached: 166 Nov. 10 – UAH Society of Women Engineers Activity: Team Interaction with Students Individuals Reached: 72 Nov. 28 – Interactive Rocketry at Lexington High School Activity: Rocketry Basics Presentation Individuals Reached: 174 Dec. 11 – Elkhorn Crossing School Presentation Activity: Rocketry Basics Presentation Individuals Reached: 144
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Feb. 16 – Science Olympiad CRW team members Activity: Battery Buggy, Boomilever & Mousetrap Vehicle Mar. 2019 – Ramsay High School CRW team members Activity: Rocketry Basics Presentation TBA: Davis Hill Elementary School Activity: Propulsion and Vehicle Design TBA: Challenger Middle School Projectile Motion and Forces TBA: Jemison High School Heat Shields & Payload Design
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Students participating in UAH Science Olympiad nsstc.uah.edu
Funding Overview Funding Status
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Projected Expenditures Actual Expenditures
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Requirement Number Requirement 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
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
Verified using the method below Validated through testing, demonstration, analysis, or inspection
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Jan Feb Mar April Vehicle Payload FRR Competition PLAR
2/9 2/2 1/25 NASA Q&A 4/6 4/26
2/9 3/2 Backup Launch Launch 2/2 2/9 Launch Backup Launch
Document Development Document Development
Competition Launch
March
1/21 - 1/27 1/28 - 2/1 2/4 - 2/10 2/11 - 2/17 2/18 - 2/24 2/25- 3/3 3/4 - 3/10 Vehicle Fab. and Assy. Final Cad Materials Order Final Drawings Part Machining Assembly Deployment Testing Piston Testing Flight Readiness Review Payload Fab. and Assembly Final Cad Materials Order Final Drawings Part Machining Assembly Payload Ejection Testing Rocket Flight Test UAV Testing FL Launch Opportunities
Jan Feb
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2/9 2/16 3/9 3/2 2/2 HARA/SoAR HARA/ SoAR MC2 SEARS SEARS 1/14 1/18 1/19 1/21-1/26 1/26-1/30 1/31 1/29-2/01 2/01 1/14 1/18 1/19 1/21-1/26 1/26-1/30 1/30-2/05 2/06 2/07-2/21