Student Launch Project

Critical Design ReviewFebruary 28, 2014

Team Structure

Final Launch Vehicle Dimensions

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 s808.959 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

Final Motor Choice (9000 ft)

Motor BrandEngine Code Diameter Length Burn Time Impulse Thrust

Boosters Aerotech I229T 54 mm 6.1417 in 1.73 s413.681 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

Static Stability Margin

Stability Analysis

From 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

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

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 Systems

Parameter Drogue Main Parallel Booster

Diameter 85’’ 120’’ 20” 60”

Deployment Altitude 18500’ 1200’ 4445’ 7150’

Velocity at Deployment (f/s)

0.8728 17.03 81 19

Descent Rate (ft/s) 17.03 14.895 18.43 20.15

Kinetic Energy (ft-lbs)

46.93 50.55 3.56 45.94

Recovery Harness Material

1” Tubular Nylon

Harness Length (ft) 20’ 30’ 6’ 10’

Predicted Drift from Launch Pad

0 mph 5 mph 10 mph 15 mph 20 mph

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

18,00 ft. Flight

0 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

Test Plans and Procedures

Recovery System Tests Ensure safe operation of recovery system Parachute tests, static ejection tests, bulkhead tests

Airframe Materials Tests Verify that airframe components can withstand expected

loads Tests to failure, including tensile and compressive tests

Wind Tunnel Tests Tests to find drag coefficient for increased accuracy of

simulationsNylon Bolts

Tests to determine the correct amount of black powder to be placed in Nylon Exploding Bolts

Electrical Components Tests to ensure minimum amount of error.

Scale Model Flight Test

Scale Model Flight Test

Final Payload Design Overview and Integration

Final Payload Design Overview and Integration

Final Payload Design Overview and Integration

Final Payload Design Overview and Integration

Interfaces

Internal

USB Connections

Raspberry Pi, Power SupplyArduino, GPS, Camera,

Digital Connections Pressure\Temp. Sensor

Analog Connections

All Other Atmospheric Sensors

Serial Connections

Raspberry Pi ↔ Arduino, GPSXbee

External

Radio Frequency

RoamEO GPS Tracker (154.60 MHz), Xbee (902-928

MHz)

Physical Connections

8 ft. 1515 Launch Rail12V Igniter Connection

Status of Requirements Verification

Requirement StatusRocket must not fly higher than 20,000 ft. AGL CompleteRocket must carry a scientific payload CompleteRocket must have dual altimeters CompleteRocket must have dual deploy recovery system CompleteRocket must be reusable on the day of recovery CompleteRocket must land within 5000 ft. of the launch pad assuming 20 mph wind CompleteStudents must do all critical design and fabrication CompleteTeam must use a launch and safety checklist CompleteRocket must use a commercially available, certified motor CompleteRocket must be capable of being prepped for launch in less than 2 h CompleteRocket must be able to remain in a launch-ready configuration for at least 1 h CompleteRocket must attain an altitude between 17,000-18,000 ft. CompleteDrogue parachute successfully deploys at apogee and main at 1200 ft. CompleteRocket must be compatible with a 1.5’’ launch rail Complete

Questions?