preliminary design review presentation
TRANSCRIPT
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Preliminary Design Review Presentation
NASA USLI 2021
November 3rd, 2020
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Presentation Overview
Introduction - Christian Suray
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Project Status
Introduction - Christian Suray
Project Management
● Established Standards and Procedures
● Composed a comprehensive list of derived
requirements
● Developed itemized budgets for subteams
● Holding weekly subteam and team meetings with
action item assignments
● Contacted schools to set up outreach opportunities
Technical Teams
● Opened trade studies:
○ Two payload designs
○ Recovery systems
○ Separation mechanisms
○ Electronics
● Created CAD models of payload and
rocket designs
● Ordered parts for subscale launch
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2020-2021 UAH CRW Team Structure
Introduction - Christian Suray
CRW Management Team
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“To learn more about high powered rocketry and the
NASA design process by meeting all USLI
requirements for the designing, building, and testing
of a rocket/payload system and to share our passion
for engineering with our community.”
Mission Statement
Introduction - Christian Suray 5
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CRW Vehicle Team
Vehicle Overview - Stephen Ward 6
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Vehicle Overview General Dimensions
● Overall length: 105in
● Upper Airframe Body Tube Length: 52 in
○ Payload: 24in and Main Parachute 18 in
● Aft Airframe Length: 44 in
○ Variable Drag System: 8 in and Drogue: 10 in
● Fin Dimensions (Span x Chord): 8x6
● Coupler Length: 14 in (1 in switch band)
General Materials
● Body Tube Material: Fiberglass
● Nose Cone Material: ABS
● Fin Material: ABS
Vehicle Overview - Stephen Ward 7
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Primary Vehicle Design
Payload Bay Main Parachute Drogue
Variable Drag System
MotorAv Bay
Elliptical Nose Cone CO2 Ejection Charges
BP EjectionEjection PistonElliptical
Fins
Separation
(600ft descent)
Apogee
Separation
Vehicle Overview - Stephen Ward 8
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Concept of Operations
4500
Alt
itu
de
AG
L(f
t.)
Vehicle Con-Ops
Jettison
Window
Ground Station
4000
1000
500
Apogee
Launch
Powered
Ascent
Burnout/VDS
Controlled Glide
Drogue
Deploy
Drogue
Opens
Vehicle
Landing
Payload Jettison
and Main Deploy
Payload Ops.
Time (sec.)0 11020 604.1
Vehicle Overview - Stephen Ward 9
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Vehicle Mission PerformanceCurrent Design Predictions (Based on L-850 motor)
● Target Apogee: 4000 ft
● Time to Apogee: 16.5 s
● Velocity Off Rail:
○ 8 ft. Launch Rod: 52.0 ft/s
○ 12 ft Launch Rod: 63.8 ft/s
● Stability Off Rail:
○ 8 ft. Launch Rod: 2.41
○ 12 ft Launch Rod: 2.67
● Ground Hit Velocity: 16.5 ft/s
● Max Ground KE: 52 ft-lbf
● Descent Time: 67.9 s
● Thrust-to-Weight ratio: 4.79
● Max Shock Force: 20 gs
● 20 mph crosswind drift: 2230 ft
● CP Location [Mach 0.3]: 83.3 in
● CG Location [Mach 0.3]: 62.3 in
Vehicle Overview - Stephen Ward 10
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Motor SelectionCurrent Design for Motor
● Aerotech L850:
○ 4280 ft apogee
○ 52.0 ft/s velocity off 8 ft rod
Alternatives Considered
● Aerotech L1520:
○ 4429 ft apogee
○ 65.4 ft/s velocity off 8 ft rod
● Aerotech L1150
○ 4006 ft apogee
○ 57.2 ft/s velocity off 8ft rod
● Aerotech K1000
○ 2579 ft apogee
○ 55.8 ft/s velocity off 8ft rodComparison of L-Class Motors Considered for Vehicle
Vehicle Components - Andrew Godwin 11
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Motor Hardware and RetentionMotor Hardware Current Design
● All three considered L motors use the
same Aerotech RMS-75/3840 Motor
Casing
○ Allows more flexibility with motor
selection
○ Can change motors if design necessitates
● Mounting Hardware
○ Motor is housed inside of the motor
casing, which is attached to the body via
the rear centering ring and motor retainer.
○ Force from the motor during firing is
transmitted to the body tube through
theaft centering ring. Aerotech RMS-75/3840 75mm Reloadable Motor Assembly
12Vehicle Components - Andrew Godwin
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Motor Hardware and Retention (cont.)Motor Retainer Current Design
● Aeropack RA75 Flanged Retainer
○ Allows quick motor change after flight
○ Simple and strong connection to vehicle
○ Retainer is attached to the back of the aft
centering ring via 12 screws
○ Keeps the motor from falling out the rear
of the vehicle during descent
Centering Ring Current Design
● Aluminum (likely 6061-T6)
● Machined in house
● More allowances for other vehicle design considerations
● Attaches to the vehicle using 4 screws through the wall of the body
tube
Aeropack RA75 Retainer13Vehicle Components - Andrew Godwin
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BulkheadsDesign Process
● Leading Material: Aluminum 6061-T6
● Machined in-house
● Designed individually based on expected loads
○ Expected load based on main parachute
deployment deceleration (≅ 20 g’s)
● Design analysis performed using Solid Edge
and Nastran NX
Nose Cone Bulkhead FEA
Alternatives Considered
● Madcow Fiberglass
● 3D-Printed ABS
● Outsourced machining
● FEA performed using 141
lbf tensile load.
● Load calculated using
nose cone mass and
estimated main chute
deployment force
● FEA shows that FOS ≅1.5
Nose Cone Bulkhead
● Pockets machined to
save weight
● Exact dimensions
determined through
repeated FEA tests
14Vehicle Components - Andrew Godwin
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Nose ConeCurrent Design
● Elliptical 8” Tall, 6.17” Max OD, 3” Shoulder
○ 3D Printed, ABS, 40% infill
■ 3D Printing simplifies manufacturing
● Tracker housed inside
○ Mounted on printed ABS sled
○ External key switch
● Payload Retention
● Removable tip
● U-bolt recovery harness attachment
● Aluminum 6061-T6 Bulkheads
● Considering Mounted Camera
Alternatives Considered
● Nose Cone - Madcow 5:1 Ogive
● Nose Cone Design - ABS, Shear Configuration
● Nose Cone Material - POM, PLA, PLA+
● Bulkhead Material - ABS, Fiberglass
Tracker Sled
Nose Cone Detail Views
Payload Retention
15Vehicle Components - Andrew Godwin
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Body Tube● Leading Design
○ 6” Madcow Fiberglass Body Tube
○ Current Rocket design is 105 in long
● Alternative Materials
○ Carbon Fiber
○ Cardboard
● Considered Parameters
○ Strength- Sufficient enough to support
the rocket under expected flight loads
○ Customizability- Sections for fins and
VDS can easily be cut into the tube
○ Availability- Reasonable shipping
times from manufacturer
○ Cost - Not an inefficient expense
○ Weight- Does not require an
unacceptable propulsion system to
reach desired apogee 16Vehicle Components - Andrew Godwin
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FinsCurrent Fin Design
● Combined fins and fin bracket
● Dimensions
○ Elliptical shape, NACA-0008 cross-section
○ 6 inch body chord, 8 inch span
○ NACA-0008 compromise between drag and strength
○ Elliptical shape gives better stability per fin area
● Material: 3D-Printed ABS
○ Allows iteration and rapid changes if needed
○ More complex/combined geometries possible
○ More consistent in production
○ Rapid replacement if one fails
● Possible challenge: mounting fins to airframe
○ Current design uses nut plates
● Pitot tube installed on two opposite fins
Alternatives considered
● Non-mechanical attachment (glue, epoxy): less reliable
● Fiberglass material: more difficult to work with and less consistent
● Non-airfoil cross-section: higher drag and larger area
Fin CAD Model Internal CAD of Pitot Probe
17Vehicle Components - Andrew Godwin
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Recovery SystemDrogue parachute
● Deploys at apogee
● Fruity Chutes CFC-18
● Descent rate of 105 ft/s
Main Parachute
● Deploys at altitude of 600 ft
● Iris Ultra IFC-96
● Descent rate of 16.4 ft/s
● Total Descent time is 67.7 seconds
● Piston will be used to deploy main parachute
● Slider being considered to lower main chute deployment
impulse by extending chute opening time
Alternatives Considered
● Main Parachute
○ Iris Ultra IFC-144
○ Chute opening force would be too great and fall time would be too long
Recovery
Harness/Layout
18Vehicle Components - Andrew Godwin
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Avionics BayCurrent Design
● 14” coupler with 1” switch band
● Electronic Sled in horizontal configuration
○ 3D printed (ABS)
○ Standoffs and battery retention integrated into print
○ Heat-Set Threaded Inserts
● 6061-T6 Aluminum Bulkheads
○ Machined to house CO2 cartridges for main deployment
Potential Concerns
● Heat-Set inserts pull out
○ No documentation on pull-out strength so will perform tensile
tests
● Hinges or latch fail on battery retention
○ Will test hinge strength to failure in tensile test
19Vehicle Components - Andrew Godwin
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CO2 EjectionCurrent Plan and Design
● CO2 used for main deployment and black powder used for
drogue○ Provides clean burn and increases safety
● CO2 kit is ordered from Tinder Rocketry○ Provides cartridges and mounting system
● CO2 cartridge size is being determined○ Piston is needed to help deployment
○ Depends on piston travel distance and separation force
required
Potential Concerns
● Increased main recovery volume leads to heavy CO2
system○ Can be tested further to ensure separation capability
● Can revert to BP if CO2 continues to fail
20Vehicle Components - Andrew Godwin
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Variable Drag System (VDS) Overview
● Objective: Narrow the uncertainty interval for target apogee
● Active controls account for anomalies during flight
○ Crosswinds
● Main Advantage: Superior apogee control
● Disadvantages: Weight, complexity, modes of failure
● Located behind center of gravity for stability
Variable Drag System
VDS Bay
Variable Drag System - Fred Schulze 21
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VDS Deployment MechanismBoth Designs
● Located at bottom of VDS bay to maximize rocket stability
Linear Translating Plate Design
● Main Advantages: Weight, Simplicity
● Main Disadvantage: Low Drag
Gear Design
● Main Advantage: Exposed Area
● Main Disadvantage: Amount of body tube removed
Linear Translating Plate Design Swivel Design
Mechanism
22Variable Drag System - Fred Schulze
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Variable Drag System Control● Rocket motor designed to overshoot target apogee
○ Control scheme aims to methodically reduce this
overshoot as apogee is approached
○ Up to 230 ft of apogee reduction (main design)
● VDS only activates after burnout and deactivates at apogee
● Parameters needed: Vehicle velocity, altitude, flight angle
● Sensors needed: Altimeter, pitot probe, accelerometer
● Velocity error controlled with PID
○ Stepper motor allows drag plates to be precisely
deployed to create the necessary drag
● VDS drag vs deployment needs to be tested
○ Wind tunnel testing for drag vs area
○ Testing Cd with subscale (non-active control)
23Variable Drag System - Fred Schulze
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CRW Payload Team
Payload Overview - Joseph Barragree 24
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Primary Design - Isopedotus
● Autogyro for descent
● Active roll-stabilization fins
● Extending legs for leveling
● Horizontal landing legs
● Multiple fish-eye cameras and image stitching
Alternate Design - Ophanim
● Drogue-chute for descent
● Allowed to land in any orientation
● Levels by balancing the entire body via reaction wheels
● Rotates the body to produce panorama with single camera
● No external mechanisms or legs
Payload High-Level Designs
Payload Overview - Joseph Barragree 25
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Isopedotís Payload Overview
Isopedotís Design - Joseph Barragree
● Cylindrical Profile
○ Spring Loaded mechanically locking legs
○ Extending all-thread
○ Three fish-eye cameras
● Jettisoned at main deploy
● Autogyro Descent
● Low CG for stability on ground impact
● Capable of correcting a 45 degree landing
orientation
● Transmits panorama to ground station
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● Spring Loaded Leg locking mechanism
○ Legs slide into lander to decrease impact on pin
● All-Thread Leveling mechanics
○ All-thread is vertically extended through the base to level the
payload body
○ Designed to correct for a maximum 45 deg tilt
Isopedotís Landing System
Isopedotís Design - Joseph Barragree 27
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● Two Options were Considered
○ Parachute
■ Increases Drag
● Simple
● Effective
● Reliable
○ Autogyro
■ Rotation increases
drag and converts
potential to rotational
Kinetic energy.
● Stable
● Innovative
● Controllable
Isopedotís Recovery
Isopedotís Design - Joseph Barragree
● Results:
○ Isopedotís - Autogyro is applicable
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Payload/Autogyro Detachment Mechanism
Descent Control Design - Joseph Baragree
● Solenoid and a thin cylindrical rod to constrain movement
● Activation of solenoid will allow for movement
● Compressed spring will push rod and allow detachment
● Tether of approximately 8 feet will connect autogyro and payload after detachment
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● Jettison at main deploy
● Payload parachute descent
● Initial landing/chute detach
● Levels the body with reaction wheel control
● Capture and process panorama while rotating
body around vertical axis
● Transmit panorama to ground station
Ophanim Payload Design - Joseph Barragree
Ophanim Payload Operations
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Ophanim Payload Details● Maximum diameter of 5.8”
● Body Material:
○ Panels of ⅛” thick acrylic
○ Screwed and epoxied together
○ Top panel screwed only to allow access
● Payload Parachute attachment options:
○ Autogyro detachment mechanism with parachute
attached instead
○ Eye bolt screwed into top triangular panel for non-
detaching parachute option
● Single Camera placed on outer edge
○ Prevents internal structure from blocking image
● Electronics placed to balance CG
● Quick release bay for battery access
○ Latched and unlatched by hand
○ Constrain batteries to ensure connection
Ophanim Payload Design - Joseph Barragree
Eye bolt Detachment
Mechanism
Autogyro Detachment
Mechanism
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● Lands naturally on any side and detaches parachute with Tender Descender
● Levels by transferring angular momentum between reaction wheels and the payload body
● Governing dynamics can be modeled like a 3D inverted pendulum
● Active leveling will use LQR or PID control to maintain level balance
o LQR requires a complex analytical model and linearization, though the 3D inverted pendulum is solved in the literature
o PID control is simpler in design, but less precise
Ophanim Landing System
Ophanim Payload Design - Joseph Barragree 32
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Payload Retention
Retention Design - Nathan Ulmer
● Applicable Subsystem Requirements
○ The retention system fully retains the payload until jettison event
○ After jettison, the payload is completely free from the rocket
○ Does not prevent the main parachute from deploying properly
● Interface With Vehicle
○ Mounted in the nose cone between two bulk plates connected
with threaded rods.
○ Retained vertically with a claw mechanism
○ Retained horizontally with sabot
● Deployment Operations
○ Nose cone pushed out with main deploy
○ Sabot falls away but remains tethered to nose cone U-bolt
○ Claw releases close to 500 feet, and allows payload to fall out
○ Payload opens autogyro and legs
● Claw mechanism Details
○ Attaches to eyebolt on payload body
○ Controlled by altimeter in nose cone body
○ Claw is closed by default due to a torsion spring
○ Servo moment arm and sabot shape resist accidental opening
○ Two servos control opening and closing of the claw33
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Retention Design Trade Study
Retention Design - Nathan Ulmer
● High Level Retention Designs Considered
○ Cage - Underneath main deployment charges, opens body tube to release payload
○ Container - Acts as piston just below main parachute, actively retained to vehicle body,
drops payload using claw mechanism after main deployment
○ Nose Cone - Extension to nose cone, deployed with main parachute, releases payload
from claw mechanism after main deployment
● Selected Option - Nose Cone Retention
○ Does not interfere with main parachute deployment, unlike the container
○ Jettison does not depend on rocket body orientation, unlike the cage
○ Highest possible center of mass increases vehicle stability
Cage Container Nose Cone
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Electrical Subsystem Design - Mason Barrow
● Payload Controlled by Teensy 4.1
○ Reads Data from Sensors
○ Operates Cameras and Motors
● Electronics will be mounted on custom PCB
○ Compact
○ Lightweight
● Batteries
○ Powered by two Samsung 18650 Batteries (3.7V, 3000mAh)
○ In series, power payload for 300+ minutes
18650 Batteries
Electrical Overview
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Selection: Teensy 4.1
● Accessibility○ Arduino Libraries
○ Prior Experience
○ Self-Contained Unit
● Specifications○ 600 MHz
○ 3 SPI, 3 I2C, 7 Serial, 31 PWM, 2 ADCs
○ On-board RTC and MicroSD Card Slot
○ Pixel Processing Pipeline
Microcontroller Selection
Electrical Subsystem Design - Mason Barrow 36
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Sensor Selection
Electrical Subsystem Design - Mason Barrow 37
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Cameras
Selection: OV5642
● Accessibility○ Made for Arduino
○ Extensive Documentation
● Specifications○ 240p, 480p, 720p, 1080p, 5MP Options
○ Compressible
○ Multiple Output Formats
● 3 Cameras 120° apart, each with 180° Fisheye Lens
Camera Selection
Electrical Subsystem Design - Mason Barrow 38
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Link Budget Calculations:
Where
● PT (Transmit Power) = 24 dBm
● GT (Transmit Gain) = 1.9 dBi
● LM (Link Margin) = 30 dB
● GR (Receiver Gain) = 10.65 dBi
● PR (Receiver Power) = -110 dBm
● Freq (Frequency) = 900 MHz
Estimated Range = 11.04 Miles
Ground Control Station Overview
Electrical Subsystem Design - Mason Barrow 39
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● Assuming max power consumption when active
Power Budget
Electrical Subsystem Design - Mason Barrow 40
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● Superloop Design
● C++ on Arduino IDE
● Software Tasks:
○ Communicate with Sensors
○ Transmit Telemetry
○ Self Level
○ Take and Transmit Multiple Pictures
Software Overview
Electrical Subsystem Design - Mason Barrow 41
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CRW Safety Team
Safety - Jason Kuhn 42
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Safety Officer: Colin Boggs
Responsibilities:
● Management of Risk and Hazard Analysis
● Failure Modes and Effects Analysis
● Application of Safety Requirements from NAR, NASA, PRC,
etc.
● Creation of Major Standard Operating Procedures
○ Review and Approval of Minor SOP’s
● Coordinate Safety Efforts at All Major Testing
● Management of Fabrication and Testing Plans
○ Includes scheduling time for the usage of the PRC
● Management of Team Certifications
○ PRC and CRW Safety Quiz
○ CPR, AED, and First Aid Certification
● Major Safety Briefings
Safety Leads: Jason Kuhn (Vehicle) and Sam Mosley (Payload)
Responsibilities:
● Interface between Sub-Teams and the Safety Officer
● Collection and Management of Component Data Sheets and
Material Safety Data Sheets
● Creation of Minor Standard Operating Procedures
● Coordinate Safety Efforts at All Minor Testing
● Minor Safety Briefings
Safety Officer
Colin Boggs
Payload Safety Lead
Sam MosleyVehicle Safety Lead
Jason Kuhn
Vehicle TeamPayload Team
Safety Organization
Safety - Jason Kuhn 43
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General Protocols:
● All project meetings, including general meetings and sub-team meetings, have been and will continue to be held online via Zoom or Discord
● All members are required to comply with UAH COVID-19 regulations
○ Completing Charger Healthcheck at least once every three days
○ Compliance with random COVID screenings
● Team members who experience symptoms or are traced to someone who has recently tested positive are encouraged to undergo a COVID-19
test
○ Team members who test positive will be required to isolate until they receive clearance from a medical professional
In-Person Operations:
● All team members are required to wear cloth face coverings when meeting in-person
● Social distancing measures will be put in place wherever possible
● Use of the UAH Machine Shop and PRC Fabrication Shop must be scheduled through the Safety Officer
COVID-19 Precautions
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Personnel Hazard Analysis
Safety - Jason Kuhn
Identification:
● Derived from safety requirements, equipment usage manuals, and SDS’s
● What characteristics of this material/equipment could cause harm to our personnel?
● What kind of accidents could happen because of improper use of this material/equipment?
● Consultation of the team mentor and faculty advisor
Causes and Effects:
● Determine the safety measure that would be insufficient or unfollowed for the hazardous
situation to happen
● How badly could this hazard harm an individual?
○ Leads to a range of effects from minor to severe
○ Effects remain the same both before and after mitigations, quantified by a
severity score
Probability:
● Quantified via Risk Assessment Matrices, both before and after mitigations are put in
place
● Will tend to be high before mitigations and significantly lower after mitigations are put in
place
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Example Hazard Analysis Table:
● Hazard analysis for the handling of fiberglass
● Individually identifies the hazards associated
with the material
○ Skin Exposure
○ Eye Contact
○ Inhalation
● Lists the determined cause(s) and effects of
each hazard
● The mitigation put in place for each hazard is
recorded, as well as any effects of that
mitigation on the project as a whole.
● A risk level is determined both before and after
any mitigations are put in place.
Personnel Hazard Analysis
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Identification:
● Derived from manufacturer information and/or known material limits
● Documented by component designers in Component Data Sheets (CDS’s)
● How could this component fail?
● Consultation of the team mentor and faculty advisor
Probability:
● Quantified via Risk Assessment Matrices, both before and after mitigations are put in place
● Valuable resource - “Launching Safely in the 21st Century”
○ Published by NAR
○ Information on common failure modes and the statistics associated with them
Failure Modes and Effects Analysis
Safety - Jason Kuhn
Causes and Effects:
● Causes of failures identified through research
○ How is the part/component manufactured?
○ Has this part/component been used in the past? If so, has it failed and why?
● Determine the consequences of failure, focus on mission performance and human safety
○ Effects remain the same before and after mitigations, quantified by severity score
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A picture or 3D rendering is included
as a reference for those unfamiliar with
the component.
A table of failure modes and effects is
included for each component, as well
as alternative options for the
component.
● General Information
○ Identifies a point of contact
○ Sub-Group
○ Designer
● Technical Information
○ Included in case the part needs
to be reproduced
○ Material
○ Dimensions
○ Weight
● Business Information
○ For reference by team
management
○ Vendor
○ Cost
○ Delivery Time
Component Data Sheet
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Probability:
● Quantified via Risk Assessment Matrices, both before and after mitigations are put in
place
● The effect of mitigations for environmental hazards are often the harshest
Causes and Effects:
● Causes of hazards identified through research
○ Environmental operation limits of components
○ Proper handling and disposal of materials
● How could this hazard effect either mission performance or the launch/testing
environment?
Identification:
● Determine risks to the vehicle or personnel posed by environmental factors
○ Non-ideal weather conditions (rain, hail, high winds)
○ Excessive heat or cold
● Determine risks the project poses to the environment
○ Pollution
○ Damage to plants and wildlife
Environmental Hazards
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General Project Risks
Safety - Jason Kuhn
Probability:
● Quantified via Risk Assessment Matrices, both before and after mitigations are put in
place
● Unlike other risks and hazards, both the probability and severity of these risks can be
mitigated
Causes and Effects:
● What managerial issues could cause major problems for the project?
○ Poor budgeting and/or scheduling
○ Poor scheduling
● How could these issues harm the project?
Identification:
● Determine risks associated with scheduling, budget, and resource allocation
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● Total Identified Risks per Risk Level
● Does not Include Component Level Failure Modes
Risk Level Totals
Safety - Jason Kuhn
● Risk Levels Decrease After Mitigation
● High Risks After Mitigation are not Acceptable
51
0
5
10
15
20
25
30
35
40
No Risk Low Risk Moderate Risk High Risk
1
10
26
38
13
38
24
0
Before Mitigation After Mitigation
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SOP’s:
● Provide a clear procedure of what to do during a test or launch, and how to do those things safely
● Require signed verifications for steps that mitigate major risks, hazards, or failure modes
● Safety briefings will be held either the night before or the morning of each test or launch
Caution Statements:
DO NOT…
● Bold red text indicates an emphasis on a certain step in the procedure or an aspect of that step
CAUTION: CHECK FOR PPE USAGE OF ALL PARTICIPANTS
● This formatting indicates required PPE usage during testing or fabrication
CAUTION: DANGEROUS MATERIAL; REVIEW SDS BEFORE HANDLING
● This formatting indicates the impending use of a hazardous material, such as black powder.
CAUTION: CRITICAL HAZARD PRESENT; USE EXTREME CAUTION
● This formatting indicates the presence of a critical hazard in the SOP.
● These hazards require the utmost caution, and tasks with this level of caution will only be carried out by a Red Team.
SOP’s and Caution Statement Methodology
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CRW Project Management
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Project Schedule Overview
Management - Christian Suray
NASA PDR Presentation
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● Residual funds from previous CRW USLI teams
● Alabama Space Grant Consortium (ASGC)
● NASA USLI 2019-2020 Safety Award
Budget Breakdown: Funding
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Budget Breakdown: By Subteam
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Requirement Tracking System
Management - Christian Suray
5.9%
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● Outreach activities will be conducted virtually for high schools
previously attended by CRW members
● Hands-on experiments and in-person demonstrations will be held at
schools in Madison City, Madison County, and Morgan County
● There are 37 prospective schools open to outreach
School Outreach
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● Presentation material will be tailored to education level.
● Examples of activities that will be conducted are as follows:
Balloon Thrust Experiment Water Bottle Rocket
School Outreach
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● Facebook, Instagram, and Twitter will be used to share weekly project
updates and CRW member highlights.
Social Media
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● Working to establish test procedures for the following:
○ 3D printed nose cone and fins, CO2 deployment, VDS
● Trading two payloads in parallel
○ Design will be down-selected as testing progresses
● Purchasing subscale rocket parts for launch in late November
● Virtual outreach starting in Mid-November. In person outreach
starting in December
● Developing and assigning CDR action items
Conclusion
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Q&A
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Back Up Slides
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TrackerLeading Choice
● 2014 CRW XBee Pro S3B/Antenova GPS Tracker
○ XBee Pro S3B Ground Station
○ Transmits up to 6 miles, realistically roughly 2 miles
○ Driven by CR123A 3V Lithium Ion Battery
○ Transmits between 902 and 928 MHz
○ 250 mW Transmission Power
○ Uses RP-SMA antennas
○ Tested, currently transmits accurate location data
Alternatives Considered
● Apogee Simple GPS Tracker
○ $431.58, 6-8 mile range, all in one
● Raspberry Pi, XBee Pro S3B, Adafruit GPS
○ Similar performance as current choice, bulky
Basic CAD Model of Leading Choice - Tracker Layout of Leading Choice
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● Cylindrical profile
○ Mechanically locking legs
○ Extending all-thread
○ Three cameras
● Total mass, including a 20% growth factor, is 3lb
● Low CG for stability
Isopedotís Payload Details
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● Operational overview
● Design considerations
Isopedotís Recovery Operation
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● Parachute:
○ Uses drag of larger area to slow down
system
○ Pros:
■ Simple
■ Effective
■ Reliable
Payload Recovery
Descent Control Design - Nathan Ulmer
● Autogyro
○ Uses aerodynamic forces of spinning
blades to reduce velocity
○ Pros:
■ Stable
■ Innovative
■ Controllable
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Payload Descent
● Autogyro
● Detach mechanism
● High level CAD render
Payload Descent - Joseph Barragree
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● “1st Order” Analysis Completed
○ Assumes:
■ Thin-Airfoil Theory
■ Totally Laminar Flow
○ Results:
■ Terminal Velocity: 7[m/s]
■ Angular Velocity: 12[rev/s] = 725 [rpm]
○ Sensitivities:
■ Bearing Damping Equation
● Fb = I μ ω^2
■ Losely- Width and Length of Blades
● Higher Order Methods in Consideration
○ CFD simulation of Autogyro alone
○ CFD simulation of Whole Payload (Much more
complex)
○ Reservations
■ Limited Skill and Mastery of Tools
■ Costly in time
■ Cost is proportional to accuracy
Autogyro Calculations
Descent Control Design - Nathan Ulmer
A
B
C
A: Conversion of actual flow to Effective conditions for simulation.
B: Velocity time dynamics (positive downwards)
C: Rotation time dynamics
Note: Values subject to change
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Comparison of Descent Devices
Autogyro Only Parachute Only
Drogue chute On
Autogyro
Importance
Criteria
Rating
Weighted
Score
Criteria
Rating
Weighted
Score
Criteria
Rating
Weighted
ScoreCriteria
Obfuscation 10 8 80 3 30 7 70
Reliability 9 5 45 9 81 6 54
Stability 8 10 80 4 32 10 80
Innovation 3 8 24 3 9 10 30
Complexity 3 4 12 10 30 4 12
Cost 3 4 12 4 12 4 12
0 0 0
Total Weighted Score 253 194 258
● Obfuscation
○ The descent mechanism should be unlikely to impede
the function of the payload via collision or
obfuscation of the camera
● Reliability
○ The descent mechanism should be unlikely to fail or
break during its launch or descent
● Stability
○ The descent mechanism should not oscillate the
payload such that the leveling device is unable to
perform its task. Less oscillation is prefered
● Innovation
○ New, innovative, or interesting designs are likely to
improve our chances during competition if
implemented properly
● Complexity
○ The intricacy of the systems is directly proportional
to construction or reliability concerns which need to
be evaluated.
● Cost
○ Weight and monetary costs. Have not yet been
assessed but parachute is likely to be more expensive
in monetary cost.
Note: Higher is better
Both autogyro solutions are roughly equivalent as such we will continue
with these approaches. The reliability and ease of a parachute make it an
ideal backup candidate.
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Subscale Gantt Chart
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Full-Scale Gantt Chart
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CRW Weekly Schedule
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Other Possible Launch Dates
Management - Christian Suray 74