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Student Launch Project Flight Readiness Review April 21, 2014. Team Structure. Presentation Overview. Final Launch Vehicle Final Motor Selection Static Stability/ Mass Margin Recovery System Full Scale Test Flight Verifications Integrated Research Payload. - PowerPoint PPT Presentation
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Student Launch Project Flight Readiness Review
April 21, 2014
Team Structure
Presentation Overview
• Final Launch Vehicle• Final Motor Selection• Static Stability/ Mass Margin• Recovery System• Full Scale Test Flight• Verifications• Integrated Research Payload
Final Launch Vehicle Design and Dimensions
Key Design Features• Launch Vehicle Sections
• CubeSat, Hazard Detection, Multi-Staging• Fin Style• Launch Vehicle Separations
• Booster Section, Drogue Bay/ Detachable Bulkhead
Forward Section - CubeSat• Nose Cone• Voltmeter• CubeSat
Avionics/Payload Section - Hazard Detection
• Avionics/ Payload components• Hazard Detection System• Drogue bay disengagement
Booster/Sustainer Section - Multi-Staging
• Booster section disengagement• Fin Style and attachment• Positive Motor Retention
Motor Description
Motor Brand Engine Code
Diameter Length Burn Time Total Impulse
Maximum Thrust
Main Cesaroni L985TT 98mm 9.3307 in 1.53s 2432Ns 996 N
Sustainer Cesaroni K1620 - Vmax
54mm 9.448 in 2.7s 2678 Ns 1589 N
Thrust Curve of Motors
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
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
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
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
Total52.4 65.5
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
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
Predicted Drift from Launch Pad0 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.
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
Full Scale Flight – 1st Test
Full Scale Flight Test Data
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
Electrical Component TestingTest Purpose Test Status
Microcontrollers including the Raspberry pi and Arduinos
To test functionality and programming logic
Complete
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
Summary of Requirements VerificationLaunch Vehicle
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
Key Design Features of the Payload• Hazard Detection System• Lateral Vibrations In line System (LVIS)• Tesseract
Payload Design and DimensionsHazard Detection/Avionics Bay
Payload Design and DimensionsLVIS
Motor Brand Engine Code
Diameter Length Burn Time Total Impulse
Maximum Thrust
Main Cesaroni K1620 - Vmax
98mm 9.3307 in 2.69s 2678 Ns 1589 N
Sustainer Cesaroni L985TT 54mm 9.448 in 1.53s 2432 Ns 996 N
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
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
Payload IntegrationHazard Detection/Avionics Bay
Payload IntegrationLVIS
• Locations of Raven3 • Avionics Bay• Above the Sustainer• Mini-Avionics Bay
Raven3 diagram from manufacturer’s website
Raven3 on payload sled
Payload IntegrationLVIS
• Electrical schematic of RockeTiltometer2 with Raven3
Image of RockeTiltometer2 with connections
Payload IntegrationTesseract
1
2
3
45
6
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 (x3 for each section)
• External Interfaces• 1515 rail buttons• Parallel booster attachment points
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
Questions?
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