Student Launch Project Critical Design Review

February 28, 2014

Team Structure

Final Launch Vehicle Dimensions

Key Design Features Launch Vehicle Sections

CubeSat/Electrometer, Camera System, Parallel Boosters Fin Style Launch Vehicle Separations

Parallel Boosters, Booster Section, Drogue Bay/Detachable Bulkhead

Forward Section-CubeSat Nose Cone Electrometer CubeSat

Avionics/Payload Section-Hazard Detection Avionics/Payload components Hazard Detection System Drogue Bay disengagement

Booster Section-Parallel Boosters Parallel booster attachment/detachment Booster section disengagement Fin material and shape Positive motor retention

Final Motor Choice (18,500 ft)

Motor BrandEngine Code Diameter Length Burn Time Impulse Thrust

Boosters Cesaroni J240 RL 54 mm 9.2913 in 3.35 s 808.959 Ns 241.624 N

Main Cesaroni L610 98mm 16.8110 in 8.13s4842.188 Ns 595.595 N

Sustainer CesaroniL3150 Vmax 98mm 15.5118 in 1.57 s

4806.279 Ns 3063.279 N

Thrust Curve of Motors (18,500ft)

Table of Motor Events (18,500ft)Event Time (s) Altitude (ft) Velocity (ft/s)

Motors Ignite 0 0 0

Parallel Motors Burnout 3.35 900 550

Separation of Parallel Boosters

5 1800 600

Main Motor Burnout 8.13 3800 590

Main Motor Separation 10 4700 481

Sustainer Ignites if within 5 degrees of the

Z-axis

11.5 5400 478

Sustainer Burn Out 13.07 7000 1265

Apogee 38 18500 10

Final Motor Choice (9,000 ft)

Motor BrandEngine Code Diameter Length Burn Time Impulse Thrust

Boosters Aerotech I229T 54 mm 6.1417 in 1.73 s 413.681 Ns 239.122 N

Main Aerotech L339N 98mm 12.1654 in 8.43 in2800.459 Ns 332.359 N

Sustainer Aerotech K1999N 98mm 11.3780 in 1.40 s2520.394 Ns 1800.281 N

Aerotech Motors were chosen over Cesaroni because of the motor mount sizes, should the team use Aerotech motors, the integration would only require the change of the type of motor casings used.

Thrust Curve of Motors (9,000 ft)

Table of Motor Events (9,000 ft)Event Time (s) Altitude (ft) Velocity (ft/s)

Motors Ignite 0 0 0

Parallel Motors Burnout 1.73 200 230

Separation of Parallel Boosters

5 1070 280

Main Motor Burnout 8.43 2100 300

Main Motor Separation 10 2500 250

Sustainer Ignites if within 5 degrees of the Z-axis

11.5 2800 200

Sustainer Burnout 12.9 3700 711

Apogee 30 9000 24

Static Stability Margin

Stability AnalysisFrom nose cone With Booster Section Without Booster Section

Center of Pressure 90.7870’” 63.1160”

Center of Gravity 79.6498” 54.2552”

Static Stability Margin 1.80 1.43

Rail Size/Length 1.5” (1515) / 144”

Thrust-to-Weight Ratio and Rail Exit

Ascent Analysis (18,500ft)With Booster Section Without Booster Section

Rail exit velocity (ft/s) 63.23 -

Max velocity (ft/s) 620 1283

Max Mach number 0.55 1.14

Max acceleration (ft/s2) 211 685

Peak altitude (ft) 7150 18500

Thrust-to-Weight Ratio 5:1 19:1

Thrust-to-Weight Ratio and Rail Exit

Ascent Analysis (9,000ft)With Booster Section Without Booster Section

Rail exit velocity (ft/s) 57.46 -

Max velocity (ft/s) 300 698.558

Max Mach number 0.27 0.62

Max acceleration (ft/s2) 175 411.965

Peak altitude (ft) 3200 9000

Thrust-to-Weight Ratio 4.38:1 13.5:1

Mass Statement and Mass MarginSubsystem Mass (oz) Mass Limit (oz)

Propulsion (Including: motor mounts and centering rings)

469 586.25

Structure (Including: body tube, coupling tubes, bulkheads, nose cones, fin sets)

232.53 290.66

Recovery (Including: main parachute, drogue parachute, detachable components parachutes)

83.23 104.04

Payload (Including: avionics bays, electrical components)

202.47 253.09

Miscellaneous (Including: Paint scheme, dressings/coatings)

16 20

Total 1003 1254.04

Mass Statement and Mass Margin

Propulsion 47%

Structure23%

Recovery8%

Payload20%

Miscellaneous2%

Recovery Subsystem• 6-sided parachutes with Cd=0.75• Ripstop nylon

• 80 – 120 CFM• 1 inch tubular nylon

• 4000 lbs • 3/16 inch flat braided Dacron

• 600 lbs• 3/8 inch brass grommets• No 69 size “E” nylon thread

• 8.5 lbs

Recovery SpecificationsParameter Drogue Main Parallel Booster

Diameter (in) 85 120 20 60

Deployment Altitude (ft)

18500 1200 1700 7150

Velocity at Deployment (ft/s)

0.8728 17.03 81 19

Descent Rate (ft/s) 17.03 14.895 18.43 20.15

Harness Length (ft) 20 30 6 10

Shroud Line Length (in)

100 135 25 70

Kinetic EnergiesParachute Section Mass of Section

(lbs)

Terminal Velocity

(ft/s)

Kinetic Energy

(ft-lbs)

Parallel Parallel Motor 0.674 18.438 3.56

Booster

Booster Section 2.78 20.157 28.40

Mini Avionics Bay 4.51 20.157 17.54

Drogue

Drogue & Main

Bay

26.27 27.07 --

Drogue Bay 10.41 17.027 46.93

Main

Avionics Bay 8.675 14.895 29.87

Main Section 6.04 14.895 20.68

Predicted Drift from Launch Pad0 mph 5 mph 10 mph 15 mph 20 mph

0 ft. 622.88 ft. 1280.92 ft. 2046.53 ft. 2663.46 ft.

18,500 ft. Flight

0 5 10 15 20 250

500

1000

1500

2000

2500

3000

f(x) = 135.0114 x − 27.3560000000005R² = 0.998777759888725

Wind Drift with Motors for 18500ft

Wind Speed (mph)

Ran

ge F

rom

Lau

nch

Pad

(ft)

Predicted Drift from Launch Pad0 mph 5 mph 10 mph 15 mph 20 mph

0 ft. 847.97 ft. 1424.93 ft. 1666.09 ft. 1301.99 ft.

9,000 ft. Flight

0 5 10 15 20 250

200

400

600

800

1000

1200

1400

1600

1800

f(x) = − 7.88554285714286 x² + 226.152857142857 x − 30.5011428571423R² = 0.993184045567849

Wind Drift with Motors for 9000ft

Wind Speed (mph)

Ran

ge F

rom

Lau

nch

Pad

(ft)

Launch Vehicle TestingTest Purpose Test Status

Subscale Test To ensure safe stage separation is possible

Completed

Cluster Ignition Test

To ensure parallel circuitry can cause simultaneous ignition

Completed

Nylon Tie-Downs

To ensure rocket motors all ignite before rocket launches

Planned

Booster Section

Separation Ground Test

To ensure booster section can separate from main bay with attachment scheme

Planned

Airstart Test To ensure Raven3 has appropriate output current to airstart sustainer

Planned

Exploding Nylon Bolt TestingTest Purpose Test Status

Exploding Nylon Bolt

Test

To ensure exploding nylon bolts can safely separate parallel boosters from the booster section

Completed. 1.5 x 3/8 inch exploding nylon bolts with 1/8 inch wide cavity almost an inch deep. Kerf mark below head.

Exploding Nylon Bolts Shearing Strength

To ensure exploding nylon bolts have enough shear strength to withstand rocket launch.

In progress

Recovery System TestingTest Purpose Test Status

To ensure design of parachute can withstand forces

Completed – Successful

To determine velocity that the parachute will fly, and impact force of different rocket sections

Planned

To test static ejection charges of full scale parachutes

Planned

To demonstrate durability of bulkhead attachment scheme within the rocket.

Planned

Electrical Components TestingTest Purpose Test Status

Raspberry Pi Camera module

To test functionality and accuracy

Completed. Camera board communicated effectively with Raspberry Pi

RockeTilTometer To test functionality Planned

Electrometer To test functionality and accuracy

Planned

Transceiver to Ground Station

To test functionality and accuracy

Planned

Linx TM Series GPS To test functionality and accuracy

Planned

Scale Model Flight Test

Scale Model Flight Test

Staged Recovery Test

• Deployment Testing

o Static ground test for rocket separation and parachute deployment.

• Altimeter Testing

o Ground testing barometric pressure sensor and accelerometer calibration

Hazard Detection System OverviewCancellation of the LiDAR System• Cost• Availability of Parts• Eliminate moving parts

Raspberry Pi Edge Detection• Sobel Operator• Minimal components• Ease of integration

P.I.M.S. Payload Overview

P.I.M.S. Payload Overview

P.I.M.S. Payload Overview

Tesseract Payload Overview

Hazard Detection/Avionics Bay Integration

P.I.M.S. Payload Integration

• Raven3 integration• Avionics Bay• Above the Sustainer• Mini-Avionics Bay

• Payload Sled • Keeps Electronics upright throughout the flight• Ease of payload retrieval• Ease of manufacturing

Raven3 diagram from manufacturer

P.I.M.S. Payload Integration

• RockeTiltometer• Ignition Control System• Ease of integration• Compatible with Raven3

Image from manufacturer

Tesseract Payload Integration

1

2

3

45

6

Launch Vehicle Interfaces• Internal Interfaces

• Nose cone and payload sections• All-threads• Bulkhead-like centering rings• Nut locks

• Drogue bay, avionics bay, main bay, sustainer section, booster section and mini parachute bay.• #2-56 nylon shear pins (x3 for each section)

• External Interfaces• 1515 rail buttons• Parallel booster attachment points

Payload Interfaces• Structural Interfaces

o All-thread rodso Aluminum chassiso Plywood sledso Grid style pc board

Electrical Connections

USB Connections

Raspberry Pi, Power SupplyArduino, GPS, Camera,

Digital and Analog Connections Atmospheric Sensor

Serial Connections Raspberry Pi ↔ Xbee, GPSArduino ↔ Xbee, GPS

Status of Requirements VerificationRequirement Status

Rocket must not fly higher than 20,000 ft. AGL. Complete

Rocket must carry a scientific payload. Complete

Rocket must have dual altimeters. Complete

Rocket must have dual deploy recovery system. Complete

Rocket must be reusable on the day of recovery. Complete

Rocket must land within 5000 ft. of the launch pad assuming 20 mph wind. Complete

Students must do all critical design and fabrication. Complete

Team must use a launch and safety checklist. Complete

Rocket must use a commercially available, certified motor. Complete

Rocket must be capable of being prepped for launch in less than 2 h. Complete

Rocket must be able to remain in a launch-ready configuration for at least 1 h. Complete

Rocket must attain an altitude of 18,500 with 500 foot variance. Complete

Drogue parachute successfully deploys at apogee and main at 1200 ft. Complete

Rocket must be compatible with a 1.5’’ launch rail. Complete

Sustainer motor will only ignite if angle of attack is between 0-5 degrees. Complete

Questions?