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