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LogDAT Flight Data Logging Sponsored by L3-Communications

LogDAT Flight Data Logging Sponsored by L3-Communications. Group 9. Group 9 Members. Winston James EE Brian Lichtman CpE Shaun Mosley CpE Tony Torres CpE. Motivation.

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LogDAT Flight Data Logging Sponsored by L3-Communications

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  1. LogDATFlight Data LoggingSponsored by L3-Communications Group 9

  2. Group 9 Members Winston James EE Brian LichtmanCpE Shaun Mosley CpE Tony Torres CpE

  3. Motivation • L3-Communications uses a software set (DATCOM) to calculate expected flight characteristics of large fixed-wing aircrafts • L3 has asked for a solution to verify the accuracy of their software set when used on small aerial vehicles

  4. Project Objective • Record vital parameters from test flights of a model airplane • Portable and easily adapted to other aircrafts • Provide easy way to obtain recorded data and compare with L3’s software set

  5. Specifications • Ability to record data at speeds of at least 60 Hz • Aircraft should be able to fly for at least 20 minutes while recording data • Test vehicle must have a wingspan larger than 3 feet • Must not have more than ½lb weight offset to one side • Cost must be under $1500.00

  6. Requirements • Lift Coefficient due to: • Basic geometry (CLα) • Flap deflection (CLδf) • Elevator Deflection (CLδe) • Pitch Rate derivative (CLq) • Angle of Attack Rate derivative (CLαdot) • Drag Coefficient due to: • Basic geometry (CdD) • Flap deflection (Cδf) • Elevator deflection (Cdδe) • Side Force Coefficient due to: • Sideslip (Cnâ) • Roll Rate derivative (Cnp) • Yaw Rate derivative (Cnr) • Pitching Moment Coefficient due to: • Basic Geometry (Cm) • Flap Deflection (Cmδf) • Elevator Deflection (Cmδe) • Pitch Rate derivative (Cmq) • Angle of Attack Rate derivative (Cmαdot) • Rolling Moment Coefficient due to: • Aileron Deflection (Clδa) • Sideslip (Clâ) • Roll Rate derivative (Clp) • Yaw Rate derivative (Clr) • Yawing Moment Coefficient • Aileron Deflection (Cyδa) • Sideslip (Cyâ) • Roll Rate derivative (Cyp) • Yaw Rate derivative (Cyr) • Misc • Horizontal Tail Downwash Angle (ε) • Derivative of Downwash Angle (δε/δα) • Elevator-surface hinge-moment derivative with respect to alpha (Chα) • Elevator-surface hinge-moment derivative due to elevator deflection (Chδ) • Normal force coefficient (body axis) (CN) • Axial force coefficient (body axis) (CA)

  7. External Components

  8. Model Airplane • MQ9 Reaper – used by USAF, US Navy, CIA • Picked to meet L3’s request • Dimensions: 8.3 ft wingspan x 3.6 ft length • Price: $100.36

  9. Autopilot • Autopilot is installed on an aircraft to allow for flight stabilization, auto takeoff, landing and fixed flight patterns • Basic units are GPS, accelerometer, gyroscope, servos, telemetry • Multiple types and brands are manufactured

  10. Autopilot Selection • ArduPilot Mega • Open-source firmware • Relatively cheap • Great community support • Free telemetry software • Price: $415.00 • Before testing in actual flight, we will test the ArduPilot in the FlightGear simulator

  11. ArduPilot Software

  12. Hardware and Firmware Integration

  13. Hardware Design • DYNAMIC PRESSURE “q” = 1/2ρV2 • Dependent on True Airspeed (TAS) • Dependent on air density (rho) • Dependent on AOA • FORCE COEFFICIENTS • TORQUES COEFFICIENTS • TAS • PITOT-TUBE PRINCIPLE • AOA & AOS • BOOM

  14. HARDWARE BLOCK DIAGRAM

  15. FORCE SENSORS • FORCE SENSORS • MFGR: INTERLINK ELECTRONICS • PN: FSR402 • THIN MEMBRANE TECHNOLOGY • SMALL = 18.28mm DIAMETER • LOW POWER = 2.5mW • CHEAPEST SOLUTION • FORCE RANGE: 0.352 oz. to 22lb! ALTERNATIVE ZEBRA SYSTEM

  16. FORCE SENSOR TERMINALS

  17. Inertial Measurement Unit • Accelerometer • MFGR: ST MICROELECTRONICS • PN: AIS326DQTR • MET SPEC • EXCELLENT BW • SENSITIVITY • 3-AXIS • SPI • LOW POWER= 2.64mW • HIGH SENSITIVITY: 1024LSB/G 0.977mm/s2 PER LSb • Gyroscope • ST MICROELECTRONICS • P/N: L3G4200DTR • MET SPEED REQUIREMENT: • 1MHz > 60Hz • 3-AXIS • SPI • LOW POWER: 18.91 mW • HIGH SENSITIVITY: 8.75 dps/lsb • FREE SAMPLES!

  18. Inertial Measurement Unit

  19. Boom Sensors • JUSTIFICATION • P/N: MPXV7002DP • RANGE: ±2 kPa • REQ: +1.475 kPa dynamic pressure = 50m/s velocity at sea level • ACCURACY: 2mV/Pa • SAMPLED • ANALOG SENSOR • USED IN OTHER DRONE PROJECTS • LOW POWER = 50mW • JUSTIFICATION • MFGR: MURATA • P/N:SV01A103AEA01B00 • LOW POWER: 5mW • LONG LIFE: 1M CYCLES • WIDE RANGE: 0-333º • VERY THIN • FREE! Q= [Vout ±6.25%(Vs-2.5v)-0.5v]/ [0.2Vs]

  20. BOOM SENSORS

  21. Hardware: Humidity Sensor • HUMIDITY SENSOR • MFGR: HONEYWELL • P/N: HIH-5031-001 • ANALOG SENSOR • LOW POWER= 1.65mW • SMALL SIZE • PURPOSE: AIR DENSITY • FREE! • BAROMETRIC PRESSURE SENSOR • MFGR = BOSCH • P/N: BMP085 • ANALOG SENSOR • LOW POWER = 0.03mW • ALTITUDE RANGE: 0 to 29,528ft (9000m) • ACCURACY: ±100Pa ±27ft = ±8.22m • PURPOSE: AIR DENSITY • TEMPERATURE SENSOR • MFGR: ANALOG DEVICES • P/N: AD7814ARMZ • SPI INTERFACE • LOW POWER =1.32mW • PURPOSE: AIR DENSITY • FREE!

  22. ALTITUDE SENSORY

  23. POWER SUPPLY

  24. MCU

  25. Microcontroller Unit (MCU) Selection • MCU Chosen • Microchip’s dsPIC33EP512MU810 • Aspects reviewed were: • Does it meet our I/O requirements? • What programming and debugging resources are available? • What kind of support is available for the MCU? • Can we get free samples of the products?

  26. I/O Requirements • I/O Requirements: • 34 Analog I/O • 30x Force Sensors • 2x Angle Sensors • 1x Differential Pressure Sensor • 1x Humidity Sensor • 4 SPI (Serial Peripheral Interface) Digital I/O • Accelerometer • Gyroscope • Temperature Sensor • SD Card Interface • 1 I2C (Inter-Integrated Circuit) Digital I/O • Barometric Pressure Sensor FSR 402 Force Sensor

  27. MCU Programming and Debugging Environment • Free academic version of their C compiler and debugger with graphical IDE • Includes code optimization not available in the normal free version. • Fully functional with all libraries and source code of commercial version • Memory Disk Drive File System Library • Multi-level code optimization

  28. Available Support • There is abundant documentation for the use of dsPic33s • Large collection of online training videos provided by Microchip • Online 24hr support system for technical support along with a large support forum community • Large collection of example code

  29. Sample Availability • 3 dsPIC33EP512MU810 MCUs • 2 Free Samples of the ICD3 • 2 Free Samples of the Explorer 16 development board • 2 Free Samples of dsPIC33EP512MU810 daughter boards for use with the development boards

  30. MCU Software Design • Software will be split into two separate sections: • Data acquisition • Data storage

  31. Data Acquisition • The MCU firmware will be designed to poll sensors at a minimum rate of 60hz. • Grab data from sensor • The analog sensors will be read 4 at a time • Digital sensors will be read sequentially • Convert each sensor value to an IEEE floating point number • Send data to data storage buffer • Repeat until all 38 sensors have been read

  32. Data Storage • Using the file system library from Microchip, an SPI interface will be used to communicate with an SD card. • A data storage buffer will wait until 38 values are received • Once this occurs, the buffer will be flushed to the SD card as raw binary

  33. PCB LAYOUT

  34. Power Consumption

  35. Software Design

  36. Software Overview • Graphical User Interface (GUI) • The GUI is a simple interface to make the file selection process much simpler than using the command prompt. • Program execution • The program will execute after the "Create" button is clicked. From there it will perform all the functions that need to take place to translate the input data to readable data for the user.

  37. Data Structures • I choose to use a linked list for memory concerns • Linked List • Can only access the next value • Is the exact length of the data and only adds one at a time • With only one node being made at a time a linked list insures the minimum amount of memory being taken.

  38. GUI • Source text box is to specify the source file location • Destination text box is to specify the name and destination of the file to be created • The create button will run the computations to do the conversion from a binary to a csv file

  39. Software Design • Required measurements • Parsed Data • Forces • q • Angle of Attack • Derivatives • Moments • Calculated measurements • Force and moment Coefficients • Coefficients due to different parameter on the plane • CL due to AOA

  40. Software Design • Derivatives • The derivatives are found by finding the slope between the two points on ether side • Because we need to find second derivatives that makes the first and last 2 data points not accurate.

  41. Software Formulas Rz= Ry = Rx = F=

  42. Formulas for Coefficients Forces True Air Speed Torques is experimentally determined Torque Coefficient Definition A is reference area, l is application length Force Coefficient Definition A is reference area Air Density

  43. Administrative

  44. Budget

  45. Work Distribution

  46. Questions

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