nasa’s student launch initiative › ... › docs › projectacepdrpresentation.pdf · nasa’s...

NASA’s Student Launch Initiative :

Seniors 8

Juniors 2

Sophomores 6

Interdisciplinary 2

Freshman 5

Preliminary Design Review

Payload:

Fragile Material Protection

1

2

Team Overview System AnalysisMission

PerformanceSafety

Educational Engagement

Administrative

Agenda

1. Team Overview

2. System Analysis

3. Mission Performance

4. Safety

5. Educational Engagement

6. Administrative

I. Airframe

II. Electronic Payload

III. Main Payload

IV. Recovery

V. Propulsion

Objectives

• Compete a high powered rocket that meets all specified criteria

• Reach an altitude between 5,125 ft. & 5,375 ft.

• Field a successful payload that produces useful vibration reduction data

• Transmit all data wirelessly to ground station

3


PerformanceSafety


Administrative

Team Structure

4


PerformanceSafety


Administrative

Airframe Objectives

• Remain intact

• Reusable

• Protect internal components

5


PerformanceSafety


Administrative

6


PerformanceSafety


Administrative

Airframe

Dimensions and Subsections

7


PerformanceSafety


Administrative

Weight Breakdown

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PerformanceSafety


Administrative

Total Weight: 35.19 lb

Decision Matrix – Nosecone Shape

Option Cost Drag

Ogive Δ О

Elliptical О Δ

Conical О X

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PerformanceSafety


Administrative

Decision Matrix – Fin and Nosecone Material

Option Cost Strength Ductility

Carbon Fiber X О О

Fiberglass О Δ Δ

ULTEM X О О

10


PerformanceSafety


Administrative

Decision Matrix – Body Tube

Option Cost Strength Ductility

Carbon Fiber X О О

Fiberglass Δ Δ Δ

Blue Tube О X X

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PerformanceSafety


Administrative

Decision Matrix – Bulkhead Material

Option Cost Strength Weight

Aluminum X О Δ

Plywood O X O

Fiberglass Δ Δ Δ

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PerformanceSafety


Administrative

Altimeter (Electronic Payload) Objectives

• Accurately measure apogee

• Retrieve flight data wirelessly

• Be able to track the rocket with GPS

• Waterproof compartment

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PerformanceSafety


Administrative

Altimeter Selection

Decision Matrix – Altimeter

Option Cost GPS Ability Data Acquisition

Altus TeleMega Δ O O

Altus TeleMetrum O O Δ

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PerformanceSafety


Administrative

Altimeter (Electronic Payload)

• Altus TeleMega• Located in nosecone

• GPS and Apogee• Easy to retrieve the data

• Detailed flight data can be used to compare to OpenRocket/Rocksim

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PerformanceSafety


Administrative

Altimeter Mounting

16


PerformanceSafety


Administrative

Altimeter Mounting

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PerformanceSafety


Administrative

5” O.D.

Payload Objectives

NASA Given:

• Protect unknown fragile object

• Envelop of 3.5 in dia. and 6 in length

• May not add nor remove material

Team Created:

• Reduce impact force by 50 percent

• Create valid mathematical model

• Reduce acceleration by 35 percent

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PerformanceSafety


Administrative

Main Payload

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PerformanceSafety


Administrative

Decision Matrix – Payload

Option CostForce

ReductionAcceleration

Reduction

ParallelSpring System

Δ X O

SingleMounted

Cylinder with Support Material

O X X

Series and Parallel Spring System

Δ O O

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PerformanceSafety


Administrative

Conceptual Design

• Concentric cylinder design

• Series and Parallel spring design

•Wire rope isolators for 360 vibration coverage

• Easily removable

• Variable fill design

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PerformanceSafety


Administrative

Mathematical Design

𝑀3

𝑀2

𝑀1

𝑘2 𝑐1

𝑘1 𝑐2

𝐹

Rocket

Housing

Payload𝑥3

𝑥2

𝑥1

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PerformanceSafety


Administrative

𝑐1 ሶ𝑥2

𝑀1

𝐹

𝑘1𝑥2 𝑐1 ሶ𝑥1𝑘1𝑥2

𝑐1 ሶ𝑥2

𝑀2

𝑘1𝑥1 𝑐1 ሶ𝑥1

𝑘1𝑥2𝑤2

𝑐2 ሶ𝑥2

𝑀3

𝑘2𝑥3 𝑐2 ሶ𝑥3

𝑘2𝑥2 𝑤3

൯Σ𝐹𝑦 = 0 = 𝑀1 ሷ𝑥1 = 𝐹 + 𝑘1 𝑥2 − 𝑥1 + 𝑐1( ሶ𝑥2 − ሶ𝑥1

൯Σ𝐹𝑦 = 0 = 𝑀2 ሷ𝑥2 = −𝑤2 + 𝑘 𝑥2 − 𝑥1 − 𝑐1 ሶ𝑥2 − ሶ𝑥1 + 𝑘2 𝑥3 − 𝑥2 + 𝑐2( ሶ𝑥3 − ሶ𝑥2

൯Σ𝐹𝑦 = 0 = 𝑀3 ሷ𝑥3 = −𝑤3 + 𝑘2 𝑥2 − 𝑥3 + 𝑐2( ሶ𝑥2 − ሶ𝑥3

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PerformanceSafety


Administrative

Mathematical ModelInputs

• Thrust curve

• Impact force

• Parachute deployment force

• Spring constant (k) values

• Damping coefficient (c) values

Outputs

• Relative position graph

• Relative velocity graph

• Relative acceleration graph

• Relative force calculation

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PerformanceSafety


Administrative

Recovery

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PerformanceSafety


Administrative

Recovery - Objectives

• Two parachutes• Drogue at apogee

• Main at low altitude

• 75 ft-lbf maximum Kinetic Energy

• Independent electronics

• Redundant altimeters• Lockable arming switches

• Separate batteries

• Shear pins

• Tracking equipment and transmission

26


PerformanceSafety


Administrative

Recovery – Dual-Deployment

• Reduce ground track during descent

• Drogue parachute at apogee

• Main parachute at 1000 feet

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PerformanceSafety


Administrative

http://www.arsabq.org/new_participants.htm

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PerformanceSafety


Administrative

DROGUE

MAIN

DROGUE CHUTE MAIN CHUTE

AFT BULKPLATESBOW BULKPLATES ELECTRONICS BAY

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PerformanceSafety


Administrative

35’25’

96”36”

Recovery – Electronics

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PerformanceSafety


Administrative

• Fully redundant, independent systems

• Black powder ejection charges

• Mounted to plywood sled

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PerformanceSafety


Administrative

Main Parachute

Drogue Parachute

On/Off Switch

PrimaryAltimeter

PrimaryBattery

PrimaryMain

Igniter

PrimaryDrogueIgniter

PrimaryMain

Charge

PrimaryDrogueCharge

On/Off Switch

BackupAltimeter

BackupBattery

BackupDrogue Igniter

BackupMain

Igniter

BackupDrogue Charge

BackupMain

Charge

PRIMARY CIRCUIT

BACKUP CIRCUIT

Recovery – Strength

• Aluminum bulkplates

• Steel U-bolts

• Tubular nylon tether

• 400 lbf max force

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PerformanceSafety


Administrative

Decision Matrix – Recovery Altimeter

Option Cost Feature Set Power Draw

PerfectFliteStratologger

CFO O Δ

AltusMetrumEasyMini Δ Δ О

Entacore AIM3 X O О

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PerformanceSafety


Administrative

http://www.perfectflite.com/SLCF.html

Decision Matrix – Recovery Harness

Option Cost Strength Elasticity

Elastic O X X

Tubular Kevlar X O Δ

Tubular Nylon Δ Δ О

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PerformanceSafety


Administrative

http://onebadhawk.com/1-tubular-nylon--2-loop.html

Decision Matrix – Drogue Parachute

Option Cost Descent Rate Max Force

24” Fruity Chutes Classic

EllipticalO Δ X


EllipticalO O Δ


EllipticalΔ Δ О

35


PerformanceSafety


Administrative

http://fruitychutes.com/parachute_recovery_systems/classic_elliptical_chutes.htm

Decision Matrix – Main Parachute

Option Cost Impact Max Force

72” Fruity Chutes Iris

UltraO X O


UltraO Δ Δ


UltraΔ O Δ

36


PerformanceSafety


Administrative

http://fruitychutes.com/parachute_recovery_systems/iris_ultra_parachutes.htm

Recovery - Performance

Wind Speed (mph) Lateral Distance (ft)

0 7

5 576

10 1296

15 2087

20 3046

Section Mass (lb)Kinetic Energy(ft-lbf)

Nose Cone & Payload

9.19 20.9

Recovery Bay 4.32 12.66

Booster 10.03 29.4

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PerformanceSafety


Administrative

Propulsion Objectives

• The vehicle should attain an apogee between 5,125 feet and 5,375

feet

• The vehicle should remain below Mach 1

• The motor mount should withstand propulsion forces and remain

reusable for any following flights

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PerformanceSafety


Administrative

Decision Matrix – Centering Rings

Option Cost Strength Weight

Plywood O X О

G10 Fiberglass Δ О О

Aluminum Δ О X

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PerformanceSafety


Administrative

Decision Matrix – Motor Mount Design

Option Cost Safety Against Regulations

Cluster Motor Mount O Δ X

Single Motor Mount X Δ O

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PerformanceSafety


Administrative

Motor Mount Design

Inner Tube – Blue Tube

Bulkhead – Aluminum 6061 T6

Centering Rings – Aluminum 6061 T6

Bulkhead

Inner Tube and Motor

Centering Rings

41


PerformanceSafety


Administrative

Exploded Motor Mount Design

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PerformanceSafety


Administrative

Manufacturer Cesaroni Technology

Inc

Animal Motor Works AeroTech

Make L800 L1080BB-P L850W

Total Impulse 3731 Ns 3686 Ns 3695 Ns

Altitude 5428 ft 5330 ft 5379 ft

Type Reloadable Reloadable Reloadable

Max Thrust 1024 N 1258 N 1185 N

Weight(Empty) 3.79 lb 4.13 lb 3.54 lb

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PerformanceSafety


Administrative

Down-Selected Motor

• Level 2 motor

• Motor Selection Criteria:• Altitude – No K class

• Impulse

• Thrust

• Reloadable

• More design flexibility

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PerformanceSafety


Administrative

Manufacturer AeroTech

Make L850W

Total Impulse 3695 Ns

Altitude 5379 ft

Type Reloadable

Max Thrust 1185 N

Weight (Empty) 3.54 lb

Decision Matrix – Fin Shape

Option Stability Ease of Manufacturing Likelihood of Damage

Clipped Delta Δ О Δ

Trapezoidal X Δ О

Tapered Swept О Δ X

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PerformanceSafety


Administrative

Fins

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PerformanceSafety


Administrative

• Root Chord: 11.5 in

• Tip Chord: 5.8 in

• Height: 7.5 in

• Surface Area: 63 in2

Predicative Altitude Assurance Plan

OpenRocket Altitude Prediction

Rocksim Altitude Prediction

CFD Data

Wind Tunnel DataTest Flight Data

Verify four methods produce similar 𝐶𝑑 values

Verify software ability to predict sub-scale altitude

Altitude Prediction

1/2Scale

OpenRocket Altitude Prediction

Rocksim Altitude Prediction

CFD Data

Wind Tunnel DataTest Flight Data

Verify four methods produce similar 𝐶𝑑 values

Verify software ability to predict full-scale altitude

FullScale

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PerformanceSafety


Administrative

Altitude Prediction: OpenRocket Software

• Program uses a model for the atmospheric conditions and for the wind

• Assumptions:• Ideal Gas

• Wind speed uniaxial

• Earth is flat

• Wind turbulence based off wind farms

• Uses Runge-Kutta 4

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PerformanceSafety


Administrative

Predicted Altitude

Altitude – 5,379 feet

• Over estimate because:• Software simulation

• Uncertainty in weight

• Plan to add ballast

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PerformanceSafety


Administrative

0

1000

2000

3000

4000

5000

6000

0 20 40 60 80 100 120 140 160 180

Alt

itu

de

(ft)

Time (s)

Rocksim Predicted Altitude

• Altitude – 5,368 ft

• Percent Difference of 0.2%• Based off of OpenRocket as

original value

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PerformanceSafety


Administrative

0

1000

2000

3000

4000

5000

6000

0 20 40 60 80 100 120 140 160 180

Alt

itu

de

(ft)

Time (s)

Basic Rocket Information

• Max Velocity and Acceleration – 592 ft/s and 208 ft/sec^2

• Mach Number – 0.53

• Thrust to Weight Ratio – 5.61:1

• Rail Exit Velocity – 69.2 ft/s

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PerformanceSafety


Administrative

Stability

Stability: 3.69 cal.

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PerformanceSafety


Administrative

90.46 in.

69.92 in.

Testing Plan

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PerformanceSafety


Administrative

Wind Tunnel Testing

Half Scale Model

Full Scale Model

Parachute Testing

Payload Testing

Recovery/ Test

Ejection

Safety

• Overview and Requirements

• Safety Officer Designation

• Checklists

• Certification and Liability

• Monitor Rules and Regulations

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PerformanceSafety


Administrative

Personnel Hazard Analysis

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PerformanceSafety


Administrative

Major Severity

Minor Severity

HighLikelihood

LowLikelihood

Handheld Tools

Fire

Craft/ExactoKnives

Black PowderRocket

Propellant

Heavy Machinery

Epoxy Fumes

Dust Particles

*Full Analysis can be seen in PDR Report*

Failure Modes and Effects Analysis

56

LowLikelihood

Major Severity

HighLikelihood

Minor Severity


PerformanceSafety


Administrative

Payload not Secured Properly

Excessively Tight Coupler

Altimeter/Electronics Malfunction

Instability During Flight

Drogue Parachute

Deployment Failure

Main Parachute Deployment

FailureLaunch Failure

Motor Mishandling/ Accidental Ignition


Environmental Consideration Analysis

57

LowLikelihood

Major Severity

HighLikelihood

Minor Severity

Water

Strong Winds

Humidity

Debris from Rocket

Rocket Motor Ignition

Dust Particles

Epoxy Fumes


PerformanceSafety


Administrative


General Risk Assessment

58

LowLikelihood

Major Severity

HighLikelihood

Minor Severity

Increase in Safety

Regulations

Underestimation of Scope of Work

Mismanagement of Time

Tight/Minimal Budget

Limited Resources


PerformanceSafety


Administrative


Education Engagement Outreach Activities

• Engage 200 Students in STEM-related Activities • Emphasis on Middle School Students

• Activities• NTI STEMFest

• Hydraulic Robotic Arms

• Snap Circuits

• Engineering Rocks• Egg Drop Competition

• Webelos Day• Tennis Ball Launcher Optimization

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PerformanceSafety


Administrative

Schedule: Reporting

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PerformanceSafety


Administrative

Schedule: Design Phase

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PerformanceSafety


Administrative

Budget 3%

26%

2%

13%

23%

5%

6%

11%

10%

1%

Item Forecasted Amount Pie Chart Color

Operating $300.00

Travel / Lodging $2,730.00

Launch Pad $220.00

Aerodynamics (Body)

$1,400.00

Propulsion $2,500.00

Main Payload $500.00

Electronic Payload $670.00

Recovery $1,150.00

Scale Model $1,050.00


$100.00

Total $10,620.00

Itemized Cost

Contingency Based on Risk

+

62


PerformanceSafety


Administrative

Thank you for your time!

Questions?

63

nasa’s student launch initiative › ... › docs › projectacepdrpresentation.pdf · nasa’s...

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