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

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

PerformanceSafety

Administrative

Team Structure

PerformanceSafety

Administrative

Airframe Objectives

• Remain intact

• Reusable

• Protect internal components

PerformanceSafety

Administrative

PerformanceSafety

Administrative

Airframe

Dimensions and Subsections

PerformanceSafety

Administrative

Weight Breakdown

PerformanceSafety

Administrative

Total Weight: 35.19 lb

Decision Matrix – Nosecone Shape

Option Cost Drag

Ogive Δ О

Elliptical О Δ

Conical О X

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

PerformanceSafety

Administrative

Decision Matrix – Body Tube

Option Cost Strength Ductility

Carbon Fiber X О О

Fiberglass Δ Δ Δ

Blue Tube О X X

PerformanceSafety

Administrative

Decision Matrix – Bulkhead Material

Option Cost Strength Weight

Aluminum X О Δ

Plywood O X O

Fiberglass Δ Δ Δ

PerformanceSafety

Administrative

Altimeter (Electronic Payload) Objectives

• Accurately measure apogee

• Retrieve flight data wirelessly

• Be able to track the rocket with GPS

• Waterproof compartment

PerformanceSafety

Administrative

Altimeter Selection

Decision Matrix – Altimeter

Option Cost GPS Ability Data Acquisition

Altus TeleMega Δ O O

Altus TeleMetrum O O Δ

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

PerformanceSafety

Administrative

Altimeter Mounting

PerformanceSafety

Administrative

Altimeter Mounting

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

PerformanceSafety

Administrative

Main Payload

PerformanceSafety

Administrative

Decision Matrix – Payload

Option CostForce

ReductionAcceleration

Reduction

ParallelSpring System

Δ X O

SingleMounted

Cylinder with Support Material

Series and Parallel Spring System

Δ O O

PerformanceSafety

Administrative

Conceptual Design

• Concentric cylinder design

• Series and Parallel spring design

•Wire rope isolators for 360 vibration coverage

• Easily removable

• Variable fill design

PerformanceSafety

Administrative

Mathematical Design

𝑘2 𝑐1

𝑘1 𝑐2

Rocket

Housing

Payload𝑥3

PerformanceSafety

Administrative

𝑐1 ሶ𝑥2

𝑘1𝑥2 𝑐1 ሶ𝑥1𝑘1𝑥2

𝑐1 ሶ𝑥2

𝑘1𝑥1 𝑐1 ሶ𝑥1

𝑘1𝑥2𝑤2

𝑐2 ሶ𝑥2

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

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

PerformanceSafety

Administrative

Recovery

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

PerformanceSafety

Administrative

Recovery – Dual-Deployment

• Reduce ground track during descent

• Drogue parachute at apogee

• Main parachute at 1000 feet

PerformanceSafety

Administrative

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

PerformanceSafety

Administrative

DROGUE

DROGUE CHUTE MAIN CHUTE

AFT BULKPLATESBOW BULKPLATES ELECTRONICS BAY

PerformanceSafety

Administrative

35’25’

96”36”

Recovery – Electronics

PerformanceSafety

Administrative

• Fully redundant, independent systems

• Black powder ejection charges

• Mounted to plywood sled

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

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

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

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

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

PerformanceSafety

Administrative

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

Recovery - Performance

Wind Speed (mph) Lateral Distance (ft)

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

PerformanceSafety

Administrative

Propulsion Objectives

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

• The vehicle should remain below Mach 1

• The motor mount should withstand propulsion forces and remain

reusable for any following flights

PerformanceSafety

Administrative

Decision Matrix – Centering Rings

Option Cost Strength Weight

Plywood O X О

G10 Fiberglass Δ О О

Aluminum Δ О X

PerformanceSafety

Administrative

Decision Matrix – Motor Mount Design

Option Cost Safety Against Regulations

Cluster Motor Mount O Δ X

Single Motor Mount X Δ O

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

PerformanceSafety

Administrative

Exploded Motor Mount Design

PerformanceSafety

Administrative

Manufacturer Cesaroni Technology

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

PerformanceSafety

Administrative

Down-Selected Motor

• Level 2 motor

• Motor Selection Criteria:• Altitude – No K class

• Impulse

• Thrust

• Reloadable

• More design flexibility

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

PerformanceSafety

Administrative

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

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

PerformanceSafety

Administrative

Predicted Altitude

Altitude – 5,379 feet

• Over estimate because:• Software simulation

• Uncertainty in weight

• Plan to add ballast

PerformanceSafety

Administrative

0 20 40 60 80 100 120 140 160 180

Time (s)

Rocksim Predicted Altitude

• Altitude – 5,368 ft

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

original value

PerformanceSafety

Administrative

0 20 40 60 80 100 120 140 160 180

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

PerformanceSafety

Administrative

Stability

Stability: 3.69 cal.

PerformanceSafety

Administrative

90.46 in.

69.92 in.

Testing Plan

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

PerformanceSafety

Administrative

Personnel Hazard Analysis

PerformanceSafety

Administrative

Major Severity

Minor Severity

HighLikelihood

LowLikelihood

Handheld Tools

Craft/ExactoKnives

Black PowderRocket

Propellant

Heavy Machinery

Epoxy Fumes

Dust Particles

*Full Analysis can be seen in PDR Report*

Failure Modes and Effects Analysis

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

LowLikelihood

Major Severity

HighLikelihood

Minor Severity

Strong Winds

Humidity

Debris from Rocket

Rocket Motor Ignition

Dust Particles

Epoxy Fumes

PerformanceSafety

Administrative

General Risk Assessment

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

PerformanceSafety

Administrative

Schedule: Reporting

PerformanceSafety

Administrative

Schedule: Design Phase

PerformanceSafety

Administrative

Budget 3%

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

PerformanceSafety

Administrative

Thank you for your time!

Questions?

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

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