student launch project preliminary design review january 10, 2014
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Student Launch Project Preliminary Design Review January 10, 2014. Team Structure. Conceptual 3D Design. Vehicle Dimensions. Vehicle Materials and Justification. Static Stability Margin. Plan for Vehicle Safety Verification. Risk Assessment Team safety b riefings - PowerPoint PPT PresentationTRANSCRIPT
Student Launch Project Preliminary Design Review
January 10, 2014
Team Structure
Conceptual 3D Design
Vehicle Dimensions
Vehicle Materials and JustificationMaterial Location Justification
Aluminum • Nose Cone Tip• CubeSat Chassis
• Light Weight• Electrically
ConductivePhenolic Tubing • Airframe • Strength to Weight
RatioPolycarbonate • Airframe
• LiDAR Payload Bay• CubeSat
• Transparency• Strength to Weight
RatioBaltic Birch Plywood • Fins
• Centering rings• Bulkheads
• Strength to Weight Ratio
Fiberglass • Nose Cone • Commercial Availability
Carbon Fiber Coating • Nose Cone • Electrically Conductive
Static Stability Margin
Stability AnalysisFrom nose cone With Booster Section Without Booster Section
Center of Pressure 83.2683” 61.4343”
Center of Gravity 73.1953” 50.5965”
Static Stability Margin 1.63 1.75
Rail Size/Length 1.5” (1515) / 144”
Risk Assessment Team safety briefings Consult mentor and industry experts Verify design with calculations and RockSim
analysis Identify potential hazards for construction
and launch Follow launch checklists and guidelines NAR High Power Rocket Safety Code Comply with federal, state, and local laws
Plan for Vehicle Safety Verification
Baseline Motor Selection
Motor BrandEngine Code Diameter Length Burn Time Impulse Thrust
Booster 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
Thrust-to-Weight Ratio and Rail Exit
Ascent AnalysisWith Booster Section Without Booster Section
Rail exit velocity (ft/s) 69.1686 -
Max velocity (ft/s) 752.0262 1531.9175
Max Mach number 0.67 1.41
Max acceleration (ft/s2) 238.1190 802.79
Peak altitude (ft) 5000 18500
Thrust-to-Weight Ratio 5.63:1 24.43:1
Launch Vehicle Verification Verification of the design requirements will be completed for the
structure, recovery, and propulsion subsystems Analysis using computer simulations or calculations
Testing hardware components
Static testing before launch
Inventory of all structural equipment
Inspect fins for damage and stability
Inspect detachable components for secure attachment
Inspect rail buttons for secure attachment
Inspect all parallel boosters and main motors
Recovery System
Recovery System
Parameter Drogue Main Parallel Booster
Diameter 62” 90” 20” 55”
Deployment Altitude 18500’ 1200’ 4445’ 5000’
Velocity at Deployment (f/s)
0.8728 39.1800 418.2604 418.2604
Descent Rate (ft/s) 15 18.612 22.4 21.42
Kinetic Energy (ft-lbs)
15 75 7.83 49.13
Recovery Harness Material
1” Tubular Nylon
Harness Length (ft) 20’ 30’ 3’ 10’
Recovery SystemElectronics/Ejection
Altimeter Make/Model 2x Missile Works mini RRC2
Redundancy Plan
Each altimeter has an independent drogue/main
charge. Redundant altimeter set to deploy 2 s after apogee and 2 s after
1200 ft.Pad Stay Time
(Launch Configuration) > 4 hours
Rocket LocatorsMini Global GPS Tracker, Adafruit Ultimate GPS v3,
USGlobalSat EM-406ABlack Powder Mass Drogue Parachute 4.752 g
Black Powder Mass Main Parachute 7.56 g
Recovery System VerificationComponent Verification MethodAttachment points Expected loadsParachutes Simulated massesEjection charges Ground tested for adequate force
Parallel Boosters
Ejection Method Motor Eject
Booster Locators Mini Global GPS Tracker
Booster Section
Altimeter Make/ModelAdept Rocketry DCS1 Deployment Controller
AltimeterPad Stay Time
(Launch Configuration)
> 4 hours
Rocket Locators Mini Global GPS Tracker
Black Powder Mass Booster Section
Parachute 1.404 g
LiDAR Hazard Detection System
LiDAR Hazard Detection System
Rotating Mirrors
Processing Subsystem
Ranging Subsystem
Ground Station
LiDAR Hazard Detection System
Parallel Inline Motor System
Parallel Stage
Inline Stage
Electronics
Parallel Inline Motor System
Parallel Inline Motor System
Tesseract
Electrometer
CubeSat
Ground Station
Tesseract
Payload Verification Complete all ground testing pertinent to payload functionality.
Set all control data.
Ensure proper wiring for all electrical components before launch.
Inspect all payload bays and detachment points for structural integrity prior to launch.
Questions?