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

Conductive

Phenolic Tubing • Airframe • Strength to Weight Ratio

Polycarbonate • Airframe• LiDAR Payload Bay• CubeSat

• Transparency• Strength to Weight

Ratio

Baltic 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 Analysis

From 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) / 96”

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 Analysis

With 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

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

Decent 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 Verification

Component Verification Method

Attachment points Expected loads

Parachutes Simulated masses

Ejection 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

Altimeter

Pad 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

Parallel Inline Motor System

Parallel Inline Motor System

Parallel Inline Motor System

Parallel Stage

Inline Stage

Electronics

Tesseract

Tesseract

Electrometer

CubeSat

Ground Station

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?