CRITICAL DESIGN PRESENTATION

Transcription

1 CRITICAL DESIGN PRESENTATION UNIVERSITY OF SOUTH ALABAMA LAUNCH SOCIETY BILL BROWN, BEECHER FAUST, ROCKWELL GARRIDO, CARSON SCHAFF, MICHAEL WIESNETH, MATTHEW WOJCIECHOWSKI ADVISOR: CARLOS MONTALVO MENTOR: CHRIS CREWS

2 Vehicle Dimensions OVERALL LENGTH: 93 BODY DIAMETER: 5 LIFT OFF WEIGHT: LBS COUPLER LENGTH ( AVIONICS BAY): 11 NOSE CONE LENGTH: 20 BODY LENGTH: 73 NOSE CONE SHAPE: OGIVE COMPONENT MATERIAL: FIBERGLASS

3 Fin Dimensions FIN DESIGN: CLIPPED DELTA NUMBER OF FINS: 4 ROOT CORD: 10 TIP CORD: 5 SWEEP LENGTH: 5 SWEEP ANGLE: 45

4 Final Motor Choice MOTOR SELECTED: K480W-P TOTAL IMPULSE: LBF-S WITH THE ESTIMATED MASS OF THE LAUNCH VEHICLE THIS MOTOR ACHIEVED AN ALTITUDE OF 5280 FT. THIS WAS SIMULATED USING OPENROCKET.

5 STABILITY AT RAIL EXIT = 2.5 STATIC STABILITY = 2.5

6 Center of Pressure and Center of Gravity Locations CENTER OF PRESSURE = IN FROM NOSE CONE CENTER OF GRAVITY = IN FROM NOSE CONE SIMULATED USING OPENROCKET \

7 Thrust to Weight Ratio and Rail Exit Velocity MAX THRUST / WEIGHT = LB /19.06 LB = 6.53 RAIL EXIT VELOCITY = 67.1 SIMULATED IN OPENROCKET FT/S

8 Mass Statement and Mass Margin TOTAL MASS LOADED = LB TOTAL MASS EMPTY =16.38 LB ADJUSTABLE MASS MARGIN = 1.15 LB

9 Recovery Subsystem - Parachutes DROGUE PARACHUTE: 36 IN NYLON MAIN PARACHUTE: 72 IN NYLON CONICAL W/ SPILL HOLE RECOVERY HARNESS: KEVLAR TIED TO WELDED EYEBOLTS KEVLAR SIZE: 0.55 IN HARNESS LENGTH: 24 FT DROGUE DESCENT RATE: 51.1 FT/S MAIN DESCENT RATE: 22.6 FT/S

10 Kinetic Energy At Key Phases THESE VALUES CORRESPOND TO BOOSTER SECTION OF THE VEHICLE WHICH HAS A MASS OF.3 LBM MAIN CHUTE DEPLOYMENT = FT-LBS LANDING = FT-LBS

11 Predicted Drift from Launch Pad 5 MPH WIND: 425 FT 10 MPH WIND: 875 FT 15 MPH WIND: 1325 FT 20 MPH WIND: 2020 FT

12 FINAL PAYLOAD DESIGN FINAL ROLL INDUCTION SYSTEM DESIGN FINAL VERIFICATION SYSTEM ELECTRICAL PAYLOAD COMPONENTS AND HARDWARE PAYLOAD CONSTRUCTION AND INTEGRATION PAYLOAD SAFETY DESIGN CRITERIA

13 Final Roll Induction System 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

14 Roll Fin Functionality and Design ROLL FIN WILL BE PLACED INSIDE THE MAIN FIN AND FIXED TO SERVO SHAFT ROLL WILL BE INDUCED IN ROCKET BY DEFLECTING ROLL FINS INTO AIR STREAM AIR DRAG WILL CREATE ROLL MOMENT

15 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

16 Electrical Payload Components ARDUINO MEGA MICROCONTROLLER USED FOR SENSOR COMMUNICATION AND SERVO OUTPUT

17 Electrical Payload Components 10 DOF IMU BREAKOUT MAIN DATA COLLECTION DEVICE USED IN THE ROLL INDUCTION SYSTEM ROTATIONAL VELOCITY AND ORIENTATION DATA WILL BE USED TO GOVERN THE SERVO OUTPUT DATA WILL BE STORED ON A MICROSD FOR PAYLOAD OBJECTIVE COMPLETION VERIFICATION

18 Electrical Payload Components GPS BREAKOUT WILL PROVIDE A DATA TIMESTAMP TO BE USED IN THE VERIFICATION SYSTEM

19 Hardware Payload Components PAYLOAD COUPLER 10 INCH FIBERGLASS BAY 0.08 INCH WALL THICKNESS

20 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

21 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

22 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

23 Payload Integration BULKHEAD CLOSES UP ONE END INSERT CENTER ROD INSERT ELECTRONICS SLED SEAL PAYLOAD WITH SECOND BULKHEAD

24 Payload Integration SERVO INSERTED INTO PLACE FROM INSIDE THE ROCKET BODY CENTERING PIN LINKING SERVO TO MAIN FIN

25 Payload Integration ASSEMBLED FROM OUTSIDE THE ROCKET INSERTED THROUGH THE REAR OF THE ROCKET

26 Payload Safety Design Criteria NET FORCE INDUCED IN THE ROCKET MUST BE ZERO THE ROLL MOMENT INDUCED BY THE ROLL FINS MUST BE A COUPLE MOMENT

27 Payload Safety Design Criteria SERVO HORN TO ROLL FIN CONNECTION THE CONNECTION MUST BE COMPLETELY RIGID SLIPPING COULD LEAD TO ANGULAR OFFSET RESULTING IN RESIDUAL FORCE SLIPPING BETWEEN THE SERVO SHAFT AND THE ROLL FIN WILL BE MINIMIZED USING A HEXAGONAL SHAFT

28 Payload Safety Design Criteria HEAT SHIELD TUBING HIGH HEAT EXPOSURE TO SERVO WIRES COULD LEAD TO ELECTRONIC MALFUNCTION ALUMINUM HEAT SHIELD TUBING WILL BE USED TO MINIMIZE THE HEAT EXPOSURE FROM THE MOTOR TO THE WIRES

29 Payload Mathematical Model ROCKWELL Step input of 0 or 1 from the command generator KP: proportional gain applied to the step signal : servo angle G: rocket φa: roll angle of the rocket

30 Payload Electronic Schematic

31 TESTING SERVO LOAD GPS - SERVO COMPATABILITY POWER COMSUMPTION BATTERY DURRATION

32 Testing of Staged Recovery System THE TEAM WILL UTILIZE THE SAME DUAL DEPLOY RECOVERY SYSTEM AS USED IN ROCKETS FOR PRELIMINARY ROCKETS ALTIMETERS HAVE BEEN TESTED FOR FUNCTIONALITY

33 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

34 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

35 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

36 References 1) Time-Domain Characteristics on Response Plot. (2016). Retrieved from 2) Fried, Limor.Adafruit. N.p., n.d. Web. 2 Nov ) Miguel, V. S. (2012). Mathematically Modeling Aeroelastic Flutter. Retrieved from