The University of Akron Akronauts Rocket Design Team · Recovery system deploys during assembly or prelaunch Personnel injury 2C Avionics sends a current to recovery system Will design

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


Static Stability Margin

CP & CG Locations

Preliminary Motor Selection &

Justification

Justification

- Performs well in simulation

(5312ft)

- Low cost ($200)

- Reloadable

Aerotech L1390G


Thrust to Weight Ratio & Rail Exit

Velocity


Average Thrust/Weight

1374 N/183.3 N 7.5

Rail Exit Velocity

73.4 ft/s

Sub-System ComponentsNose Cone


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


Sub-System ComponentsEngine Bay• Dual Thrust plate configuration

• Series of center rings to align motor casing

• Independent section


Length 35in

Weight 16lb

Sub-System Components

Fins

• Trapezoidal

configuration

• Attached to body tube

• Fastened with lip design

as well as epoxy


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


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


Removable Canister

Locking Mechanism


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


21. 2.

1

Recovery Parachutes


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


• 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

•

•

•

•

•

•


Drift and Energy Calculations


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 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


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.


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


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


Personnel-Specific Hazard Analysis (Continued)


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




Uncontrolled Descent

Recovery System Failure

Rocket ballistic descent, drift to populated

area1C

See below FMEA Table for failure- specific risk mitigations


1E

Fabrication Injury

Member inexperienced,

untrained, unprepared to

work

Personal Injury 2D



use.


times

2D

Assembly Injury

Member inexperienced, untrained, or

unprepared for work

Personal Injury 2D



use.


times

2D




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


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


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)


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


launch

CO2 charges will be

large enough for

overcompensation


launch

Parachute gets

stuck in body of

rocket

CO2 charges will be

large enough for

overcompensation


launch




Recovery system

deploys during

assembly or prelaunch

Personnel injury 2CAvionics sends a

current to recovery

system

Will design

avionics to not

have parasitic

voltage


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


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




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


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.


Project

Plan


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


Times Welcome 101's Trainings

Meeting 4 OFF Welcome 101's Trainings


needed



Time TBA)


meeting 7:30pm



Monthly Safety Saturday

Meeting

Meeting 2 OFF


Times


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


needed


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


Time TBA)


meeting 7:30pm



Optional Meet day if

needed



Fundraising promo

Senior Design Meeting

6:30pm Air brake meeting 5:00 pm Out Reach Testing/ Simulations day

Meeting 3 OFF


Times Out Reach


needed


Times

Meeting 4 OFF Welcome 101's Trainings Welcome 101's Trainings


needed



Time TBA)

Monthly Full Team update

meeting 7:30 pm



Optional Meet day if

needed

Meeting 2 OFF


Times


Fundraising promo


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

Documents

The University of Akron Akronauts Rocket Design Team · Recovery system deploys during assembly or prelaunch Personnel injury 2C Avionics sends a current to recovery system Will design