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FRRPRESENTATION
UNIVERSITY OF SOUTH ALABAMA LAUNCH SOCIETY
BILL BROWN, BEECHER FAUST, ROCKWELL GARRIDO, CARSON SCHAFF, MICHAEL WIESNETH, MATTHEW
WOJCIECHOWSKI
ADVISOR: CARLOS MONTALVO
MENTOR: CHRIS CREWS
Vehicle DimensionsOVERALL LENGTH: 93” BODY DIAMETER: 5” LIFT OFF WEIGHT: 22..93 LBS COUPLER LENGTH (
AVIONICS BAY): 11”
NOSE CONE LENGTH: 20” BODY
LENGTH: 73”
NOSE CONE SHAPE: OGIVE COMPONENT
MATERIAL: FIBERGLASS
Key Vehicle Design Features
● Clipped Delta fin planform
● Aluminum tubing to shield servo wires
● Roll fin stabilization bracket
● Screw cap motor retention
FINAL PAYLOAD DESIGN
• FINAL ROLL INDUCTION SYSTEM DESIGN
• FINAL VERIFICATION SYSTEM
• ELECTRICAL PAYLOAD COMPONENTS AND HARDWARE
• PAYLOAD CONSTRUCTION AND INTEGRATION
• PAYLOAD SAFETY DESIGN CRITERIA
Final Roll InductionSystem Design
• ROLL FINS WILL BE CONNECTED DIRECTLY
TO TWO SEPARATE SERVOS
• AN ARDUINO MEGA WILL SEND EQUIVALENT
SIGNALS TO BOTH SERVOS TO ENSURE
EQUAL ROLL FIN DEFLECTION
Roll Fin Functionality and Design
• ROLL FIN WILL BE PLACED INSIDE THE
MAIN FIN AND FIXED TO SERVO SHAFT
• MAX VELOCITY START CONDITION - 200 FT/S
• ROLL FIN CANT PROFILE WILL BE
• 3 SECONDS +45 DEGREES
• 2 SECONDS -45 DEGREES
• 1 SECOND NEUTRAL
Final Verification System Design
• DUAL SENSOR REDUNDANCY TO BE USED AS VERIFICATION
METHOD
• DATA WILL BE RECORDED ONTO AN MICROSD CARD
TO BE OBSERVED POST FLIGHT
• BOTH SENSORS SHOWING COMPLETION OF PAYLOAD OBJECTIVE
WILL SERVE AS SUCCESS CRITERIA
Main Controller Constructed
Electrical Payload Components
ARDUINO MEGA
• MICROCONTROLLER USED FOR SENSOR
COMMUNICATION AND SERVO OUTPUT
Electrical Payload Components
10 DOF IMU BREAKOUT
• MAIN DATA COLLECTION DEVICE USED IN THE ROLL
INDUCTION SYSTEM
• ROTATIONAL VELOCITY AND ORIENTATION WILL
BE COLLECTED
• DATA WILL BE STORED ON A MICROSD FOR
PAYLOAD OBJECTIVE COMPLETION VERIFICATION
Electrical Payload Components
9 DOF IMU BREAKOUT
• POSSESSES SIMILAR CAPABILITIES AND COMPONENTS
OF THE 10 DOF
• DATA WILL BE STORED ON A MICROSD FOR
PAYLOAD OBJECTIVE COMPLETION VERIFICATION
Electrical Payload Components
GPS BREAKOUT
• WILL PROVIDE A DATA TIMESTAMP TO BE USED IN THE
VERIFICATION SYSTEM
Electrical Payload Components
MICROSD BREAKOUT
• ROLL RATE AND ORIENTATION DATA WILL BE
STORED FOR POST FLIGHT ANALYSIS
Hardware Payload Components
PAYLOAD COUPLER
• 9 INCH FIBERGLASS BAY
• 0.08 INCH WALL THICKNESS
Hardware Payload Components
BULKHEAD END CAPS
• USED TO SEAL BOTH ENDS OF THE PAYLOAD
COUPLER TUBE
• PROTECTS PAYLOAD FROM BLACKPOWDER
EXPLOSIONS NECESSARY FOR CHUTE DEPLOYMENT
Hardware Payload Components
ELECTRONICS SLED
• 3D PRINTED WITH MOUNTING HOLES
COMPATIBLE WITH THE ARDUINO MEGA
• BATTERY COMPARTMENT WILL BE USED
TO SECURE THE POWER SOURCE
Hardware Payload Components
TOWER PRO MG995R HIGH TORQUE SERVO
• ONE SERVO WILL BE CONNECTED TO EACH OF THE
TWO ROLL FINS
• SERVO HORN WILL BE MOUNTED DIRECTLY TO THE
ROLL FIN
Motor Description
MOTOR SELECTED: K480W-P
TOTAL IMPULSE: 515.93 LBF-S
WITH THE AS BUILT MASS OF THE LAUNCH VEHICLE THIS MOTOR ACHIEVED AN ALTITUDE OF
4538 FT.
AS SIMULATED USING OPENROCKET AND ACTUAL MASSES OF THE FULL SCALE ROCKET.
STABILITY AT RAIL EXIT = 2.6
STATIC STABILITY = 2.62
Center of Pressure and Center of Gravity Locations
CENTER OF PRESSURE = 72.8 IN FROM NOSE CONE
CENTER OF GRAVITY = 59.3 IN FROM NOSE CONE
THESE ARE ACTUAL VALUES OBTAINED WITH THE FULL SCALE VEHICLE
\
Thrust to Weight Ratio and Rail Exit Velocity
AVERAGE THRUST / WEIGHT = 124.54 LB /22.93 LB = 5.43
RAIL EXIT VELOCITY = 61 FT/S
THIS IS ABOVE THE MINIMUM OF 52 FT/S
OPENROCKET SIMULATION WITH ACTUAL MASSES OF THE FULL SCALE VEHICLE
Mass Statement
TOTAL MASS WITH LOADED MOTOR = 22.93 LB
TOTAL MASS WITH EMPTY MOTOR =20.22 LB
Recovery Subsystem - Parachutes
DROGUE PARACHUTE: 24” NYLON
MAIN PARACHUTE: 84” NYLON
RECOVERY HARNESS: KEVLAR TIED TO WELDED EYEBOLTS
KEVLAR SIZE: 0.55 IN
HARNESS LENGTH: 24 FT
DROGUE DESCENT RATE: 85.9 FT/S
MAIN DESCENT RATE: 23.3 FT/S
Kinetic Energy At Key Phases
WHEN MAIN PARACHUTE DEPLOYS THE BOOSTER SECTION EXPERIENCES 653 FT-LBS
THESE VALUES ARE FOR LANDING IMPACT
Predicted Drift and Altitude
DRIFT DISTANCE ALTITUDE
5 MPH WIND: 150 FT 4526 FT
10 MPH WIND: 250 FT 4486 FT
15 MPH WIND: 550 FT 4441 FT
20 MPH WIND: 850 FT 4371 FT
Payload Integration
BULKHEAD CLOSES UP ONE END
INSERT CENTER ROD
INSERT ELECTRONICS SLED
SEAL PAYLOAD WITH SECOND BULKHEAD
Payload Integration
SERVO INSERTED INTO PLACE FROM OUTSIDE THE ROCKET BODY
CENTERING PIN LINKING SERVO TO MAIN FIN
Payload Integration
ASSEMBLED FROM OUTSIDE THE ROCKET
INSERTED THROUGH THE REAR OF THE ROCKET
Testing
• SOFTWARE TESTING
• HARDWARE TESTING
• PAYLOAD TESTING
Software Testing
• PRELIMINARY DATA COLLECTION TEST
• GPS AND SERVO COMPATIBILITY
• SIMULTANEOUS I2C PORT READING
Hardware Testing
• SERVO TORQUE OUTPUT TEST
• CONTROL SYSTEM BATTERY LIFE TEST
Payload Testing
• MAKESHIFT PAYLOAD CONSTRUCTED
• TESTING IN WIND TUNNEL
• MAX SPEED 88 FT/S
Payload Testing• CANTILEVER SUPPORT SYSTEM
• 4 SUPPORTS FOR DISTRIBUTED LOAD
• BEARING SYSTEM TO ALLOW ISOLATED ROTATION
• BEARINGS FIXED INSIDE SUPPORTS
Payload Testing• ENTIRE ROCKET PLACED IN WIND TUNNEL
• WEIGHTS USED TO COUNTERBALANCE
• CANT PROFILE
• 10 SECONDS +45
• 5 SECONDS -45
• 5 SECONDS NEUTRAL
Payload Testing Results
• ROLL INDUCTION OF 6.9 REVOLUTIONS OVER 10 SECONDS
• COUNTER ROLL STABILITY NEUTRALIZED ROLL
Full Scale Flight Test
MOTOR USED = AEROTECH K535W-14A
FULL SCALE THRUST TO WEIGHT RATIO: 5.38
APOGEE: 1881 FT
SIMULATION APOGEE: 2466 FT
MAX VELOCITY: 231 FT/S
Launch Results
• KEVLAR FAILED AFTER MAIN CHUTE DEPLOYMENT
• BOOSTER SECTION DETACHED
• FREE DESCENT OF 700 FT
• ELECTRONICS DESTROYED UPON IMPACT
• MAJORITY OF ROCKET SALVAGEABLE
• PLAN TO LAUNCH 3/11 IF ALLOWED
Recovery System Tests
• THE TEAM WILL UTILIZE THE SAME DUAL
DEPLOY RECOVERY SYSTEM AS USED IN
PRELIMINARY ROCKETS
• ALTIMETERS HAVE BEEN TESTED FOR
FUNCTIONALITY
• GROUND IGNITION TESTS SUCCESSFUL
Updated Team Derived Requirements
● Team must produce optimal roll
fin system
Verification: A square roll fin has been
chosen as this design provides simplicity
for airflow analysis
Updated Team Derived Requirements (cont.)
● Equalize Roll Fin Deflection
Verification: Hexagonal cross section will
be used for servo to roll fin shaft to
minimize potential for angular offset
between the servo and roll fin
Updated Team Derived Requirements (cont.)
● Implementation of derivative
gain to reduce overshoot
Verification: Team is pursuing an open
loop control system as this should
provide sufficient functionality
Interfaces With Ground Systems
• THE FULL SCALE TEST LAUNCH ENSURED THAT
THE VEHICLE IS COMPATIBLE WITH STANDARD
LAUNCH RAILS AND LAUNCH PADS
• A TRANSMITTER IS FIXED IN THE ROCKET TO ALL
THE ROCKET TO BE TRACKED THROUGHOUT ITS
FLIGHT
References1) Time-Domain Characteristics on Response Plot. (2016). Retrieved from https://www.mathworks.com/help/control/ug/view-system-
characteristics-on-response-plots.html
2) Fried, Limor.Adafruit. N.p., n.d. Web. 2 Nov. 2016. https://www.adafruit.com
3) Miguel, V. S. (2012). Mathematically Modeling Aeroelastic Flutter. Retrieved from http://www.personal.psu.edu/vjs5077/projects/fin-
flutter.html
https://www.adafruit.com
Acknowledgements
We would like to thank the Alabama Space
Grant Consortium for providing generous
funds to support this project.
Structure BookmarksSlideSpanFRRFRRFRR
PRESENTATIONPRESENTATION
UUUNIVERSITYOFSOUTHALABAMALAUNCHSOCIETY
BBILLBROWN, BEECHERFAUST, ROCKWELLGARRIDO, CARSONSCHAFF, MICHAELWIESNETH, MATTHEWWOJCIECHOWSKI
AADVISOR: CARLOSMONTALVO
MMENTOR: CHRISCREWS
SlideSpanFigureVehicle DimensionsVehicle DimensionsVehicle Dimensions
OOOVERALLLENGTH: 93”BODYDIAMETER: 5”
LLIFTOFFWEIGHT: 22..93 LBSCOUPLERLENGTH( AVIONICSBAY): 11”
NNOSECONELENGTH: 20”BODYLENGTH: 73”
NNOSECONESHAPE: OGIVECOMPONENTMATERIAL: FIBERGLASS
SlideSpanKey Vehicle Design FeaturesKey Vehicle Design FeaturesKey Vehicle Design Features
●●●●●Clipped Delta fin planform
●●●Aluminum tubing to shield servo wires
●●●Roll fin stabilization bracket
●●●Screw cap motor retention
FigureFigure
SlideSpanFINALFINALFINALPAYLOAD DESIGN
•••••FINALROLLINDUCTIONSYSTEMDESIGN
•••FINALVERIFICATIONSYSTEM
•••ELECTRICALPAYLOADCOMPONENTSANDHARDWARE
•••PAYLOADCONSTRUCTIONANDINTEGRATION
•••PAYLOADSAFETYDESIGNCRITERIA
SlideSpanFinal Roll InductionFinal Roll InductionFinal Roll Induction
System DesignSystem Design
•••••ROLLFINSWILLBECONNECTEDDIRECTLY
TOTOTWOSEPARATESERVOS
••••ANARDUINOMEGAWILLSENDEQUIVALENT
SIGNALSSIGNALSTOBOTHSERVOSTOENSURE
EQUALEQUALROLLFINDEFLECTION
Figure
SlideSpanRoll Fin Functionality and DesignRoll Fin Functionality and DesignRoll Fin Functionality and Design
•••••ROLLFINWILLBEPLACEDINSIDETHE
MAINMAINFINANDFIXEDTOSERVOSHAFT
••••MAXVELOCITYSTARTCONDITION-200 FT/S
•••ROLLFINCANTPROFILEWILLBE
••••3 SECONDS+45 DEGREES
•••2 SECONDS-45 DEGREES
•••1 SECONDNEUTRAL
Figure
SlideSpanFinal Verification System DesignFinal Verification System DesignFinal Verification System Design
•••••DUALSENSORREDUNDANCYTOBEUSEDASVERIFICATION
METHODMETHOD
••••DATAWILLBERECORDEDONTOANMICROSD CARD
TOTOBEOBSERVEDPOSTFLIGHT
••••BOTHSENSORSSHOWINGCOMPLETIONOFPAYLOADOBJECTIVE
WILLWILLSERVEASSUCCESSCRITERIA
Figure
SlideSpanMain Controller ConstructedMain Controller ConstructedMain Controller Constructed
Figure
SlideSpanElectrical Payload ComponentsElectrical Payload ComponentsElectrical Payload Components
AAARDUINOMEGA
••••MICROCONTROLLERUSEDFORSENSOR
COMMUNICATIONCOMMUNICATIONANDSERVOOUTPUT
Figure
SlideSpanElectrical Payload ComponentsElectrical Payload ComponentsElectrical Payload Components
10 DOF IMU B10 DOF IMU B10 DOF IMU BREAKOUT
••••MAINDATACOLLECTIONDEVICEUSEDINTHEROLL
INDUCTIONINDUCTIONSYSTEM
••••ROTATIONALVELOCITYANDORIENTATIONWILL
BEBECOLLECTED
••••DATAWILLBESTOREDONAMICROSD FOR
PAYLOADPAYLOADOBJECTIVECOMPLETIONVERIFICATION
Figure
SlideSpanElectrical Payload ComponentsElectrical Payload ComponentsElectrical Payload Components
9 DOF IMU B9 DOF IMU B9 DOF IMU BREAKOUT
••••POSSESSESSIMILARCAPABILITIESANDCOMPONENTS
OFOFTHE10 DOF
••••DATAWILLBESTOREDONAMICROSD FOR
PAYLOADPAYLOADOBJECTIVECOMPLETIONVERIFICATION
Figure
SlideSpanElectrical Payload ComponentsElectrical Payload ComponentsElectrical Payload Components
GPS BGPS BGPS BREAKOUT
••••WILLPROVIDEADATATIMESTAMPTOBEUSEDINTHE
VERIFICATIONVERIFICATIONSYSTEM
Figure
SlideSpanElectrical Payload ComponentsElectrical Payload ComponentsElectrical Payload Components
MMMICROSD BREAKOUT
••••ROLLRATEANDORIENTATIONDATAWILLBE
STOREDSTOREDFORPOSTFLIGHTANALYSIS
Figure
SlideSpanHardware Payload ComponentsHardware Payload ComponentsHardware Payload Components
PPPAYLOADCOUPLER
••••9 INCHFIBERGLASSBAY
•••0.08 INCHWALLTHICKNESS
Figure
SlideSpanHardware Payload ComponentsHardware Payload ComponentsHardware Payload Components
BBBULKHEADENDCAPS
••••USEDTOSEALBOTHENDSOFTHEPAYLOAD
COUPLERCOUPLERTUBE
••••PROTECTSPAYLOADFROMBLACKPOWDER
EXPLOSIONSEXPLOSIONSNECESSARYFORCHUTEDEPLOYMENT
Figure
SlideSpanHardware Payload Components Hardware Payload Components Hardware Payload Components
EEELECTRONICSSLED
••••3D PRINTEDWITHMOUNTINGHOLES
COMPATIBLECOMPATIBLEWITHTHEARDUINOMEGA
••••BATTERYCOMPARTMENTWILLBEUSED
TOTOSECURETHEPOWERSOURCE
Figure
SlideSpanHardware Payload ComponentsHardware Payload ComponentsHardware Payload Components
TTTOWERPROMG995R HIGHTORQUESERVO
••••ONESERVOWILLBECONNECTEDTOEACHOFTHE
TWOTWOROLLFINS
••••SERVOHORNWILLBEMOUNTEDDIRECTLYTOTHE
ROLLROLLFIN
Figure
SlideSpanMotor DescriptionMotor DescriptionMotor Description
MMMOTORSELECTED: K480W-P
TTOTALIMPULSE: 515.93 LBF-S
WWITHTHEASBUILTMASSOFTHELAUNCHVEHICLETHISMOTORACHIEVEDANALTITUDEOF4538 FT.
AASSIMULATEDUSINGOPENROCKETANDACTUALMASSESOFTHEFULLSCALEROCKET.
Figure
SlideSpanFigureSSSTABILITYATRAILEXIT= 2.6
SSTATICSTABILITY= 2.62
Figure
SlideSpanCenter of Pressure and Center of Gravity LocationsCenter of Pressure and Center of Gravity LocationsCenter of Pressure and Center of Gravity Locations
CCCENTEROFPRESSURE= 72.8 INFROMNOSECONE
CCENTEROFGRAVITY= 59.3 INFROMNOSECONE
TTHESEAREACTUALVALUESOBTAINEDWITHTHEFULLSCALEVEHICLE
\\
SlideSpanThrust to Weight Ratio and Rail Exit VelocityThrust to Weight Ratio and Rail Exit VelocityThrust to Weight Ratio and Rail Exit Velocity
AAAVERAGETHRUST/ WEIGHT= 124.54 LB/22.93 LB= 5.43
RRAILEXITVELOCITY= 61 FT/S
THISTHISISABOVETHEMINIMUMOF52 FT/S
OOPENROCKETSIMULATIONWITHACTUALMASSESOFTHEFULLSCALEVEHICLE
SlideSpanMass StatementMass StatementMass Statement
TTTOTALMASSWITHLOADEDMOTOR= 22.93 LB
TTOTALMASSWITHEMPTYMOTOR=20.22 LB
FigureFigure
SlideSpanRecovery Subsystem Recovery Subsystem Recovery Subsystem -Parachutes
DDDROGUEPARACHUTE: 24” NYLON
MMAINPARACHUTE: 84” NYLON
RRECOVERYHARNESS: KEVLARTIEDTOWELDEDEYEBOLTS
KKEVLARSIZE: 0.55 IN
HHARNESSLENGTH: 24 FT
DDROGUEDESCENTRATE: 85.9 FT/S
MMAINDESCENTRATE: 23.3 FT/S
SlideSpanFigureFigureKinetic Energy At Key PhasesKinetic Energy At Key PhasesKinetic Energy At Key Phases
WWWHENMAINPARACHUTEDEPLOYSTHEBOOSTERSECTIONEXPERIENCES653 FT-LBS
TTHESEVALUESAREFORLANDINGIMPACT
SlideSpanFigurePredicted Drift and AltitudePredicted Drift and AltitudePredicted Drift and Altitude
DDDRIFTDISTANCEALTITUDE
5 5 MPHWIND: 150 FT4526 FT
10 10 MPHWIND: 250 FT4486 FT
15 15 MPHWIND: 550 FT4441 FT
20 20 MPHWIND: 850 FT4371 FT
SlideSpanPayload IntegrationPayload IntegrationPayload Integration
BBBULKHEADCLOSESUPONEEND
IINSERTCENTERROD
IINSERTELECTRONICSSLED
SSEALPAYLOADWITHSECONDBULKHEAD
Figure
SlideSpanPayload IntegrationPayload IntegrationPayload Integration
SSSERVOINSERTEDINTOPLACEFROMOUTSIDETHEROCKETBODY
CCENTERINGPINLINKINGSERVOTOMAINFIN
Figure
SlideSpanPayload IntegrationPayload IntegrationPayload Integration
ASSEMBLEDASSEMBLEDASSEMBLEDFROMOUTSIDETHEROCKET
IINSERTEDTHROUGHTHEREAROFTHEROCKET
Figure
SlideSpanTestingTestingTesting
•••••SOFTWARETESTING
•••HARDWARETESTING
•••PAYLOADTESTING
Figure
SlideSpanSoftware TestingSoftware TestingSoftware Testing
•••••PRELIMINARYDATACOLLECTIONTEST
•••GPS ANDSERVOCOMPATIBILITY
•••SIMULTANEOUSI2C PORTREADING
Figure
SlideSpanHardware TestingHardware TestingHardware Testing
•••••SERVOTORQUEOUTPUTTEST
•••CONTROLSYSTEMBATTERYLIFETEST
Figure
SlideSpanPayload TestingPayload TestingPayload Testing
•••••MAKESHIFTPAYLOADCONSTRUCTED
•••TESTINGINWINDTUNNEL
••••MAXSPEED88 FT/S
Figure
SlideSpanPayload TestingPayload TestingPayload Testing
•••••CANTILEVERSUPPORTSYSTEM
••••4 SUPPORTSFORDISTRIBUTEDLOAD
•••BEARINGSYSTEMTOALLOWISOLATEDROTATION
••••BEARINGSFIXEDINSIDESUPPORTS
Figure
SlideSpanPayload TestingPayload TestingPayload Testing
•••••ENTIREROCKETPLACEDINWINDTUNNEL
••••WEIGHTSUSEDTOCOUNTERBALANCE
•••CANTPROFILE
••••10 SECONDS+45
•••5 SECONDS-45
•••5 SECONDSNEUTRAL
Figure
SlideSpanPayload Testing ResultsPayload Testing ResultsPayload Testing Results
•••••ROLLINDUCTIONOF6.9 REVOLUTIONSOVER10 SECONDS
•••COUNTERROLLSTABILITYNEUTRALIZEDROLL
FigureFigure
SlideSpanFull Scale Flight TestFull Scale Flight TestFull Scale Flight Test
MMMOTORUSED= AEROTECHK535W-14A
FFULLSCALETHRUSTTOWEIGHTRATIO: 5.38
AAPOGEE: 1881 FT
SSIMULATIONAPOGEE: 2466 FT
MMAXVELOCITY: 231 FT/S
Figure
SlideSpanLaunch ResultsLaunch ResultsLaunch Results
•••••KEVLARFAILEDAFTERMAINCHUTEDEPLOYMENT
•••BOOSTERSECTIONDETACHED
••••FREEDESCENTOF700 FT
•••ELECTRONICSDESTROYEDUPONIMPACT
•••MAJORITYOFROCKETSALVAGEABLE
••••PLANTOLAUNCH3/11 IFALLOWED
SlideSpanRecovery System TestsRecovery System TestsRecovery System Tests
•••••THETEAMWILLUTILIZETHESAMEDUALDEPLOYRECOVERYSYSTEMASUSEDINPRELIMINARYROCKETS
•••ALTIMETERSHAVEBEENTESTEDFORFUNCTIONALITY
•••GROUNDIGNITIONTESTSSUCCESSFUL
Figure
SlideSpanUpdated Team Derived RequirementsUpdated Team Derived RequirementsUpdated Team Derived Requirements
●●●●●Team must produce optimal roll fin system
Verification: A square roll fin has been Verification: A square roll fin has been Verification: A square roll fin has been chosen as this design provides simplicity for airflow analysis
Figure
SlideSpanUpdated Team Derived Requirements (cont.)Updated Team Derived Requirements (cont.)Updated Team Derived Requirements (cont.)
●●●●●Equalize Roll Fin Deflection
Verification: Hexagonal cross section will Verification: Hexagonal cross section will Verification: Hexagonal cross section will be used for servo to roll fin shaft to minimize potential for angular offset between the servo and roll fin
Figure
SlideSpanUpdated Team Derived Requirements (cont.)Updated Team Derived Requirements (cont.)Updated Team Derived Requirements (cont.)
●●●●●Implementation of derivative gain to reduce overshoot
Verification: Team is pursuing an open Verification: Team is pursuing an open Verification: Team is pursuing an open loop control system as this should provide sufficient functionality
Figure
SlideSpanInterfaces With Ground SystemsInterfaces With Ground SystemsInterfaces With Ground Systems
FigureSpan•••••THEFULLSCALETESTLAUNCHENSUREDTHATTHEVEHICLEISCOMPATIBLEWITHSTANDARDLAUNCHRAILSANDLAUNCHPADS
•••A TRANSMITTERISFIXEDINTHEROCKETTOALLTHEROCKETTOBETRACKEDTHROUGHOUTITSFLIGHT
Figure
SlideSpanReferencesReferencesReferences
1) Time1) Time1) Time-Domain Characteristics on Response Plot. (2016). Retrieved from https://www.mathworks.com/help/control/ug/view-system-characteristics-on-response-plots.html
2) Fried, Limor.Adafruit. N.p., n.d. Web. 2 Nov. 2016. 2) Fried, Limor.Adafruit. N.p., n.d. Web. 2 Nov. 2016. https://www.adafruit.comhttps://www.adafruit.comSpan
3) Miguel, V. S. (2012). Mathematically Modeling Aeroelastic Flutter. Retrieved from http://www.personal.psu.edu/vjs5077/proj3) Miguel, V. S. (2012). Mathematically Modeling Aeroelastic Flutter. Retrieved from http://www.personal.psu.edu/vjs5077/projects/fin-flutter.html
SlideSpanAcknowledgementsAcknowledgementsAcknowledgements
We would like to thank the Alabama Space We would like to thank the Alabama Space We would like to thank the Alabama Space Grant Consortium for providing generous funds to support this project.
Figure