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