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The University of Akron
Akronauts Rocket
Design Team
Preliminary Design Review
Vehicle dimensions
Total Length – 121 in.Tube I.D. – 5 in.
Tube O.D. – 5.125 in.
Wall Thickness – .0625 in.
Preliminary Design Review 2
Fiberglass
Polycarbonate
AluminumSteel
Epoxy
Vehicle
Materials
Formable for body construction, low cost, high strength
Low load bulkheads, light weight, low cost,
see through
High load bulkheads, high
strength to weight, Easy to machine
Fasteners and springs, high strength,
low cost
Fastens Bulkheads/Fins/couplers, high
strength, light weight, low cost
Preliminary Design Review 3
Static Stability Margin
CP & CG Locations
Preliminary Motor Selection &
Justification
Justification
- Performs well in simulation
(5312ft)
- Low cost ($200)
- Reloadable
Aerotech L1390G
Preliminary Design Review 5
Thrust to Weight Ratio & Rail Exit
Velocity
Preliminary Design Review 6
Average Thrust/Weight
1374 N/183.3 N 7.5
Rail Exit Velocity
73.4 ft/s
Sub-System ComponentsNose Cone
Preliminary Design Review 7
Length - 25in
Weight - 5lb
Von Karman (Haack series)
• High performance and efficiency at subsonic
speeds
• Room allowed for main chute
• Independent section
Sub-System Components
Avionics Bays
Peregrine Raptor CO2 System
2 Separate Avionics Bays
• Main Chute
• Drogue Chute
Swivel mount for chute tethering
Preliminary Design Review 8
Sub-System ComponentsEngine Bay• Dual Thrust plate configuration
• Series of center rings to align motor casing
• Independent section
Preliminary Design Review 9
Length 35in
Weight 16lb
Sub-System Components
Fins
• Trapezoidal
configuration
• Attached to body tube
• Fastened with lip design
as well as epoxy
Preliminary Design Review 10
Payload
Preliminary Design
Main Design - Concept Review
Current Design
Spring Damper and
Air Bag/Bladder
Combination
Non-Newtonian Fluid System
Air Bag/Bladder System
Spring Damper System
Preliminary Design Review 12
Minor Design Options
Air
Puncture
Continuous
Ballistic Gel
Hatch Door
Twist Mount
Fluid-filled Bags/Bladders
Non-Puncture Proofing
Controlled Air Flow
Conforming Solids
Screw-Top Lid
Bolt
VS.
Current
Design
Air-filled Bladders, Puncture Proofing, Continuous
Air Flow, Gel Tiles, Screw-Top Lid, Twist and Lock
Mounting
Object
Area
Damper
System
Retention
SystemElectronics
Bay
Layout B
reakdow
n
Preliminary Design Review 14
Removable Canister
Locking Mechanism
Preliminary Design Review 15
Allows for
removal of
retention
canister
through the
side of the
rocket
Electronics
Layout
Two 9V
batteries
Parker
CTS
Pump
Arduino
Printed
Circuit
Board
Recovery System
Drogue Chute deployed from mid-section of rocket
• Altitude 5,280 ft
Main Chute deployed from nosecone of rocket
• Altitude 800 ft
Event Sequence
Preliminary Design Review 18
21. 2.
1
Recovery Parachutes
Preliminary Design Review 19
Diameter
(in)30
Area (ft2) 4.91
Estimated
Fabric
Weight (g)
30
Design Elliptical
Material
64 gsm
Ripstop
Nylon
Drag
Coefficient1.33
Terminal
Velocity 80.28 ft/s
Diameter (in) 165
Area (ft2) 148.49
Estimated Fabric Weight
(g)880
Design Annular
Material64 gsm Ripstop
Nylon
Drag Coefficient 2.2
Terminal Velocity 11.35 ft/s
Drogue Parachute Main Parachute
Ejection SystemPeregrine CO
2Cartridges
Preliminary Design Review 20
• 1 System for drogue ejection
• 1 System for main ejection
• 1 Redundant system for drogue ejection
• 1 Redundant system for main ejection
Total of
4 Ejection
Systems
• QTY (1) 23 g peregrine CO2 will be used for the Drogue parachute
• QTY (1) 45 g peregrine CO2 will be used for the Main parachute
Ground tests will be done to verify
Bulkheads
•
•
•
•
•
•
•
Altimeter Selection
•
•
•
•
•
•
Preliminary Design Review 22
Drift and Energy Calculations
Preliminary Design Review 23
Nosecone Upper Section Lower Section
Estimated Weight (lbs) 3 27 20
Speed on Impact (ft/s) 11.35 11.35 11.35
Kinetic Energy (ft-lbf) 6.00 53.99 40.00
Kinetic Energy with
33% Margin (ft-lbf)7.98 71.81 53.19
Drift from 0 mph Winds (ft) 0
Drift from 5 mph Winds (ft) 926
Drift from 10 mph Winds (ft) 1,852
Drift from 15 mph Winds (ft) 2,779
Drift from 20 mph Winds (ft) 3,705
Drift Distances
Landing Kinetic Energy
Safety
Severity
Level of Risk Probability 1 Catastrophic 2 Critical 3 Marginal 4 Negligible
High A- Frequent 1A 2A 3A 4A
Moderate B- Probable 1B 2B 3B 4B
Low C- Occasional 1C 2C 3C 4C
Minimal D- Remote 1D 2D 3D 4D
E- Improbable 1E 2E 3E 4E
Preliminary Design Review 25
to be used in the analysis of all hazards, failure modes and any other matrix-style decisions
Implementation of a standard code across the board allows for easier risk analysis in a complex system.
Serves as a standards guide for resource allocation for risk mitigation.
Preliminary Design Review 26
Personnel-Specific Hazard Analysis
Hazard Cause EffectPre-
RACMitigation Verification Post-RAC
Launchpad Topple Over Improperly Secured Laceration / Blunt force injury 2D Launchpad will be anchored to groundUse a second (trained) member to
verify1E
Launchpad Vehicle
ExplosionMotor Failure
Rocket is severely damaged and risk
of injuring personnel1E
Range Officer (Certified) Supervision, Minimum
distance kept by all members
Range Officer and team Safety Officer
Enforced1E
Launch Hang FireElectronic ignition failure, thermite or
charge improperly mounted
Launch delay, possible personal
Injury2C
Minimum certified (NAR/TRA) level 3 rocketeer or
Range Officer are to approach launchpad
Range Officer and team Safety Officer
Enforced2E
Mid-Flight explosion Catastrophic system failureFalling debris, shrapnel- possible
death or severe injury1D Team of spotters watching entire flight sequence
Range Officer,team Safety Officer, all
present members3D
Uncontrolled Descent Recovery System FailureRocket ballistic descent, drift to
populated area
1C
See below FMEA Table for failure- specific risk
mitigations Test to verify prior to launch 1E
Fabrication InjuryMember inexperienced,untrained,
unprepared to work Personal Injury 2D
Members will trained with all machine, tools, or
chemicals they plan to use.
Have two or more (trained) members at
all times2D
Assembly InjuryMember inexperienced, untrained, or
unprepared for work Personal Injury 2D
Members will trained with all machine, tools, or
chemicals they plan to use.
Have two or more (trained) members at
all times2D
Recovery Systems
Testing- Premature
misfire
Powder Charge Misfire- current sent
to recovery system
Personal Injury
(Burns)2C Will design avionics to not have parasitic voltage Test to verify prior to launch 1E
Fuel Creation injuryChemical spill, powder- friction
ignition
Personal Injury (skin contact, burns,
abrasions), powder explosion2C
Supervision of University EOHS Safety Officer, PPE
worn at all times
EOHS Safety Officer, Team Safety
Officer2D
Fuel Testing injury Pressure Vessel Rupture Death, Severe Injury 1DComponents purchased from certified
suppliers, pressure rated
Design Review, assembled with
University Chemistry Dept. Mechanic3D
Preliminary Design Review 27
Personnel- Specific Hazard Analysis (Continued)
Hazard Cause Effect Pre-RAC Mitigation Verification Post-RAC
Launchpad Topple Over
Improperly Secured
Laceration / Blunt force
injury2D
Launchpad will be anchored to
ground
Use a second (trained)
member to verify
1E
Launchpad Vehicle
ExplosionMotor Failure
Rocket is severely
damaged and risk of injuring
personnel
1E
Range Officer (Certified)
Supervision, Minimum
distance kept by all members
Range Officer and team
Safety Officer Enforced
1E
Launch Hang Fire
Electronic ignition failure, thermite or charge improperly
mounted
Launch delay, possible personal Injury
2C
Minimum certified (NAR/TRA)
level 3 rocketeer or Range Officer are to approach launchpad
Range Officer and team Safety Officer Enforced
2E
Preliminary Design Review 28
Personnel-Specific Hazard Analysis (Continued)
Hazard Cause Effect Pre-RAC Mitigation Verification Post-RAC
Mid-Flight explosion
Catastrophic system failure
Falling debris, shrapnel-
possible death or severe injury
1D
Team of spotters
watching entire flight sequence
Range Officer,team
Safety Officer, all present members
3D
Uncontrolled Descent
Recovery System Failure
Rocket ballistic descent, drift to populated
area1C
See below FMEA Table for failure- specific risk mitigations
Test to verify prior to launch
1E
Fabrication Injury
Member inexperienced,
untrained, unprepared to
work
Personal Injury 2D
Members will trained with all machine, tools,
or chemicals they plan to
use.
Have two or more (trained) members at all
times
2D
Preliminary Design Review 29
Personnel-Specific Hazard Analysis
Hazard Cause Effect Pre-RAC Mitigation Verification Post-RAC
Uncontrolled Descent
Recovery System Failure
Rocket ballistic descent, drift to populated
area1C
See below FMEA Table for failure- specific risk mitigations
Test to verify prior to launch
1E
Fabrication Injury
Member inexperienced,
untrained, unprepared to
work
Personal Injury 2D
Members will trained with all machine, tools,
or chemicals they plan to
use.
Have two or more (trained) members at all
times
2D
Assembly Injury
Member inexperienced, untrained, or
unprepared for work
Personal Injury 2D
Members will trained with all machine, tools,
or chemicals they plan to
use.
Have two or more (trained) members at all
times
2D
Preliminary Design Review 30
Personnel-Specific Hazard Analysis
Hazard Cause Effect Pre-RAC Mitigation Verification Post-RAC
Recovery Systems Testing-
Premature misfire
Powder Charge Misfire- current
sent to recovery system
Personal Injury(Burns)
2C
Will design avionics to not have parasitic
voltage
Test to verify prior to launch
1E
Fuel Creation injury
Chemical spill, powder-
friction ignition
Personal Injury (skin contact,
burns, abrasions),
powder explosion
2C
Supervision of University
EOHS Safety Officer, PPE worn at all
times
EOHS Safety Officer, Team Safety Officer
2D
Fuel Testing injury
Pressure Vessel Rupture
Death, Severe Injury
1D
Components purchased from
certified suppliers, pres
sure rated
Design Review, assembled with
University Chemistry
Dept. Mechanic
3D
Preliminary Design Review 31
Failure Mode & Effect Analysis
(FMEA)
Values assigned are based on
• Common standards and probabilities for FMEA
• Previous team experience at the Experimental Sounding Rocket Association’ s (ESRA) Intercollegiate Rocket Engineering Competition.
• System failure incidents of competitor University Teams
Ranked based on our defined Risk Assessment Code (RAC)
Preliminary Design Review 32
FMEA Hazard Analysis
Hazard Effect Pre-RAC Cause Mitigation Verification Post-RAC
Rocket Deviates from
nominal flight path and
comes in contact with
personnel at high speed
Death or severe
personal injury 1C
Fin detaches from
launch vehicle
Fin alignment fixture
will be built. Fins are
to be thru-walled
attached
Design Review
1E
Rocket is
Unstable
CG and CP to be
correctly calculated. CG
will be measured and
fins will be designed for
any future variations in
weight that could
reduce the distance
between CG and CP
Design Review
Rocket recovery
system fails to deploy,
rocket comes into
contact with personnel
Death or severe
personal injury1C
Avionics armed
incorrectly
Create an arming
sequence
Use a second
(trained) member
verify sequence
1E
Avionics improperly
programmed
Avionics will not be
sending signals to
recovery system
Test to verify prior to
launch
Nose cone does not
detach from launch
vehicle
Correct shear pin
size will be used
Test to verify prior to
launch
CO2 charges will be
large enough for
overcompensation
Test to verify prior to
launch
Parachute gets
stuck in body of
rocket
CO2 charges will be
large enough for
overcompensation
Test to verify prior to
launch
Preliminary Design Review 33
FMEA Hazard Analysis
Hazard Effect Pre-RAC Cause Mitigation Verification Post-RAC
Recovery system
deploys during
assembly or prelaunch
Personnel injury 2CAvionics sends a
current to recovery
system
Will design
avionics to not
have parasitic
voltage
Test to verify prior to
launch1E
Main parachute deploys
at or near apogee,
rocket drifts
Risk of landing in
municipal areas
and difficult
recovery of
launch vehicle
3DMain parachute is
not attached
properly
Connection to be
checked before
taking to launch
pad
Test to verify prior to
launch
1E
Hang Fire upon ignition
command, then ignites
upon personnel
approach
Personnel injury 2DIgnitor is
connected to
battery
Disconnect wires
leading from
arming switch to
ignitor
Use a second
(trained) member or
Range Officer to
verify
1E
Rocket falls from launch
rail during prelaunchPersonnel injury 2C
Rail buttons are
incorrectly sized
Check the rail
buttons for
compatibility of
launch rail
Use a second
(trained) member to
verify1E
Rail buttons are
torn from body of
launch vehicle
Rail buttons will be
fastened with
proper hardware
Rail buttons to be
checked prior to
launch
Preliminary Design Review 34
FMEA Hazard Analysis
Hazard Effect Pre-RAC Cause Mitigation Verification Post-RAC
Motor explodes on
the launch pad
Rocket is
severely
damaged and
risk of injuring
personnel
1E Faulty MotorBuy a commercial
motor
Make sure motor
system is free of
any visible defects1E
Rocket doesn't leave
launch rail above 52
feet per second
Rocket
becomes
unstable2D
Too much friction
between rocket
and launch pad,
Rocket weighs too
much, or motor
doesn't produce
enough thrust
Use simulations
and test results to
verify; use lubricant
on launch rail to
reduce friction
Design Review 1E
Member gets hurts
while manufacturing a
part of the rocket
Personnel
Injury2D
Not following the
safety plan
Members will
trained with all
machine, tools, or
chemicals they
plan to use.
Have two or more
(trained) members
at all times2D
Preliminary Design Review 35
Sweeping Regulation Compliance Statement
The University of Akron Akronauts Rocket Design Team prides itself on rapid growth and development, while maintaining a safe environment for all team members, faculty, guests and onlookers.
The Akronauts Rocket Design Team follows all guidelines written or verbal by any applicable governing body. Chief among these are guidelines set forth by Federal Governance; ie: OSHA & Fire Codes, FAA regulations. Followed by University of Akron EOHS requirements or representative instructions, and then further local governance.
If found to not be in compliance in any instance, there will be an immediate work freeze until the issue is addressed.
Preliminary Design Review 36
Project
Plan
Preliminary Design Review 37
Month Sunday Monday Tuesday Wednesday Thursday Friday Saturday
Meeting 1 OFF
Bi-Weekly Project
Management assesment
meeitng 5:30pm
Recovery Meeting (Skype
Time TBA)
Weekly Leads and officers
meeting 7:30pm
Weekly Aerostructure
Meeting 6:00pm FEA Meeting
Bi-Monthly Saturday
Success report meeting
Meeting 2 OFF Fuel Team Meeting 6:30pm
PR Analysis Meeting /
Fundraising promo
Senior Design Meeting
6:30pm Air brake meeting 5:00 pm Out Reach Testing/ Simulations day
Meeting 3 OFF
R&D Meetings Multiple
Times Out Reach
Team Design Reviews if
needed
R&D Meetings Multiple
Times Welcome 101's Trainings
Meeting 4 OFF Welcome 101's Trainings
Team Design Reviews if
needed
Meeting 1 OFF Fuel Team Meeting 6:30pm
Recovery Meeting (Skype
Time TBA)
Weekly Leads and officers
meeting 7:30pm
Weekly Aerostructure
Meeting 6:00pm FEA Meeting
Monthly Safety Saturday
Meeting
Meeting 2 OFF
R&D Meetings Multiple
Times
PR Analysis Meeting /
Fundraising promo
Monthly Mentor or guest
visit day 8:30pm Air brake meeting 5:00 pm Out Reach Out Reach
Meeting 3 OFF Welcome 101's Trainings
Team Design Reviews if
needed
Team Design Reviews if
needed Welcome 101's Trainings
Meeting 4 OFF Welcome 101's Trainings Welcome 101's Trainings
Meeting 1 OFF
Bi-Weekly Project
Management assesment
meeitng 5:30pm
Recovery Meeting (Skype
Time TBA)
Weekly Leads and officers
meeting 7:30pm
Weekly Aerostructure
Meeting 6:00pm FEA Meeting
Optional Meet day if
needed
Meeting 2 OFF Fuel Team Meeting 6:30pm
PR Analysis Meeting /
Fundraising promo
Senior Design Meeting
6:30pm Air brake meeting 5:00 pm Out Reach Testing/ Simulations day
Meeting 3 OFF
R&D Meetings Multiple
Times Out Reach
Team Design Reviews if
needed
R&D Meetings Multiple
Times
Meeting 4 OFF Welcome 101's Trainings Welcome 101's Trainings
Team Design Reviews if
needed
Meeting 1 OFF Fuel Team Meeting 6:30pm
Recovery Meeting (Skype
Time TBA)
Monthly Full Team update
meeting 7:30 pm
Weekly Aerostructure
Meeting 6:00pm FEA Meeting
Optional Meet day if
needed
Meeting 2 OFF
R&D Meetings Multiple
Times
PR Analysis Meeting /
Fundraising promo
Team Design Reviews if
needed Air brake meeting 5:00 pm Out Reach Testing/ Simulations day
Monthly Schedule -Semester I (Pre-Fab)
Week 1
Week 2
Week 3
Week 4
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