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Preliminary Design Review Presentation Tarleton State University

NASA USLI 2012-2013

Presentation Outline # Title

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Team Introduction Mission Summary Vehicle Dimensions Vehicle Sections Elliptical Nose Cone Ballast System Upper Body Airframe Payload Housing Structure Booster Section Fins Static Stability Margin Vehicle Safety Verification and Testing Motor Trade and Selection Motor Selection 12:1 Thrust to Weight Ratio Vehicle Verification and Testing Recovery Verification and Testing Dual Deployment Avionics Bays Deployment Altimeters Selection Deployment Altimeters Wiring Maximum Landing Velocity Calculating Minimum Diameter of Main Parachute

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Main Parachute Selection Drift for Main Parachute Maximum Drift for Drogue Minimum Drogue Parachute Diameter Drogue Parachute Selection Deployment Altimeters Wiring Recovery Components Kinetic Energy Weather Cocking Landing Radius SMD Payload Payload Framework Atmospheric Data Gathering Precision of Instrumentation Autonomous Camera Orientation Payload PCB Schematic Scoring Altimeter Selection Payload Verification and Testing Cost of Vehicle and Payload Budget Summary Educational Outreach Project Outline SMD Deliverable Schedule

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Team Introduction

3

Mission Summary

Science Mission Directorate Payload

Vehicle

Recovery

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Vehicle Overview

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Vehicle Dimensions

• 108 inches total length

• 5.525 inch outer diameter

• 33.5 pounds

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Vehicle sections Nose Cone

Upper Body Airframe

Payload Housing

Booster Section

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Elliptical Nose Cone

Dimensions

• 13 inch long total

• 5.5 inch shoulder

Material

• Fiberglass

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Ballast System

Washers

Bulkheads

Apogee Altitude Control

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Upper Body Airframe

Dimensions

• 28 inches long

• 0.075 inches thick

Material

• Fiberglass

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Payload Housing Structure

Dimensions

• 36 inches long

• 0.125 inches thick

Material

• Clear Acrylic

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Booster Section Dimensions

• 36 inches long

• 0.075 inches thick

Materials

• Fiberglass

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Fins Dimension

Root Chord

12 in

Tip Chord

0 inches

Height

5 inches

Sweep Length

9.8 inches

Sweep Angle

63 Degrees

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Static Stability margin

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Center of Gravity

• 65.667 inches from the tip of the nose

Center of Pressure

• 79.738 inches from the tip of the nose

Stability margin

• 14.071 inches or 2.55 calibers of body width

Vehicle Safety Verification and Testing

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• Structure Testing • Lab Prototyping • Low Altitude Flights • Dual Deployment Testing • Force of Impact Testing • Full Scale Flights • Timed Assemblies

Motor Trade and Selection

Motor Apogee

(ft.)

Velocity

Off Rail

(ft./s)

Total

Impulse

Max.

Velocity

(ft./s)

Average

Thrust

Burn

Time

(s)

Thrust to

Weight

Ratio

Availability/

Cost

Cesaroni

L1720-WT-P 5345 76

831 lbfs

3696 Ns 738

394 lbf

1754 N 2.15 11.8

High/

$171

Aerotech

L1390G 5618 66

887 lbfs

3949 Ns 723

309 lbf

1374 N 2.65 9.2

Medium/

$210

Cesaroni

L1090SS-P 6479 77

1082 lbfs

4815 Ns 733

247 lbf

1097 N 4.4 7.4

Medium/

$347

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Motor Selection Cesaroni L1720-WT-P

• Rail Exit Velocity 76 ft/s

• 2.95 inch diameter

• Total impulse of 831 lbf -s

• Estimated apogee at 5345 ft unballasted

• 738 ft/s max velocity

• 2.15 second burn time

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12:1 Thrust to Weight Ratio

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Vehicle Verification and Testing SOW# Vehicle Requirement Satisfying Design Feature Verification Method

1.1 Deliver payload to 5,280 feet AGL Motor selection Testing, Simulation

1.2 Carry official scoring barometric altimeter Adept A1E is included in the payload housing Inspection

1.3 Launch vehicle remains subsonic Motor selection Testing, Analysis

1.4 Vehicle must be recoverable and reusable Recovery system allows a safe landing of vehicle Testing, Inspection, Analysis

1.5 Vehicle has a maximum of four sections Vehicle is composed of 3 tethered sections Inspection

1.6 Vehicle prepared for flight within 2 hours Launch operations and assembly procedure Testing, Inspection

1.7 Launch-ready for a minimum of one hour Critical on-board components run for 1.5 hours Testing, Inspection, Analysis

1.8 Vehicle compatible with 8 feet long 1 inch rail 1010 rail buttons attached to vehicle body Inspection

1.9 Launch vehicle use 12 volt DC firing system Motor is compatible with firing system Inspection

1.11 Commercially available, certified APCP motor Motor Selection: Cesaroni L1720 Inspection

1.12 Total impulse under 5,120 Ns 3695.6 Ns Inspection

1.15 Final vehicle successfully launched and

recovered prior to FRR Testing Schedule Testing

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Recovery

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Recovery Verification and Testing SOW#

Recovery System Requirement Satisfying Design Feature Verification Method

2.1 Dual Deployment Recovery Altimeters fire at the prescribed altitudes Testing

2.2 Maximum KE of 75 ft-lbf. Main parachute selection Testing, Analysis

2.3 2500ft Landing Radius Drogue and main parachute selection Testing, Analysis

2.4 Independent Recovery Electronics Altimeters have dedicated Power Supplies Inspection

2.5 Redundant Altimeters Deployment by main and backup altimeter Inspection

2.6 External Arming Switches Port holes in vehicle airframe to altimeter bays Inspection

2.7 Each altimeter have a dedicated power supply Each altimeter uses a separate 9 Volt battery Inspection

2.8 Arming switches able to be locked ON Port holes in vehicle airframe to altimeter bays Testing, Inspection

2.9 Arming switches located max of 6ft from base Main altimeter bay is located at 5’ 8” Inspection

2. 10 Use removable shear pins Nylon shear pins couple parachute compartments Inspection

2.11 Vehicle carry an electronic tracking device GPS in payload and altimeter bays Testing

2.12 Recovery electronics not disrupted by other

electronics Altimeters shielded by copper mesh lining Inspection, Testing

2.12.1 Recovery altimeters separated from transmitting

devices Altimeters have separate compartment Inspection

2.13 Recovery use commercial low-current e matches Davyfire N28BR e-matches have been selected Inspection, Testing 21

Dual Deployment

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Drogue Parachute

• 5280 feet AGL

• 63 ft/s

Main Parachute

• 500 feet AGL

• 13 ft/s

Avionics Bays • Copper mesh shielding

Black Powder Wells

Altimeters

GPS

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Deployment Altimeters Selection Item Distributor Product

Unit

Dimensions

Unit

Cost Number

Total

Cost

Main

Altimeter

Featherweight

Altimeters Raven3

1.8in. X 0.8in.

X 0.55in. X

0.34oz

$155.00 2 $310.00

Backup

Altimeter PerfectFlite Stratologger

2.75in. long X

0.9 in. wide X

0.45 oz

$79.95 2 $159.90

Option 1 Loki Research Ozark ARTS

3.75in. long X

1.4in. wide X

2.75 oz

$190.00 2 $380.00

Option 2 Adept

Rocketry ALTS1-50K

0.9in. X 0.65in.

X 4.25in. X

4.25oz

$89.00 2 $178.00

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Deployment Altimeter Wiring

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Maximum Landing Velocity

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Calculating Minimum Diameter of Main Parachute

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Main Parachute Selection

Manufacturer Item Shroud

Lines Diameter

Unit

Cost

Top Flight

Recovery TFR Par-120 16 10ft $89.95

The

Rocketman

STANDARD LOW-POROSITY 1.1

RIPSTOP PARACHUTE 4 10ft $110.00

Fruity Chutes Custom Parachute - 50lb @ 20fps 16 10ft $240.00

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Drift For Main Parachute

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Maximum Drift For Drogue

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Minimum Drogue Parachute Diameter

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Drogue Parachute Selection

Manufacturer Item Shroud

Lines Diameter

Unit

Cost

Top Flight PAR-STD-24 6 2ft $9.95

The

Rocketman

STANDARD LOW-

POROSITY 1.1 RIPSTOP 4 2ft $25.00

Apogee

Rockets Nylon Parachute #29218 6 2ft $11.44

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Recovery Components Proposed Selection Distributor Item Number Qty. Total Cost

Main Altimeters Featherweight Altimeters Raven3 2 $310.00

Backup Altimeters PerfectFlite StratoLogger 2 $159.90

Electric Matches Coast Rocketry Daveyfire N28BR 4 $11.80

FFFFg Black Powder Goex Goex 4F Black Powder 1 $15.75

Black Powder Ejection Charge Holders Aerocon Systems BPSmall 1 $3.00

Swivels Commonwealth Rocketry SWLDK80 2 $3.98

Main Shock Cord Giant Leap Rocketry Tubular Kevlar 1 $37.99

Drogue Shock Cord Giant Leap Rocketry Tubular Kevlar 1 $31.49

Main Parachute Top Flight Recovery TFR Par-120 1 $89.95

Flameproof Main Parachute Deployment Bag Rocketman Enterprises DB8 1 $40.00

Drogue Parachute Top Flight PAR-STD-24 1 $9.95

Flame-Proof Drogue Parachute Deployment

Bag Rocketman Enterprises DB2 1 $25.00

U-Bolts Sunward Aerospace U-Bolt Assembly - 0.25in. (compact) 2 $8.58

Quick Links Commonwealth Rocketry 0.25in. Stainless Steel Delta Quick Link 4 $11.96

Shear Pins Missile Works 2-56 Nylon Shear-Pin (10 pack) 1 $1.00

Arming Switches Featherweight Altimeters Featherweight Magnetic Switch 2 $50.00

Hand-held Rotary Fan Anemometer Weather Shack SpeedTech WM-300 1 $154.95

GPS System Big Red Bee BeeLine GPS-Package Deal 2 $578.00

Radio Frequency Shielding Material LessEMF Pure Copper Polyester Taffeta Fabric 2 $21.90

Total $1,565.20

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Kinetic Energy

Section Weight Kinetic Energy

Nose Cone 2.252 lbs 5.662 ft∙lbf

Upperbody Airframe and

Payload 16.766 lbs 42.1533 ft∙lbf

Booster 10.602 lbs 26.6557 ft∙lbf

Total 29.62 lbs 74.471 ft∙lbf

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Weather Cocking

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Landing Radius

Wind Speed Landing Radius

0 mph 7 ft

5 mph (7.33 ft/s) 275 ft

10 mph (14.67 ft/s) 550 ft

15 mph (22 ft/s) 900 ft

20 mph (29.33 ft/s) 1300 ft

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Payload

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SMD Payload

Atmospheric Data Gathering

Autonomous Real-Time Camera Orientation System (ARTCOS)

Video Recording

Clear Housing

Moving Towards PCB

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Payload Framework

Solar Irradiance and UV Sensors

ARTCOS

Circuit Board Video Camera LCD Screen

Atmospheric Data Gathering

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Precision of Instrumentation

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Purpose Product Precision

Barometric Pressure BMP180 ±0.017psi

Barometric Pressure MS5611-01BA03 ±0.029psi

Temperature BMP180 ±1.8° F

Temperature MS5611-01BA03 ±1.44° F

Humidity HIH4030 ±3.6% RH

Humidity HH10D ±3% RH

Solar Irradiance SP-110 ±5%

Solar Irradiance TSL2561 ±5%

Ultraviolent Radiation SU-100 ±10%

Ultraviolent Radiation TOCON_ABC3 ±10%

GPS LS20031 ±9.84ft

Accelerometer ADXL345 ±4.3mg

Official Altimeter Adept A1E ±1ft

Autonomous Real-Time Camera Orientation System (ARTCOS)

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Payload PCB Schematics

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Scoring Altimeter

Adept A1E

Name Distributor Dimensions Input Voltage Cost

A1E Adept 0.55" x 2.2" 12V $29.95

Stratologger PerfectFlite 2.75" x 0.9" 9V $79.95

ARTS Loki Research 3.75" x 1.4” 9 - 15V $190.00 44

Payload Verification and Testing SOW# Requirement Satisfying Design Feature Verification Method

3.1 Launch vehicle shall carry a science or engineering payload SMD payload selection Inspection, Analysis

3.1.3.1 Measurements of pressure, temperature, relative humidity,

solar irradiance and ultraviolet radiation

An appropriate sensor for each of these

measurements is onboard Testing, Analysis, Inspection

3.1.3.2 Measurements occur every 5 seconds during descent Main flight computer frequency 16Mhz Testing, Analysis

3.1.3.3 Measurements occur every minute after landing Main flight computer frequency 16Mhz Testing, Analysis

3.1.3.4 Data collection will cease 10 minutes after landing Flight computer halts data collection

after 10 minutes Testing, Analysis, Inspection

3.1.3.5 Take 2 pictures during descent and 3 after landing Control of camera to appropriate image

capture Testing

3.1.3.6 Pictures with sky at top of frame, ground at bottom Self-leveling camera mount Testing, Inspection

3.1.3.7 Data stored onboard and transmitted wirelessly microSD onboard storage; Xbee

Wireless Transimtter Testing

3.1.3.8 Separations of payload at apogee is allowed, but such

separation may cause drifting outside recovery area

The payload does not detach from the

rocket vehicle Inspection

3.1.3.9 Payload will carry GPS Locosys LS20031 is incorporated in the

payload design Inspection, Testing

3.2 Data from payload will be collected, analyzed, and reported by

team following scientific method

Research question is the correlation

between altitude and atmospheric data Analysis

3.5 Payload must be designed to be recoverable and reusable Mount to rails inside housing Testing, Inspection

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Budget

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Cost of Vehicle and Payload

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Subsystem Cost

Structure $765

Recovery $1383

Payload $1558

Propulsion $434

Total $4202

Budget Summary

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Element Est. Cost

Testing/Prototyping $13,972

Outreach $3,669

Final Build $4,202

Travel to Competition $8,200

Total $29,922

Educational Outreach

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Project Goal To reach 2,500 students Highlight Project minimum was reached on the first day of the project >100 students

Major events Star Party November 9th Science Olympiad February 23

Project Outline

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SMD Deliverables Schedule

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Questions

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