student launch project critical design review february 28, 2014
DESCRIPTION
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 - PowerPoint PPT PresentationTRANSCRIPT
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Student Launch Project Critical Design Review
February 28, 2014
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Team Structure
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Final Launch Vehicle Dimensions
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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
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Forward Section-CubeSat Nose Cone Electrometer CubeSat
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Avionics/Payload Section-Hazard Detection Avionics/Payload components Hazard Detection System Drogue Bay disengagement
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Booster Section-Parallel Boosters Parallel booster attachment/detachment Booster section disengagement Fin material and shape Positive motor retention
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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
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Thrust Curve of Motors (18,500ft)
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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
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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.
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Thrust Curve of Motors (9,000 ft)
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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
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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”
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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
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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
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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
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Mass Statement and Mass Margin
Propulsion 47%
Structure23%
Recovery8%
Payload20%
Miscellaneous2%
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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
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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
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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
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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)
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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)
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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
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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
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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
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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
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Scale Model Flight Test
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Scale Model Flight Test
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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
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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
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P.I.M.S. Payload Overview
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P.I.M.S. Payload Overview
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P.I.M.S. Payload Overview
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Tesseract Payload Overview
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Hazard Detection/Avionics Bay Integration
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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
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P.I.M.S. Payload Integration
• RockeTiltometer• Ignition Control System• Ease of integration• Compatible with Raven3
Image from manufacturer
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Tesseract Payload Integration
1
2
3
45
6
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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
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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
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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
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Questions?