NASA SL Flight Readiness Review UNIVERSITY OF ALABAMA IN - PowerPoint PPT Presentation

NASA SL Flight Readiness Review UNIVERSITY OF ALABAMA IN HUNTSVILLE CHARGER ROCKET WORKS MARCH 9, 2017

Presentation Summary • Project Overview • Readiness and Design Summary • Key Components • Mission Performance • Full-Scale Flight Analysis • Payload • Safety & Procedures • Educational Engagement • Project Management • Questions 2 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Technology Readiness Level • Actual system “flight proven” through successful mission operations • Actual system completed and “flight qualified” through test and demonstration (ground or flight) • Prototype demonstration in a flight environment • Payload ground test to verify functionality. • Sub-scale model or prototype demonstration in relevant environment (ground or flight) • Component validation through analysis and experiments as outlined in the component description sheets. • Design concept and/or application formulated • Basic design principals observed and reported 3 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Concept of Operations Drogue Main Apogee Drogue Main Parachute Primary Fire Primary Fire (18.0 seconds) (600 feet) Coast & Roll Phase Drogue Secondary Fire (19.0 seconds) Main Parachute Secondary Fire (550 feet) 600 ft. (73 seconds) Landing (114 seconds) Launch (0 – 2.4 seconds) UNIVERSITY OF ALABAMA IN HUNTSVILLE 4

Vehicle Overview Vehicle Dimensions: Payload Briefing: • Diameter: 6 inches • Roll induction and counter roll • Length: 119 inches • Proportional Interval • Mass: 52.72 lbs Derivative (PID) updates fin • Center of Pressure (CP): 89.83 inches angle to actively control • Center of Gravity (CG): 76.5 inches external fins • No major dimensional changes since CDR CG CP 5 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Changes since CDR Recovery CDR Main Parachute: SkyAngle CERT-3 XL which yielded a landing kinetic energy of 110 ft-lbf. FRR Main Parachute: Fruity Chute 144” Iris Ultra Compact with predicted landing kinetic energy of 64 ft-lbf. Upper Airframe Removable rivets changed to 4 8-32 screws with nut plates for threaded backing Aluminum all thread changed to steel all thread Solid Aluminum bracket changed to fiberglass with aluminum brackets at each end Lower Airframe Drogue bulkhead thickness changed from 0.25’’ to 0.5’’ 6 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Upper Airframe Key Components • Tracker Assembly • Located in the nose cone • Tracker unit communicates with ground station via laptop to trace vehicle • Avionics Bay • Houses recovery avionics • Two independent Stratologger altimeters • Switches • Switch mounts • 9V batteries • 3D printed sled 7 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Lower Airframe Key Components • Fin Assembly • Fins were created from fiberglass sheets • Fin brackets were machined from stock 2024 aluminum • Tail Cone • Tail cone printed from ABS plastic • Compression proof tested to ~1000 lbf • Motor • Aerotech L2200 • Max Thrust: 697 lbs • Impulse: 5104 Ns • Burn time: 2.3 s • Total Weight: 4783 g • Propellant Weight: 2518 g • Motor Case: RMS-75/5120 8 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Key Components – Recovery System • Drogue Parachute: Fruity Chute CFC- 18 • Main Parachute: Fruity Chute 144” Iris Ultra Compact • Recovery Harness: 1” Tubular Nylon Drogue Parachute (50 ft each) • Quick Links: 3/8” Oval -Shaped Threaded Steel • Drogue Nomex : 18” x 18” Cloth Sheet • Main Nomex : 36” x 36” Cloth Sheet Main Parachute 9 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Interfaces with Ground Systems • Tacker • 2 XBee radios were configured and linked to the XCTU software via the use of a laptop. • One Xbee radio remained connected to Ground Station while the other was located in the nose cone. • Coordinates were recorded throughout flight and upon landing. • Final coordinates were verified by the use of a web mapping service (Google Maps). • Rail Button Placement • Structural Ground System Interface • Close to CG • Close to aft fins 10 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Mission Performance UNIVERSITY OF ALABAMA IN HUNTSVILLE

Trajectory Curves Flight Predictions Maximum Velocity 636.73 ft/s Maximum Mach 0.57 Max Acceleration 408.52 ft/s2 Target Apogee 5287 ft T/W 9.38 Rail Exit Velocity 73.79 ft/s Stability Margin 2.18 calibers 12 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Altitude Predictions Coefficient of Drag Analysis: • Predicted Cd measured from Full-Scale results input to RockSim (0.485) • Open Rocket internally derives the Cd without manual input Wind Apogee (ft) (mph) 0 5255 5 5281 10 5293 15 5288 20 5266 13 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Descent Calculations • Drogue Parachute: Fruity Chute CFC-18 • Parachute Diameter: 18 in • Terminal Velocity: 87.1 ft/s Section Nose Cone/Upper Lower Airframe Mass (lb) 18.11 25.25 Velocity (ft/s) 87.1 87.1 KE (ft-lbf) 2132.79 2974.49 • Main Parachute: Fruity Chute 144” Iris Ultra Compact • Parachute Diameter: 144 in • Terminal Velocity: 12.8 ft/s Section Nose Cone Upper Airframe Lower Airframe Mass (lb) 5.8 12.31 25.25 Velocity (ft/s) 12.8 12.8 12.8 KE (ft-lbf) 14.76 31.32 64.24 14 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Drift Results and Predictions Wind Speed Drift Distance (ft) • Worst Case Drift (20 mph) = 2,581 ± 153 ft 0 mph 0 • Max wind speed to meet drift requirement: 648 ± 37 5 mph • 18 mph 10 mph 1289 ± 76 15 mph 1950 ± 114 20 mph 2581 ± 153 15 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Recovery System Tests Volume Test Number Rocket / Section Results (gram) Separation but main 1 First launch/Upper 4 parachute did not eject from rocket Separation and main 2 First launch/Upper 5 parachute ejected Main Drogue Separation and main 3 First launch/Upper 5 parachute ejected Primary 5g at 600ft 3g at apogee Separation and drogue Charge 4 First launch/Lower 3 parachute ejected Secondary 3.5g one second after Separation and drogue 5.5g at 550ft 5 First launch/Lower 3 Charge apogee parachute ejected Separation and drogue 1 Second launch/Lower 3 parachute ejected Separation and main 2 Second launch/Upper 5 parachute ejected Separation and main 3 Second launch/Upper 5 parachute ejected 16 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Monte Carlo Analysis • Distribution of projected altitudes • Normalized by random variable distributions • Done to obtain more realistic range of altitude values • Standard deviation of 117 feet • 2 𝜏 of 234 feet 17 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Flight 1 Overview Launch Conditions February 4 th 2017 Date Location Childersburg, AL Wind 5 mph 56 °F Temperature Motor Aerotech L2200 Parachute SkyAngle XL Launch Rod Angle 4° Objectives: • Ensure structural reliability of vehicle components for launch, flight and recovery. • Payload RIC not powered – neutral position. • Verify prediction methods. • Test dual deploy recovery system. • Match stability margin of final vehicle. • Not fully ballasted. 18 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Flight 1 Analysis Key Flight Components Wet Mass 50.40 (pounds) Stability Margin 2.18 (caliber) Thrust to Weight 9.80 Cd (coast phase) 0.45 Apogee (ft) Apogee % Error Prediction Simulation 5489 2.66% Flight Data 5639 - Post-Flight Simulation 5613 0.46% 19 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Flight 1 Recovery • Drogue Parachute : Fruity Chute CFC-18 • Terminal Velocity: 80.7 ft/s Drift Landing Distance • Main Parachute: SkyAngle CERT-3 XL Wind Speed Drift Distance (ft) 5 mph 2079 • Terminal Velocity: 17.2 ft/s Landing Kinetic Energies Section Nose Cone Upper Airframe Lower Airframe Mass (lb) 5.03 10.78 23.93 Velocity (ft/s) 17.2 17.2 17.2 KE (ft-lbf) 23.11 49.52 109.93 SkyAngle CERT-3 XL 20 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Flight 2 Overview Launch Conditions February 18 th 2017 Date Location Murfreesboro, TN Wind 4 mph 54 °F Temperature Motor Aerotech L1420 Parachute SkyAngle XL Launch Rod Angle 7 ° Objectives: • Payload RIC powered • Demonstrate ability to control roll • Verify launch detect system • Verify altitude, kinetic energy & drift prediction methods • Test dual deploy recovery system 21 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Flight 2 Analysis Key Flight Components Wet Mass 52.72 (pounds) Stability Margin 2.09 (caliber) Thrust to Weight 6.02 Cd (coast phase) 0.485 Apogee (ft) Apogee % Error Prediction Simulation 4337 1.50% Flight Data 4273 - Post-Flight Simulation 4296 0.46% 22 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Flight 2 Recovery • Drogue Parachute : Fruity Chute CFC-18 • Terminal Velocity: 86.2 ft/s Drift Landing Distance • Main Parachute: SkyAngle CERT-3 XXL Wind Speed Drift Distance (ft) • Terminal Velocity: 18.9 ft/s 4 mph 2177 Landing Kinetic Energies Section Nose Cone Upper Airframe Lower Airframe Mass (lb) 4.77 11.2 24.61 Velocity (ft/s) 18.9 18.9 18.9 KE (ft-lbf) 26.46 62.12 136.51 SkyAngle CERT-3 XXL 23 UNIVERSITY OF ALABAMA IN HUNTSVILLE

Payload Final Design