student launch project flight readiness review april 21, 2014
TRANSCRIPT
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Student Launch Project
Flight Readiness ReviewApril 21, 2014
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Team Structure
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Presentation Overview
• Final Launch Vehicle• Final Motor Selection• Static Stability/ Mass Margin• Recovery System• Full Scale Test Flight• Verifications• Integrated Research Payload
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Final Launch Vehicle Design and Dimensions
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Key Design Features• Launch Vehicle Sections
• Voltmeter/ CubeSat, Hazard Detection, Multi-Staging
• Fin Style• Launch Vehicle Separations
• Booster Section, Drogue Bay/ Detachable Bulkhead
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Forward Section - CubeSat• Nose Cone• Voltmeter• CubeSat
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Avionics/Payload Section - Hazard Detection
• Avionics/ Payload components• Hazard Detection System• Drogue bay disengagement
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Booster/Sustainer Section - Multi-Staging
• Booster section disengagement• Fin Style and attachment• Positive Motor Retention
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Motor Description
Motor Brand Engine Code
Diameter Length Burn Time Total Impulse
Maximum Thrust
Main Cesaroni K1620 - Vmax
98mm 9.3307 in 1.53s 2432Ns 996 N
Sustainer Cesaroni L985TT 54mm 19.33 in 2.7s 2678 Ns 1589 N
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Thrust Curve of Motors
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Table of Motor Events
Event Time (s) Altitude (ft) Velocity (ft/s)
Motor Ignites 0 0 0
Main Motor Burnout 1.53 230 290
Main Motor Separation 2 360 275
Sustainer Ignites if within critical angle off
of the Z-axis
2.5 550 270
Sustainer Burn Out 5.2 2000 700
Apogee 24 7000 <20
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Static Stability MarginStability Margin
Stability Margin Center of Gravity Center of Pressure
With Booster 1.68 87.6 in 98.0 in
Without Booster 1.14 65.8 in 72.8 in
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Thrust-to-Weight Ratio and Rail Exit
Ascent Analysis
With Booster Section Without Booster Section
Rail exit velocity (ft/s) 64 -
Max velocity (ft/s) 290 690
Max Mach number 0.26 0.61
Max acceleration (ft/s2) 260 262
Peak altitude (ft) 1350 7000
Thrust-to-Weight Ratio 7:1 6:1
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Mass Statement and Mass MarginSubsystem Mass (lbs) Mass Limit (lbs)
Propulsion (Including: motor mounts and centering rings)
12.0 15.0
Structure (Including: body tube, coupling tubes, bulkheads, nose cones, fin sets)
21.4 26.5
Recovery (Including: main parachute, drogue parachute, detachable components parachutes)
5.0 6.3
Payload (Including: avionics bays, electrical components)
13.0 16.3
Miscellaneous (Including: Paint scheme, dressings/coatings)
1.0 1.4
Total 52.4 65.5
Propulsion23%
Structure41%
Recovery10%
Payload25%
Miscellaneous2%
Mass Distribution
Propulsion Structure RecoveryPayload Miscellaneous
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Parachute Sizes and Descent Rates
Parameter Drogue Main Booster
Diameter (in) 85 120 60
Deployment Altitude (ft) 7000 1200 1350
Velocity at Deployment (ft/s)
>20 54 >20
Descent Rate (ft/s) 17.5 15 23
Harness Length (ft) 20 30 10
Shroud Line Length (in) 93.5 132 66
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Kinetic EnergiesParachute Parachute
SizeVehicle Section
Mass of Section
Descent Rate
Kinetic Energy
Booster 60 inches Booster Section
6 lbs 22.6 ft/s 50 ft-lbs
Mini Avionics Bay
3 lbs 22.6 ft/s 24 ft-lbs
Drogue 85 inches Drogue & Main Bay
29.5 lbs 54 ft/s --
Drogue Bay
11 lbs 17.5 ft/s 52.6 ft-lbs
Main 120 inches Avionics Bay
8 lbs 15 ft/s 28 ft-lbs
Main Section
8.5 lbs 15 ft/s 30 ft-lbs
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Predicted Drift from Launch Pad
0 mph 5 mph 10 mph 15 mph 20 mph
0 ft. 1050ft. 2284ft. 3654ft. 4515 ft.
Predicted Altitude
0 mph 5 mph 10 mph 15 mph 20 mph
7089ft. 7078ft. 7043ft. 6981ft. 6888ft.
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Test Plans and ProceduresTest Purpose Test Status
Full-Scale Test Flight
To ensure safe stage separation and sustainer motor ignition during flight
In Progress
Smart Ignition Device
To ensure that the sustainer ignition charge will be inhibited if the rocket off of the vertical.
Completed
Booster Section Separation Ground
Test
To ensure booster section can separate from main bay with attachment scheme
Complete
Airstart Test To ensure Raven3 has appropriate output current to airstart sustainer
Complete
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Full Scale Flight – 1st Test
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Full Scale Flight Test Data
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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
Completed – Successful
To test static ejection charges of full scale parachutes
Completed – Successful
To demonstrate durability of bulkhead attachment scheme within the rocket.
Completed – Successful
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Electrical Component TestingComponent Test Purpose Test Status
Microcontrollers including the Raspberry pi and Arduinos
To test functionality and programming logic
Completed
RockeTiltometer and Raven 3 altimeters
To test functionality and accuracy
Completed
Voltmeter To test functionality and accuracy
Completed
XBee Pro 900 To test functionality and communication between systems
Completed
GPS units for separable sections
To test functionality and accuracy
Completed
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Summary of Requirements VerificationLaunch Vehicle
Requirement 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 between 6500-7500 ft.
Complete
Drogue parachute successfully deploys at apogee and main at 1200 ft.
Complete
Rocket must be compatible with a 1.5’’ launch rail Complete
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Key Design Features of the Payload• Hazard Detection System• Lateral Vibrations In line System (LVIS)• Tesseract
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Payload Design and DimensionsHazard Detection/Avionics Bay
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Payload Design and DimensionsLVIS
Motor Brand Engine Code
Diameter Length Burn Time Total Impulse
Maximum Thrust
Main Cesaroni K1620 - Vmax
98mm 9.3307 in 1.53s 2432Ns 996 N
Sustainer Cesaroni L985TT 54mm 19.33 in 2.7s 2678 Ns 1589 N
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Payload Design and Dimensions• Designed to measure the magnitude of accumulated
triboelectric charge on the surface of the nose cone at carious altitudes
• Time stamp all altitudes and charge measurements to assist in post flight analysis
Tesseract
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Tesseract Payload Overview• The system can be broken down into three separate subsystems:
• Voltmeter• CubeSat• Ground Station
• The nose cone will be coated with MGM Chemicals 838 Total Ground Carbon Conductive Coating
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Payload IntegrationHazard Detection/Avionics Bay
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Payload IntegrationLVIS
• Locations of Raven3 • Avionics Bay• Above the Sustainer• Mini-Avionics Bay
Raven3 diagram from manufacturer’s website
Raven3 on payload sled
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Payload IntegrationLVIS
• Electrical schematic of RockeTiltometer2 with Raven3
Image of RockeTiltometer2 with connections
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Payload IntegrationTesseract
1
2
3
45
6
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Interfaces with Ground Systems
• 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 (x2 for each section)
• External Interfaces• 1515 rail buttons
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Summary of Requirements VerificationPayload
Payload Requirement StatusHazard Detection Bulkhead covering camera must be detachable CompleteHazard Detection Payload must be capable of detecting landing hazards CompleteHazard Detection Data must be transmitted to the ground in real time IncompleteLVIS Motor staging must perform properly CompleteLVIS Payload must record lateral vibrations in the airframe CompleteLVIS Data must be recoverable CompleteTesseract Payload must be able to record a potential difference CompleteTesseract Payload must record altitude CompleteTesseract Data must be stored and recoverable Complete
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Questions?