PRELIMINARY DESIGN REVIEW PDR Charger Rocket Works University

PRELIMINARY DESIGN REVIEW (PDR) Charger Rocket Works University of Alabama in Huntsville NASA Student Launch 2013 -14 Kenneth Le. Blanc (Project Lead) Brian Roy (Safety Officer) Chris Spalding (Design Lead) Chad O’Brien (Analysis Lead) Wesley Cobb (Payload Lead)

Prometheus Flight Overview Event Value Units Max Speed 1960 ft/s Time To Apogee 24. 9 s Apogee 14800 ft Time at Main Deploy 176 s Main Chute Deployment Altitude 1000 ft Ground Impact Speed Nose Cone Impact Energy Body Impact Energy 7. 0 ft/s 0. 83 ft-lbf 15. 9 ft-lbf

Project Schedule

Outreach • Under Construction • Modular in Nature • Adaptable for different ages and lengths • Supporting activity • Water Rockets • Drag Experiment • Packet format for easy integration into existing events

Materials and Justifications Component Material Justification Body Tube Carbon Fiber High strength requirement, ease of fabrication, student learning experience Fins Carbon Fiber High strength requirement, ease of fabrication, student learning experience Bulkheads Carbon Fiber High strength requirement, ease of fabrication, student learning experience Nose Cone Fiberglass Radio transparency, moderate strength requirement Payload Bays 3 D Printed ABS Low strength requiement, low weight, complex profiles possible Payload Shaft Alumium Low weight, threaded shaft required

Vehicle Component Discussion • Body Tube • 4. 5” inside diameter • Wrapped carbon fiber tube • Carbon cloth wrapped over mandrel • High strength, ease of fabrication

Vehicle Component Discussion • Payload Shaft • 3/8” Aluminum Thread • Threaded into motor case end cap • Passes thrust/ recovery forces into bulkhead, payloads, etc • Retains body tube segments

Vehicle Component Discussion • Fins • Carbon fiber • Nanolaunch profile • Two piece design allowing large flange fabrication

Vehicle Component Discussion • Nose Cone • Fiberglass • Nanolaunch Profile • Will include Nanolaunch payload components

Next Steps • Hardware • Materials and Structures Testing • Design Refinement • Subscale and Prototype Fabrication

Launch Vehicle Verification • Tension tests of materials samples • Control samples and samples heated to temperatures shown in supersonic CFD analysis • Confirms suitability of standard epoxy for short bursts at supersonic temperatures • Compression tests to failure of representative high stress components • Confirms design calculations • Proof loading of actual flight hardware • Non destructive • Confirms strength of critical, difficult-to-inspect epoxy joints

Static Stability Margin •

Baseline Motor Selection • Cessaroni Technology Incorporated - 7312 M 4770 -P • 3 Grain • High Impulse (7, 312 N-s) • Low Burn Time (1. 53 seconds) • Thrust to Weight Ratio (36. 5)

Projected Flight Path 2000 1900 1800 1700 1600 1500 1400 1300 1200 1100 1000 900 800 700 600 500 400 300 200 100 0 -100 0 15000 14000 13000 12000 110000 9000 8000 7000 6000 5000 4000 3000 2000 1000 50 100 150 200 Time (sec) Event Value Units Total Flight Time 249 sec 2500 Altitude (ft) Velocity (ft/s) Mission Trajectory Profile Velocity Altitude

Ascent 2000 1900 1800 1700 1600 1500 1400 1300 1200 1100 1000 900 800 700 600 500 400 300 200 100 0 15000 14000 13000 12000 110000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 0 5 10 15 Time (sec) 20 25 Event Value Units Time To Apogee 24. 9 14800 seconds ft Altitude (ft) Velocity (ft/s) Vehicle Ascent Profile Velocity Altitude

Powered Flight 2000 1900 1800 1700 1600 1500 1400 1300 1200 1100 1000 900 800 700 600 500 400 300 200 100 0 2400 2200 2000 1800 1600 1400 1200 1000 800 600 400 200 0 0 0. 2 0. 4 0. 6 0. 8 1 1. 2 Time (sec) 1. 4 1. 6 Event Value Units Burn Time Burn Out Altitude Burn Out Velocity Max Acceleration 1. 53 1500 1900 43 seconds feet fps G’s 1. 8 2 Altitude (ft) Velocity (ft/s) Vehicle Acceleration Profile Velocity Altitude

Descent 100 90 80 70 60 50 40 30 20 10 0 -10 -20 -30 -40 -50 -60 -70 -80 -90 -100 15000 14000 13000 12000 110000 9000 8000 7000 6000 5000 4000 3000 2000 1000 0 20 45 70 95 120 145 Time (sec) 170 195 220 245 Event Value Units Drogue Release High Altitude Descent Speed Main Release Low Altitude Descent Speed Impact Energy Bottom Section Impact Energy Nose Cone 26 1000 7 15. 9 0. 83 seconds ft/s ft ft/s lbf Altitude (ft) Velocity (ft/s) Descent Velocity Altitude

Mass Variance Analysis Mass (lb) Speed Variance with Launch Mass 1. 9 1. 85 1. 8 Mach 14950 14900 14850 14800 14750 14700 14650 14600 14550 14500 27. 39 27. 89 28. 39 28. 89 29. 39 29. 89 30. 39 30. 89 31. 39 1. 75 1. 7 1. 65 1. 6 1. 55 27. 39 27. 89 28. 39 28. 89 29. 39 29. 89 30. 39 30. 89 31. 39 Mass (kg) Acceleration Variance with Mass 49 48 Acceleration (G's) Altitude (ft) Altitude Variance with Launch Mass 47 46 45 44 43 42 41 40 27. 39 27. 89 28. 39 28. 89 29. 39 29. 89 30. 39 30. 89 31. 39 Mass (lb)

Next Steps • Analysis • CFD-ACE+ Fluid Dynamics Models • Post Flight Analysis • Generate a 6 -axis Flight Trajectory Model using Commercial Software

Payload Systems Dielectrophoresis Effects of Supersonic Flight on Paints/Coatings Nanolauch 1200 Experiment Landing Hazard Detection System

Baseline Payload Design • • Segmented modular design Customizable Able to be arranged for CG Can be inserted and removed in one piece Consolidated Easy Maintenance Designed to account for high G-forces

Payload Verification and Test Plan Payload Requirement Design Capability Risk Administer High Voltage Dielectric Test Provide same voltage as previous experiments Electric shock or dielectric failure Microgravity Experience a second of low g to run experiment Not enough time to see clear results Coatings and Paint Preflight Post flight surface analysis Rocket appearance could change depending on the paint’s reaction to the heat. Metric/Verification Post flight video inspection and buzzer sounding to indicate voltage is on. Post-flight video inspection Visual inspection of surface roughness Two different coatings/ paints for changes, most heat resistant, and analysis durability of coating Pre-flight vs Post-flight Optical microscope Deterioration of initial inspection/analysis of the surface paint/coating due to comparison at before and after flight high heat microscopic level

Payload Verification and Test Plan Payload Requirement Hazard detection camera Live Data Feed Recoverable and Reusable Design Capability Risk Metric/Verification Camera tangles up Camera deploys safely Hang a camera below with the shock cord or and analyzes the rocket on descent parachute, and/or landing zone blocks the camera view Camera results could Ground station Recording data if the be inconclusive due to receives live conclusive ground below is clear swaying motion of evidence of landing of hazards parachute hazards Capable of being All or some of the All payload launched again on the systems/subsystems components same day without destroyed due to recovered, and in repairs or recovery failure working condition modifications

Next Steps • Avionics and Payload • Payload Sled Fabrication and Strength Test • Component Calibration and Testing • LHDS Development • Nanolaunch Program Code