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CanSat 2012 CDR Outline Version 0.4

CanSat 2012 CDR Outline Version 0.4. Team #1719 Tarleton Aeronautical Team. Presentation Outline. ## Title. 6 7 8 11-13 14-18 19 20 21 23 27 28 29 30-31 33-34 35 36-37 40-41 42 44. Systems Overview Mission Summary Summary of Changes since PDR

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CanSat 2012 CDR Outline Version 0.4

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  1. CanSat 2012 CDR OutlineVersion 0.4 Team #1719 Tarleton Aeronautical Team CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  2. Presentation Outline ## Title 6 7 8 11-13 14-18 19 20 21 23 27 28 29 30-31 33-34 35 36-37 40-41 42 44 Systems Overview Mission Summary Summary of Changes since PDR System Concepts of Operations Physical Layout Launch vehicle compatability Sensor Subsystem Design Sensor Subsystem Overview Sensor Changes since PDR Descent Control Design Descent Control Overview Descent Control Changes since PDR Descent Control Hardware Summary Descent Rate Estimates Mechanical Subsystem Design Mechanical System Overview & changes since PDR Lander Egg Protection Mechanical Layout of Components Carrier Lander Interface CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  3. Presentation Outline ## Title 48 49 50 55 57-58 60 62-64 66-67 70 72-74 77-78 80-81 84-85 87-88 89 90 102 114 Communication & Data Handling Overview CDH Overview Changes since PDR Carrier Antenna Selection Radio Configuration Telemetry Transmission Electrical Power Subsystem Electrical Block Diagrams Power Source Selection Flight Software Overview Carrier Overview Lander Overview Ground Control Station GCS Antenna GCS Software CanSat Integration & Test Mission Operations & Analysis Conclusions CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  4. Team Organization Presenter: Cletus Fuhrmann CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  5. Acronyms • A – analysis • ACL – acceleration • ADC – Analog to digital convertor • ALD – audible locating device • ALT – altitude • ASI – asynchronous serial interface • BMR – base mission requirement • bps – bits per second • CDH – communication and data handling • CMOS – Complimentary Metal oxide semi- conductor • COTS – Commercial off the shelf • D – demonstration • dB - decibels • DCS – Descent Control System • DIO – digital input\output • EPS – Electrical Power System • FSC – Flight Software of Carrier • FSL – Flight Software of Lander • FSW – flight software • G – G force • g-gram • GHz-Gigahertz • GCS – Ground Control Station • GPS – global positioning system • hPA – hectoPascal • Hz – hertz • I – inspection • I2C – Inter-integrate circuit • IDE – Integrated development environment • lb – pound • LED – Light Emitting Diode • m – meter • m/s – meters per second • mA – milliamps • MAC – Media access control • MEC – Mechanical Requirement • mg – milligrams • mm – millimeters • mW - milliwatts Presenter: Cletus Fuhrmann CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  6. Acronyms (continued) • NASA – National Aeronautics and Space Administration • PDR – Preliminary Design Review • RF – radiofrequency • SD – secure digital • SMA-SubMiniature version A • SPI –Serial Peripheral Interface • SSR – Sensor Subsystem requirement • SYS – System Requirement • T – Test • TEM – Temperature • TTL –Transistor–transistor logic • TNC-Threaded Neill-Concelman • UART – Universal asynchronous receiver/transmitter • USLI – University Student Launch Initiative • UTC - Coordinate Universal Time • V - Volts Presenter: Cletus Fuhrmann CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  7. Systems Overview Cletus Fuhrmann CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team) )

  8. Mission Summary Launch an autonomous Cansat with a deployable lander that ensures the safe descent of a large raw hen’s egg - Descent rate must be controlled throughout - Deployment must occur at a set altitude - Sensors must collect a variety of data during flight - Some data must be transmitted to a ground station - All data must be collected and analyzed Main Objective Selected Objective Measure the lander’s force of impact with the ground External Objective Gain familiarity with subject for NASA USLI competition Presenter: Cletus Fuhrmann CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  9. Summary of Changes Since PDR • Sensor Subsystem • Descent Control Subsystem • Mechanical Subsystem • Communication & Data Handling • Electrical Power Subsystem • Flight Software Design • Ground Control Station Presenter: Cletus Fuhrmann CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  10. System Requirements Presenter: Cletus Fuhrmann Cansat 2012 PDR: Team 1719 (Tarleton Aeronautical Team)

  11. System Requirements Presenter: Cletus Fuhrmann Cansat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  12. System Concept of Operations Launch Operations Assemble Cansat Presenter: Cletus Fuhrmann CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  13. System Concept of Operations At 200 meters 2nd parachute deployed Rocket separates at apex Payload deploys first parachute Carrier & Lander separate Sensors still recording Carrier sending data Lander storing data CanSat sensors running Communicating data to GS Lander records impact force In-Flight Operations Presenter: Cletus Fuhrmann CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  14. System Concept of Operations Post-launch recovery and data reduction Presenter: Blake lohn-Wilie CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  15. Physical Layout Presenter: Greg Mosier CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  16. Physical Layout - Carrier 114mm 20mm 27mm 152mm 103mm Presenter: Greg Mosier CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  17. Physical Layout - Carrier Presenter: Greg Mosier CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  18. Physical Layout - Lander 82mm 21mm 103mm 64.5mm 15 mm Presenter: Greg Mosier CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  19. Physical Layout - Lander Presenter: Greg Mosier CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  20. Launch Vehicle Compatibility • CanSat will be loaded into rocket payload compartment with first parachute stored towards rear of rocket • Payload dimensions • Height = 152 mm • Diameter = 127 mm • CanSat dimensions • Height = 152 mm • Diameter = 124 mm • CanSat compatibility will be checked before launch date by model rocket payload compartment Diameter = 124mm .5 mm each Height = 152 mm Presenter: Greg Mosier CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team) )

  21. Sensor Subsystem Design Blake Lohn-Whilie CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  22. Sensor Subsystem Overview Temperature & Altitude Sensor BMP 180 GPS Sensor LocoSys LS20031 Force Impact Sensor ADXL 345 Presenter: Blake Lohn-Wilie CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  23. Sensor Subsystem Requirements Presenter: Blake Lohn-Wiley CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  24. Sensor Changes Since PDR • No changes since PDR Presenter: Blake Lohn-Wiley CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  25. Carrier GPS Summary GPS module chosen --- LS20031 • Accuracy around ±3m • Will be accessing the GPS using a software serial library on the Arduino. • Must use PMTK commands to limit messages to only GGA. • Lower the baud rate, and refresh time so Arduino is not overloaded with data. • Will be using NMEA GGA data messages. Ex. • $GPGGA,053740.000,32.2564,N,-98.21113,E,1,8,1.8,410.6,M,21.2,M,*64 CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  26. Carrier & Lander Altitude & Temperature Sensory Summary • Pressure sensor chosen --- BMP180 • Accurate to ±0.02 hPa and ±0.5ºC • Using the I^2C interface requires only 4 pins for a connection. Vcc, Gnd, SDA, and SCL. • Requires calibration on startup, the data is stored in it’s registers. • Calculates altitude using this equation: • Where p is the measured pressure a and p knot is the sea level pressure. • Range of 0-1000 m is equal to delta p of about 100 hPa. CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  27. Lander Impact Force Sensor Summary • Summary of air temperature sensor selection and characteristics • At the ±16 g range, accuracy of ±0.03125 g, with resolution of 0.015625 g. • Using the I^2C connection, using pins: SDA, SCL, CS tied to VCC, and SD0 tied to GND. • Data reading in the format: (x,y,z) • Will begin sampling data at an altitude of 30 m, and will turn off when altitude is constant for 5 seconds. CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  28. Descent Control Design Greg Mosier CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  29. Descent Control Overview • 450-670m – Cansat deploys from rocket • – Dynastar 24” parachute ↓ 10±1 m/s • 200m – Cansat slows descent rate • – Dynastar 36” parachute deployment using servo and fiberglass cover ↓ 5±1 m/s • 91m – Carrier & Lander separate • – Lander deploys Dynastar 24” parachute using a static line connected to Carrier Carrier Lander ↓ ↓ <5 m/s • 0m – Recover Carrier & Lander Presenter: Greg Mosier CanSat 2012 PDR: Team 1719 (Tarleton Aeronautical Team)

  30. Descent Control Changes Since PDR • Deployment mechanism for parachutes finalized • Will use servo to release fiberglass disc cover for 2nd parachute • Will use static line to release fiberglass disc cover for final parachute • Carrier and Lander separation mechanism altered to prevent Lander from rotating Presenter: Greg Mosier CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  31. Descent Control Requirements Presenter: Blake Lohn-Wiley CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  32. Carrier Descent Control Hardware Summary • Passive Components • 1st parachute (fluorescent orange) • Released at rocket separation • 24” • 2nd parachute (fluorescent orange) • Release triggered by height sensing by microcontroller • Servo releases fiberglass cover that flops open to release parachute • 36” • Active Components • Altimeter • ±0.02 hPa • Stored in a 3 element array • Servo • 0.10 sec/60º @ 4.8V CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  33. Lander Descent Control Hardware Summary • Parachute deployment is triggered by separation of Carrier and Lander pulling a static line which releases parachute • Passive Components • 3rd parachute (fluorescent orange) • Fiberglass cover holds parachute in place until static line pulls it open upon Carrier-Lander separation • 24” Fiberglass cover Static Line Parachute LANDER CARRIER CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  34. Descent Rate Estimates • d is the diameter of the parachute Presenter: Blake Lohn-Wiley CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  35. Descent Rate Estimates Assumptions The changes in air density will not significantly affect descent rate. Parachutes will be modified for appropriate diameters as indicated above. Presenter: Blake Lohn Wiley CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  36. Mechanical Subsystem Design Greg Mosier Ethan Moore CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  37. Mechanical Subsystem Overview • Carrier • Was prototyped to specification with a perforated steel body and silicon bulk heads that also carried the electronics • Compartment size stayed the same as the original design • Lander • Was prototyped using aluminum instead of carbon fiber • Both worked in static testing Presenter: Ethan Moore CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  38. Mechanical Subsystem Changes Since PDR • Dimensions of several compartments changed • Two rods added to carrier frame to prevent rotation of lander during separation • Lander frame discs have notches added as guides for the rods Presenter: Ethan Moore CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  39. Mechanical System Requirements Presenter: Cletus Fuhrmann CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  40. Mechanical Systems Requirements Presenter: Cletus Fuhrmann CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  41. Lander Egg Protection Overview • Egg will be placed sideways in a polyurethane mold that will fit in a cylindrical shape of 82 cm x 64.5 cm • Duct tape will be used to hold the two sections of the mold together Presenter: Tyler Case CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  42. Lander Egg Protection Overview • Testing indicated that our egg protection is more than significant to protect our egg from the forces of acceleration upon takeoff and the impact force upon hitting the ground • Our data is as follows: Presenter: Tyler Case CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  43. Mechanical Layout of Components Lander Carrier Dimensions: 124mm (dia) x 152mm (height) Presenter: Ethan Moore CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  44. Material Selections • Frame rods • Carbon fiber • High strength • Low weight • Frame discs • Carbon fiber • High strength • Low weight • Separation Screw & Nut • Plastic • Low weight • Fewer number of turns • Static Line • 60 lb Braided Dacron • Exceeds strength needed to open cover • Parachute Covers • Fiberglass • Lightweight • Easily modified • Outer Shell • Plastic • Allows for easy access to CanSat while still enclosing structure Presenter: Ethan Moore CanSat 2012 CDR: Team1719 (Tarleton Aeronautical Team)

  45. Carrier – Lander Interface GM11a Metal Geared Motor Deployment Trigger & Mechanism www.solarbotics.com Static line connecting carrier to cover of lander parachute. Opens cover upon separation. Notches in side of lander top disc will keep it from rotating while screw is turning. CARRIER Presenter: Ethan Moore CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  46. Structure and Survivability • Lander and Carrier successfully static tested • 1st prototype was identical to PDR model but used 26 gauge aluminum and steel rods • Failed the strength test • 2nd prototype: lander had all aluminum cylindrical shell • Both lander and carrier used silicon board for bulk heads and electronics • Both used PVC pipe for an anti-torsion collar to prevent rotation during separation Presenter: Ethan Moore CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  47. Carrier Mass Budget Carrier Total: 269.1 g Presenter: Greg Mosier CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  48. Lander Mass Budget Lander Total: 183.6 g CanSat Total: 453 g Presenter: Greg Mosier CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  49. Communication and Data Handling Subsystem Design Blake Lohn-Wiley Billy Fournie CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

  50. CDH Overview • Lander • Data from the accelerometer, barometer is received by the Arduino Pro mini and stored on external Micro SD card. • Retrieved later by reading from the Arduino using an FTDI cable • Carrier • Data from the GPS, barometer, and temperature sensor is received by the Arduino Pro Mini and transmitted by the Xbee Pro S2B transceiver to the Ground Control Station (GCS) for fault tolerance data will also be stored on an external Micro SD Card Presenter: Billy Fournie CanSat 2012 CDR: Team 1719 (Tarleton Aeronautical Team)

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