PRELIMINARY DESIGN PRESENTATION UNIVERSITY OF SOUTH ALABAMA LAUNCH SOCIETY CONNER DENTON, JOHN FAULK, NGHIA HUYNH, KENT LINO, PHILLIP RUSCHMYER, ANDREW TINDELL MENTOR : CARLOS J. MONTALVO MISSION STATEMENT MISSION PERFORMANCE CRITERIA ACHIEVE MAXIMUM ALTITUDE OF 5,280 FT (1 MILE) SUCCESSFUL EJECTION OF TOP BODY TUBE SUCCESSFUL DROGUE DEPLOYMENT AT APOGEE SUCCESSFUL EJECTION OF NOSE CONE MAIN PARACHUTE DEPLOYMENT WITHIN 2500-2000 FT INTO DESCENT ACHIEVE SAFE LANDING AND RECOVERY FLIGHT PROFILE SIMULATIONS With Wind Without Wind VEHICLE DATA & COMPONENT ANALYSIS FLIGHT PREDICTIONS & THRUST CURVE WIND SPEED = 4.47MPH APOGEE = 5992 FT WIND SPEED = 0 MPH APOGEE = 5992 FT MAXIMUM ACCELERATION = 489 FT/S2 VEHICLE PARAMETERS OVERALL VEHICLE DIMENSIONS HEIGHT: 94.0 INCHES BODY DIAMETER: 4.0 INCHES WALL THICKNESS: 1/16 INCHES VEHICLE MATERIALS NOSECONE: PVC SIMILAR MATERIAL BODY TUBES: CARDBOARD FINS: FIBERGLASS MOTOR MOUNT: CARDBOARD BULKHEADS: BALSA WOOD SHOCKCORD: ABRASION RESISTANT NYLON VEHICLE DESIGN JUSTIFICATIONS VEHICLE MATERIAL CONSIDERATIONS INEXPENSIVE LIGHTWEIGHT MEDIUM-HIGH FLEXURAL STRENGTH MEDIUM-HIGH COMPRESSIVE STRENGTH BALSA WOOD INEXPENSIVE HIGH STRENGTH-TO-WEIGHT-RATIO NYLON EXCELLENT ABRASION RESISTANCE HIGH MELTING POINT WEATHER RESISTANT PROPERTIES BALLISTIC DURABILITY TENSILE STRENGTH UP TO 27000 PSI STATIC STABILITY MARGIN CENTER OF PRESSURE (COP) MUST BE AFTER THE CENTER OF GRAVITY (COG) STATIC MARGIN - “CALIBER OF STABILITY” DISTANCE BETWEEN (COG) AND (COP) ONE BODY TUBE DIAMETER OPENROCKET (COG) = 67.228 IN FROM NOSE CONE TIP (COP) = 74.464 IN FROM NOSE CONE TIP STABILITY MARGIN = 1.81 CAL Vehicle Safety and Verification Critical Vehicle Risks and Mitigation RISK 1 : EJECTION CHARGES DAMAGES VEHICLE. MITIGATION : TEST RECOVERY SYSTEMS MORE CAREFULLY. WEIGHING BLACK POWDER PRECISELY TO PREVENT DAMAGE UPON IGNITION RISK 2 : LANDING IMPACT DAMAGES THE VEHICLE MITIGATION : PROPER TESTING OF RECOVERY SYSTEM AND SIMULATIONS TO PREVENT UNNECESSARY DAMAGES Critical Vehicle Risks and Mitigation (cont.) RISK 3 : TEAM MEMBER IS INJURED BY VEHICLE MITIGATION : MAKE SURE EACH MEMBER IS AWARE OF SURROUNDINGS. PROTOCOLS REVIEWED AND ENFORCED BEFORE ANY FLIGHTS. RISK 4 : MAJOR/MINOR DAMAGE TO PARACHUTE MITIGATION : PARACHUTE PACKING WILL BE SHADOWED BY TEAM MENTOR Critical Vehicle Risks and Mitigation (cont.) RISK 5 : FAILURE OF ALTIMETERS MITIGATION : ITERATIVE TESTING TO MAKE SURE ALTIMETERS ARE FUNCTIONAL. HAVE EXTRA ALTIMETERS IN INVENTORY IN CASE OF EMERGENCY. RISK 6 : FIN SEPARATION FROM VEHICLE MITIGATION : REINFORCE FINS WITH HIGH QUALITY OF ADHESIVE. VERIFY THE SAME DISTANCE BETWEEN FINS TO ENSURE STABILITY. BASELINE MOTOR SELECTION SELECTION CRITERIA CONSIDERED MOTOR SELECTIONS FINAL DECISION Selection Criteria MUST FIT DIAMETER OF VEHICLE MUST NOT REACH SUPERSONIC SPEEDS MUST BE MANUFACTURED FROM CERTIFIED COMPANY MUST FIT ACCORDINGLY WITH DIAMETER OF ROCKET RELOADABLE OR ONE TIME USE? Considered Motor Selections LOKI K-960 ; IMPULSE = 1949 LB.F-S / APOGEE = 6626 FT. LOKI K-690SF ; IMPULSE = 1689 LB.F-S / APOGEE = 5994 FT. CESARONI K-935 ; IMPULSE = 1570 LB.F-S / APOGEE = 6251 FT. GORILLA ROCKET K763GT-P ; IMPULSE = 1725 LB.F-S / APOGEE = 6073 FT. Final Decision LOKI K690-SF DIAMETER OF 2.13 IN. EXCEEDS REQUIRED APOGEE RELOADABLE EXPERIENCED THRUST-TO-WEIGHT RATIO RAIL EXIT VELOCITY OPEN ROCKET THRUST-TO-WEIGHT RATIO = 40.8269 THRUST OF THE MOTOR = 721 N WEIGHT OF THE MOTOR = 17.6599 N RAIL EXIT VELOCITY - “VELOCITY OFF ROD” = 51.4 FT/S LAUNCH VEHICLE VERIFICATION TARGET ALTITUDE OF 5,280 FEET FROM GROUND LEVEL AERODYNAMIC AESTHETICS (NOSECONE & FINS) MOTOR SELECTION OPENROCKET SIMULATIONS FULL LAUNCH VEHICLE FUNCTIONALITY AT LAUNCH TIMED LAUNCH ASSEMBLY PRACTICE WHILE MAINTAINING FUNCTIONALITY DURABILITY TESTING FOR CRITICAL LAUNCH COMPONENTS CAPABILITY TESTING FOR DIRECT CURRENT FIRING SYSTEM TEST PLAN OVERVIEW FOR VEHICLE LAUNCH VEHICLE RECOVERABILITY, REUSABILITY, & DURABILITY DROGUE & MAIN DEPLOYMENT PARACHUTE TESTING ALTIMETER WITH E-MATCH TESTING SIMULATIONS TO OPTIMIZE DEPLOYMENT ALTITUDE LAUNCH VEHICLE REUSABILITY ENSURING STRENGTH OF ATTACHMENT SCHEME AFTER DEPLOYMENT FATIGUE TESTING ON USE OF RECOVERY SYSTEM OVERTIME LAUNCH VEHICLE DURABILITY MATERIALS SELECTION OF VEHICLE ASSEMBLY TOUGHNESS TESTING ON BODY, NOSE CONE, AND FIN DESIGN MAJOR COMPONENT AND SUBSYSTEM RECOVERY SYSTEM REUSEABILITY, RELIABILITY, AND DURABILITY DUAL-DEPLOYMENT SETUP DROGUE AND MAIN PARACHUTE CONTROL DESCENT VELOCITY ROCKET ORIENTATION LANDING IMPACT PREVENT WIND DRIFT ELECTRONICS ELECTRONICS MICROCONTROLLER ARDUINO UNO RASPBERRY PI PIXY CAM DC MOTOR TURBINE E-MATCH ALTIMETERS BASELINE PAYLOAD DESIGN POTENTIAL PAYLOAD OPTIONS ELIMINATION OF OPTIONS FINALIZATION OF SELECTION Potential Payload Options (Choose 2) ATMOSPHERIC MEASUREMENTS PAYLOAD FAIRING DESIGN & DEPLOYMENT LANDING HAZARD DETECTION LIQUID SLOSHING IN MICRO-G PROPULSION SYSTEM ANALYSIS AERODYNAMIC ANALYSIS DESIGN YOUR OWN CENTENNIAL CHALLENGE - MAV Elimination of Options EACH PAYLOAD WAS RATED BY DIFFICULTY AND TIME CONSUMPTION COLLABORATIONS WITH DIFFERENT PROFESSORS PER PAYLOAD COST TEAM EXPERIENCE WITH PAYLOAD OPTIONS Finalization of Selection HAZARDS DETECTION DESIGN YOUR OWN AVAILABLE ELECTRONICS WIND TURBINE GENERATING ELECTRICAL COST EFFICIENT APPLICABLE RESEARCH TOPIC MODERATE DIFFICULTY CURRENT CAN BE RESEARCHED FURTHER ORIGINAL COST EFFICIENT MODERATE DIFFICULTY PAYLOAD VERIFICATION PAYLOADS PIXY CAMERA (CMUCAM5) HAZARD DETECTION PAYLOAD DATALOG RELATIVE CAMERA X & Y COORDINATES ACTUAL COORDINATES FROM RELATIVE CAMERA COORDINATES ARDUINO UNO ANALYSIS IN EXCEL PAYLOAD BAY DEPLOYMENT PAYLOAD VERIFICATION TURBINE DROGUE DEPLOYMENT BACKUP SYSTEM SAFETY SMALL DC MOTOR POWER STORAGE IN CAPACITOR RC CIRCUIT SWITCH CAPACITOR DISCHARGE ZERO VOLTAGE FROM TURBINE APOGEE AMPERAGE FROM DISCHARGE POWER E-MATCH PAYLOAD TESTING PIXY CAM (CMUCAM5) TESTING UNIQUE COLORED OBJECT DESIGNATION DATALOG EACH RELATIVE CAMERA POSITION (X & Y) ARDUINO UNO MEASURE HEIGHT OF CAMERA FROM OBJECT (Z) MEASURE EXACT POSITION OF OBJECT FROM CENTER OF CAMERA (X & Y) LAW OF SINES EQUATION AND FIELD OF VIEW VERIFY EXACT POSITION FROM RELATIVE CAMERA COORDINATES TOLERANCE PAYLOAD TESTING TURBINE TESTING MAX VOLTAGE VERIFICATION WIND TUNNEL MAX VELOCITY FROM OPENROCKET SIMULATION CURRENT VERIFICATION TURBINE WITH CIRCUIT WIND TUNNEL DURATION AND SPEED TO APOGEE OF OPENROCKET SIMULATION TEST RC CIRCUIT WITH SWITCH MEASURE CURRENT OUTPUT CAPACITOR DISCHARGE COMPARE WITH CURRENT FROM STRATOLOGGER DROGUE DEPLOYMENT DISCHARGE