Difference between revisions of "F13: Quadcopter"

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=== Grading Criteria ===
 
<font color="green">
 
*  How well is Software & Hardware Design described?
 
*  How well can this report be used to reproduce this project?
 
*  Code Quality
 
*  Overall Report Quality:
 
**  Software Block Diagrams
 
**  Hardware Block Diagrams
 
**:  Schematic Quality
 
**  Quality of technical challenges and solutions adopted.
 
</font>
 
 
 
== Quadcopter ==
 
== Quadcopter ==
  
 
== Abstract ==
 
== Abstract ==
The Quadcopter is a four rotor remote controlled aircraft.  It takes in remote commands from a hobbyest remote control, and achieves steady flight by utilizing a 3 axis accelerometer and a 3 axis gyroscope to determine the current attitude.  It then takes the values from the remote control, and current attitude, and determines the needed changes to the motors to achieve the desired flight.
+
The Quadcopter project will build a four rotor remote controlled aircraft.  It takes in remote commands from a hobbyist remote control, and achieves steady flight by utilizing a 3 axis accelerometer and a 3 axis gyroscope to determine the current attitude.  It then takes the values from the remote control, and current attitude from the sensors, and determines the needed changes to the motors to achieve the desired flight.
  
 
== Objectives & Introduction ==
 
== Objectives & Introduction ==
  
 
=== Objectives ===
 
=== Objectives ===
The objective of this project is to build a remote controlled quadcopter that is capable stable flight.  We will control the quadcopter via a Spektrum DX5E hobbyist controller.  We will be creating an Inertial Measurement Unit(IMU) using a 3 axis accelerometer and a 3 axis gyroscope.  The IMU will communicate with the SJ One Board via I2C.  We will be implementing a complementary filter in software to estimate the quadcopter attitude, and will then have a PID control loop in software to generate outputs to the motors.
+
The objective of this project is to build a remote controlled quadcopter that is capable stable flight.  We will control the quadcopter via a Spektrum DX5E hobbyist controller.  We will be creating an Inertial Measurement Unit (IMU) using a 3 axis accelerometer and a 3 axis gyroscope.  The IMU will communicate with the SJ One Board via I2C.  We will be implementing a complementary filter in software to estimate the quadcopter attitude, and will then have a PID control loop in software to add to the throttle inputs to generate outputs to the motors.
  
 
===Introduction===
 
===Introduction===
Line 225: Line 213:
  
 
==== PWM In From Remote Ctrl====
 
==== PWM In From Remote Ctrl====
 +
 +
The DX5e on board receiver outputs 5 channels of PWM input running at a 50Hz refresh rate.  The voltage levels of the PWM in are 5V.  The SJ One board is not 5V tolerant, and there are not 5 channels of input capture pins available.  In order to get the values requested by the remote control, one needs to translate the voltage levels to 3.3V, and to try to combine the signals to a single input.  After researching on line, an example design was found that took the 5 channels of input and or'ed all of them together to get a single pulse train out.  The example design also suggested a 5V tolerant part that would output 3.3V.  After investigating the hardware that is used on the Quadcopter project, it was decided that this could work.  A logic analyzer capture of the receiver output is shown below, as well as the output of the or gate.  As is shown, the pulse train does not overlap, so the or gate is sufficient to handle both the level shift to 3.3V and the combining of signals.
  
 
{|
 
{|
 
[[File:Cmpe240 f13 quadcopter pwm input.png]]
 
[[File:Cmpe240 f13 quadcopter pwm input.png]]
 
|}
 
|}
 +
 +
Below is a logical representation of how the or gate is wired.
  
 
{|
 
{|
Line 235: Line 227:
  
 
==== PWM Out ====
 
==== PWM Out ====
 +
 +
Quadcopters by nature need fast refresh rate on current position, and need low latency thru the control loop to actual commands to the motors.  To help keep the latency low, the output PWM was ran at a faster than normal rate.  The output PWM is running at 400hz instead of the normal 50hz refresh rate.  The minimum pulse width is approx 1ms and the maximum pulse width is about 2 ms.
  
 
==== I2C Sensor Bus ====
 
==== I2C Sensor Bus ====
  
=== Software Design ===
+
The sensors all run off of a single I2C bus.  The accelerometers base address is 0xE5, the magnetometer base address is 0x48, and the gyroscope base address is 0xD3.  The I2C bus clock rate is 400kHz to help minimize the control loop latency.
Show your software designFor example, if you are designing an MP3 Player, show the tasks that you are using, and what they are doing at a high levelDo not show the details of the code.  For example, do not show exact code, but you may show psuedocode and fragments of code.  Keep in mind that you are showing DESIGN of your software, not the inner workings of it.
+
 
 +
=== Hardware Implementation ===
 +
 
 +
Here is the board layout.
 +
 
 +
[[File:Cmpe240 f13 quadcopter board layout.png ]]
 +
 
 +
Here is a picture of the fully assembled quadcopter
 +
 
 +
[[File:Cmpe240 f13 quadcopter assembled.jpg ]]
 +
 
 +
=== Software Design & Implementation ===
 +
The top level software block diagram is shown belowThe quadcopter project utilized free RTOS to help with schedulingThe following sections will go into the details on each block shown.
 +
 
  
 
[[File:Cmpe240 f13 quadcopter sw block diagram.png]]
 
[[File:Cmpe240 f13 quadcopter sw block diagram.png]]
  
=== Implementation ===
+
==== RX Capture ISR ====
This section includes implementation, but again, not the details, just the high level.  For example, you can list the steps it takes to communicate over a sensor, or the steps needed to write a page of memory onto SPI FlashYou can include sub-sections for each of your component implementation.
+
 
 +
The PWM input is connected to Capture pin CAP1.1 on gpio P1.19.  The CAP input is setup to trigger an interrupt on each rising edge and each falling edge of the input PWM pulse train.  The TIMER1_IRQHandler is setup to give a semaphore to get_remote_ctrl_values task, and then quickly clears the current interrupt.  The get_remote_ctrl_values task is shown in the block diagram below.
 +
 
 +
[[File:Cmpe240 f13 quadcopter isr flowcharg.png]]
 +
 
 +
==== Remote Command Translator ====
 +
 
 +
The remote command translator task is a straight forward look up table.  The throttle value is passed unchanged to the PWM output.  All of the other inputs (roll, pitch, and yaw) are decoded and passed to the PID task as the new set point for the control loop.  As a design decision, there is a hard limit of 30 degrees for each input.  If the remote ctrl sets roll to be max value, the angle offset that is sent to the PID is limited to 30 degrees.
 +
 
 +
==== I2C Driver ====
 +
 
 +
The I2C Driver task calls low level I2C functions to read and write registers on the I2C slave devices.  The I2C Driver is tasked with initialization of all I2C slave devices.  It also handles burst reading of sensor registers.  This driver task reads the sensor values every 5ms.  All delta t values used in algorithms down stream use the delta t values measured this task.  It is measured with internal timer 0. 
 +
 
 +
This task is the driver for all tasks except the PWM input taskAll downstream tasks are waiting for the output queue from this task to be written, and will then process the data.
 +
 
 +
This driver currently reads without checking to see if data is available.  A possible optimization that would be to utilize the data ready interrupt from the gyro and accelerometer.  Another optimization would be to increase the burst value from 2 8bit registers to 6 8bit registers.
 +
 
 +
==== Data Smoothing ====
 +
 
 +
Due to vibrational noise, an additional lowpass filter was added before the sensor fusion and after the I2C input.  The filter acts on the raw sensor data after it has been scaled correctly.  The code for the filter is quite simple:
 +
 
 +
    smoothed_value = smoothed_value + alpha * (input - smoothed_value);
 +
 
 +
There is very little latency thru the filter, and it really seemed to help with data noise.
 +
 
 +
==== Sensor Fusion ====
 +
 
 +
Sensor fusion is the act of taking reading from two or more sensors, and combining them in a meaningfull way.  Sensor fusion is used in this case because we are taking data from a noisy accelerometer, and from a gyroscope that shows accumulated error on readings over a long time (more than a sec).  We combine them such that we are taking the stable instantaneous values from the gyro and combining them with the long term stable values from the accelerometer.  We manage this via a Complementary Filter.  A complementary filter takes the angle values from both the accelerometer and the gyroscope and low pass filters the accelerometer,and high pass filters the integrated angular velocity from the gyroscope.  See the figure below.
 +
 
 +
[[File:Cmpe240 f13 quadcopter complementary filter 3.jpg]]
 +
 
 +
This function can be implemented in a couple of lines of code for each axis.
 +
 
 +
    // Complementary Filter Implementation
 +
    filtered_angle = (A)*(filtered_angle+gyro_rate*dt);
 +
    filtered_angle += (1-A)*acc_angle;
 +
 
 +
There is a complementary filter for both the X and the Y axis.  It was decided as the project was winding down to not implement yaw control due to schedule constraints.  When there is time, there will be a complementary filter taking in gyro values and values from magnetometer to measure yaw and feed that into an additional PID stage to control the yaw.
 +
 
 +
==== PID ====
 +
 
 +
A PID controller is a flexible control loop often used when the impulse response of the system under control is unknown.  A generic block diagram for a PID is shown below.  PID is an acronym for Proportional, Integral, and Derivative control loop. 
 +
 
 +
[[File:Cmpe240 f13 quadcopter pid 2.jpg]]
 +
 
 +
===== Proportional =====
 +
 
 +
The proportional leg of the control loop is simply the setpoint (from the rx input) and the current state of the quadcopter from the sensor fusion section.  The equation is given by Kp*e(t) where Kp is the gain, and e(t) is the error term at time t. 
 +
 
 +
The code is very simple:
 +
    x_proportional_error = setpoint.thetaX - angle.thetaX;
 +
 
 +
If there were no inertia, or no friction, then the P would be all that was needed.  The exact amount of error is subtracted from the controls, and would fix the error in an ideal world.  Since the real world has both of those items, a control loop needs one or both of the other types of control.
 +
 
 +
===== Integral =====
 +
 
 +
The integral leg of the control loop is a running sum of the current proportional error multiplied by delta t, which is the time since the last sample. 
 +
 
 +
The code looks like: 
 +
    x_integral_error += x_proportional_error*dt;
 +
 
 +
The integral portion of the control loop is there to account for environmental influences over the quadcopter.  An example would be an unbalanced quadcopter such that one corner is heavier than the others.  The control loop without an I would see that the quadcopter is not level and make the changes it is programed to do, but it still stays unbalances.  The integral term of the loop will continually add error to the motors until it increases such that it levels the quadcopter.
 +
 
 +
===== Derivative =====
 +
 
 +
The derivative leg of the control loop is the change in error from the last sample to the current sample divided by the time interval. 
 +
 
 +
This code looks like: 
 +
    x_derivative_error = (x_proportional_error - x_prev_error)/dt;
 +
 
 +
The derivative portion of the control loop predicts future errors based on the rate of change of past errors.  It can speed up error correction or can put the brakes on as well helping stop over correction if tuned correctly.
 +
 
 +
===== PID Loop Implementation =====
 +
The entire control loop for a single axis looks like this:
 +
 
 +
            x_proportional_error = setpoint.thetaX - angle.thetaX;
 +
            x_integral_error += x_proportional_error*dt;
 +
            x_derivative_error = (x_proportional_error - x_prev_error)/dt;
 +
            x_error = x_proportional_error*proportional_gain + x_integral_error*integral_gain + x_derivative_error*derivative_gain;
 +
            x_prev_error = x_proportional_error;
 +
 
 +
==== PWM Out ====
 +
 
 +
The error values out of the PID section are applied directly to the PWM pulse width mathSee the code below:
 +
 
 +
            motor_front_sum = throttle_in +  error_in.errorX;
 +
            motor_back_sum  = throttle_in + -error_in.errorX;
 +
            motor_left_sum  = throttle_in +  error_in.errorY;
 +
            motor_right_sum = throttle_in + -error_in.errorY;
 +
 
 +
Note, what was added to one half of front/back is subtracted from the other half.  Same holds true for the left/right pair.  This is done to keep the power coming out of props the same, and to keep the elevation control only come from the throttle.
 +
 
 +
The design also has limitations of pulse widths min and max to make sure not to disable the motors.  If the throttle in + error is larger than the max value for pulse width, it clips at the max value.  The same is true if throttle in + error is less than min pulse width.  It holds the minimum value.
  
 
== Testing & Technical Challenges ==
 
== Testing & Technical Challenges ==
Describe the challenges of your project.  What advise would you give yourself or someone else if your project can be started from scratch again?
 
Make a smooth transition to testing section and described what it took to test your project.
 
  
Include sub-sections that list out a problem and solution, such as:
+
=== Testing ===
 +
 
 +
The first testing attempted was I2C read/write testing.  Once the sensors were wired up, a quick while loop with a delay was implemented to show that the sensors could be read reliably.
 +
 
 +
The next portion of testing was the PWM input testing.  This took a while to get right due to ISR issues.  Once the ISR was working, it was possible to printf the pulsewidth values calculated and compare to what the input controls were set to.
 +
 
 +
To test the ability to run the motors correctly, a test task was created that would drive the motors at 25%, 50%, 75%, and 100% depending upon which button on the SJ One board was pressed.
 +
 
 +
The angle calculation for X, Y, and Z was tested by having the data_smoothing task print to the console 1 time out of every 100 calculations.  The test consisted of holding the quadcopter in my hand and rotating it around each axis and watch the value of angle match the correct sign, as well as test if the magnitude was in the correct ballpark.
 +
 
 +
Once the angle calculation seemed correct, the feedback loop was closed by adding in the PID with a guess of the values.  To do this testing, we attached the quadcopter between two saw horses so that it could only rotate in a single plane.  The majority of testing was of this type.  PID gain values were tested until the X axis was quasi stable.  We then switched to the Y axis and set the PID gains to the same values.  After fixing some sign errors, and other math errors, we were able to make the Y axis mostly stable as well.  A video of some 2D testing can be found at the link below.
 +
 
 +
* [http://youtu.be/6wISzeOmDDU Quadcopter 2D Testing]
 +
 
 +
The final bit of testing attempted was flight testing.  This testing showed that we need to make sure to implement the yaw control.  Once the quadcopter lifted off, it started to yaw, which made it hard to fly correctly.  Video of flight testing can be found in the section marked Project Video.
 +
 
 +
=== Technical Challenges ===
 +
 
 +
One of the largest technical challenges found was getting the PWM input ISR to not crash the processor, and to operate correctly.  After long hours of debugging it was found that there was a low level driver that was using the same timer interrupt.  Once this was solved, the development went a lot smoother, and we were able to reliably receive the commands from the remote control, and have the flight control software act upon these commands.
 +
 
 +
The largest technical challenge found is still being investigated.  There seem to be some issues with the data coming out of the sensors.  In an attempt to clean this up, there was some additional data smoothing added to both the gyro output and the accel output.  This did help the stability of the flight correction, but there are still issues.
  
=== Wifi Connection Issues ===
+
Another technical challenge found was the process of tuning the PID gain valuesThis will continue to be a work in progress until the sensor reads are clean and accurate.
Many wifi connection issues were encounteredTo solve this problem, a dedicated task was created to re-connect to wifi if the connection was ever lost.
 
  
 
== Conclusion ==
 
== Conclusion ==
Conclude your project hereYou can recap your testing and problems.  You should address the "so what" part here to indicate what you ultimately learnt from this project. How has this project increased your knowledge?
+
The quadcopter was a very challenging project.  While I was not able to achieve the stable flight I had been hoping for, the quadcopter did fly.  The project was a great learning experience.  I learned a lot about the LPC1758.  I learned a lot about interrupt service routines.  I learned a lot about IMU's and flight control software.  I learned a lot about how to implement and tune a PID control loop.
 +
 
 +
The next step for the quadcopter project will be to implement the yaw control and yaw portion of the PID.  I also want to continue attempting to clean up the data from the sensors.  There may be some issues with noise and or discontinuities on the I2C reads.  This will be facilitated by getting data logging to the mico SD card working.  I will then be able to characterize any data problems off line via matlab, and target filtering and or changes to sensor reads to fix the issuesAnother possible upgrade on the I2C reads will be to enable the data ready interrupts from the sensors, and only read them when I know data is ready.
  
 
=== Project Video ===
 
=== Project Video ===
Upload a video of your project and post the link here.
+
* [http://youtu.be/66KNhXO450A Quadcopter Best Flight]
 +
* [http://youtu.be/oM4p4W0TSjM Quadcopter Crash]
  
 
=== Project Source Code ===
 
=== Project Source Code ===
Send me your zipped source code and I will upload this to SourceForge and link it for you.
+
*  [https://sourceforge.net/projects/sjsu/files/CmpE240_LM_F2013/ Sourceforge link for source code]
  
 
== References ==
 
== References ==
 
=== Acknowledgement ===
 
=== Acknowledgement ===
Any acknowledgement that you may wish to provide can be included here.
+
I would like to acknowledge and thank my patient wife Sandie for putting up with all the time spent on the project.
 +
 
 +
I would like to acknowledge and thank Brandon for loaning me his logic analyzer and being there to field my software questions.
 +
 
 +
I would like to acknowledge and thank Rob for lending me his RC expertise, and answering all of my silly questions.
 +
 
 +
I would like to acknowledge and thank Preet for the help with the ISR issues encountered and for teaching a very interesting class.
  
 
=== References Used ===
 
=== References Used ===
List any references used in project.
 
  
=== Appendix ===
+
 
You can list the references you used.
+
[http://www.nxp.com/documents/data_sheet/LPC1769_68_67_66_65_64_63.pdf LPC1758 Datasheet] <br/>
 +
[http://www.nxp.com/documents/user_manual/UM10360.pdf LPC1758 User Manual] <br/>
 +
[http://dlnmh9ip6v2uc.cloudfront.net/datasheets/Sensors/Gyros/3-Axis/CD00265057.pdf Gyro Datasheet]<br/>
 +
[https://www.sparkfun.com/datasheets/Sensors/Accelerometer/ADXL345.pdf Accel Datasheet]<br\>
 +
[http://dlnmh9ip6v2uc.cloudfront.net/datasheets/Sensors/Magneto/HMC5883L-FDS.pdf Magno Datasheet]<br\>
 +
[http://dlnmh9ip6v2uc.cloudfront.net/datasheets/Wireless/Bluetooth/RN42XV.pdf Bluetooth Datasheet] <br\>
 +
http://nicisdigital.wordpress.com/category/quadcopter/ <br/>
 +
http://web.mit.edu/scolton/www/filter.pdf <br/>
 +
http://theboredengineers.com/2012/05/the-quadcopter-basics/ <br/>
 +
http://theboredengineers.com/2012/05/the-quadcopter-part-1-genesis-of-the-project/ <br/>
 +
http://www.instructables.com/id/RC-Quadrotor-Helicopter/?ALLSTEPS <br/>
 +
http://blog.oscarliang.net/quadcopter-pid-explained-tuning/ <br/>

Latest revision as of 06:02, 8 December 2013

Quadcopter

Abstract

The Quadcopter project will build a four rotor remote controlled aircraft. It takes in remote commands from a hobbyist remote control, and achieves steady flight by utilizing a 3 axis accelerometer and a 3 axis gyroscope to determine the current attitude. It then takes the values from the remote control, and current attitude from the sensors, and determines the needed changes to the motors to achieve the desired flight.

Objectives & Introduction

Objectives

The objective of this project is to build a remote controlled quadcopter that is capable stable flight. We will control the quadcopter via a Spektrum DX5E hobbyist controller. We will be creating an Inertial Measurement Unit (IMU) using a 3 axis accelerometer and a 3 axis gyroscope. The IMU will communicate with the SJ One Board via I2C. We will be implementing a complementary filter in software to estimate the quadcopter attitude, and will then have a PID control loop in software to add to the throttle inputs to generate outputs to the motors.

Introduction

Before we get started, we must first define a few aircraft terms, and describe how they are manifested on the quadcopter.

Aircraft Motion Primer

The motion of an aircraft can be described by three types of motion: Roll, Pitch and Yaw.

Figure 1 - Roll Pitch and Yaw

Roll is the rotation of the aircraft around the x axis and makes the aircraft turn left and right. Pitch is rotation about the Y axis, and in an airplane causes the aircraft to climb and dive. On a quadcopter, the pitch controls going forward and backward. Yaw is defined by rotation about the Z axis.

Cmpe240 f13 quadcopter motion.png

On a quadcopter, two of the rotors move in a counter-clockwise motion, and two move in a clockwise motion. The opposite rotation will allow for flight without uncontrollable yaw due to the angular momentum of the motor/propeller assemblies canceling each other out. Vertical motion is controlled by the motor speed for all rotors. Moving forward/backward is caused by pitching forward or pitching backward. To pitch forward, speed up the rear prop, and slow down the front prop. To pitch backward speed up the front rotor, and slow down the back rotor. To roll left, speed up the right rotor, while slowing down the left rotor. To roll right, speed up the left rotor, while slowing down the right rotor. To Yaw right, speed up both the left and right rotors, while slowing down the front and back rotors. To yaw left, speed up the front and back rotors, and slow down the left and right rotors.

Team Members & Responsibilities

  • Craig Farless
    • Airframe Design
    • Sensor Design
    • Remote Control Interface Design
    • Flight Controller Software Design

Schedule

Task Projected Completion Date Actual Completion Date Status Notes
Buy Parts 1-Oct 1-Oct Complete
Build frame 8-Oct 8-Oct Complete
Install Sensors 15-Oct 8-Oct Complete
Code I2C i/f to sensors 15-Oct 15-Oct Complete
Code Filters 22-Oct 15-Oct Complete More filtering may be needed
Code accel/gyro conversion to angle 22-Oct 22-Oct Complete
Integrate Power System 22-Oct 22-Oct Complete
Code PWM input 29-Oct 15-Nov Complete Much more difficult than planned
Code cmd translator 29-Oct 20-Nov Complete
Code PID 5-Nov 17-Nov Complete Will continue tuning PID
Code PWM Encode Driver 12-Nov 16-Nov Complete
Integrate Processor with Aircraft 12-Nov 1-Nov Complete
Tether Testing 2D stabilization (pitch, roll) 19-Nov 30-Nov Complete More sensor filtering and PID tuning may be needed
Tether Testing 3D stabilization (pitch, roll, yaw) 26-Nov - - Went directly to Flight Testing
Full Flight Testing 26-Nov 3-Dec Initial Testing More flight testing required
Demo 3-Dec 3-Dec Complete

Parts List & Cost

The table below summarizes the parts used and the cost for the Quadcopter project.

Qty Description Manufacturer Part Number Total Cost
4 Electric Speed Controller (ESC) Castle Creations 010-0125-00 $148.00
4 Park 480 Brushless Outrunner 1020kV motor E-Flight EFLM1505 $180.00
1 Triple Axis Accelerometer Breakout - ADXL345) Sparkfun SEN-09836 $27.95
1 Tri-Axis Gyro Breakout - L3G4200D Sparkfun SEN-10612 $49.95
1 Triple Axis Magnetometer Breakout - HMC5883L Sparkfun SEN-10530 $14.95
1 SJOne Board SJSU - $75.00
1 Logic Level Converter Bi-Directional Sparkfun BOB-12009 $2.95
1 Quad 2 Input Or Gate On-Semiconductor MC14071BCP $2.25
1 DX5E 5 Channel 2.4Ghz Tx/Rx Remote Control Spektrum DX5e $89.99
1 4000mAH 25C 3S Lipo battery Hyperion - $45.00
5 EC5 male and female connector Hobby King - $20.00
1 Black Silicon coated wire 12AWG 1 meter Hobby King - $5.00
1 Red Silicon coated wire 12AWG 1 meter Hobby King - $5.00
1 12x24 Aluminum Treadplate (0.063) Home Depot - $34.78
2 1/2" Aluminum Trim Channel, 4' Home Depot - $22.54
- Misc Nuts and Bolts Home Depot - $30.00
Total Cost $753.36

Design & Implementation

Hardware Design

The quadcopter consists of two main groups: the airframe, and the flight controller subsystem. The airframe consists of arms of 1/2 inch aluminum trim channel arms, sandwiched by 1/16 inch aluminum diamond plate. The assembled airframe is show below.

Cmpe240 f13 quadcopter frame.JPG


The quadcopter project flight controller subsystem block diagram is shown below. The major components are the SJ One board, the remote RX, the quad 2 input or gate, the accelerometer, the gyroscope, and the magnetometer, the 4 ESC modules, and the motors connected to the ESCs.

Cmpe240 f13 quadcopter hw block diagram.png

The quadcopter power distribution diagram is shown below. All power comes from the on board 3S 4000mAh 25C Lithium Polymer battery. The battery puts out 11.1V nominal, and the ESC takes in the 11.1V and outputs a 5V output for use by the rest of the flight controller. The SJ One board takes in the 5V and creates 3.3V to be used by the rest of the components.

Cmpe 240 f13 quadcopter power dist.png

Hardware Interface

PWM In From Remote Ctrl

The DX5e on board receiver outputs 5 channels of PWM input running at a 50Hz refresh rate. The voltage levels of the PWM in are 5V. The SJ One board is not 5V tolerant, and there are not 5 channels of input capture pins available. In order to get the values requested by the remote control, one needs to translate the voltage levels to 3.3V, and to try to combine the signals to a single input. After researching on line, an example design was found that took the 5 channels of input and or'ed all of them together to get a single pulse train out. The example design also suggested a 5V tolerant part that would output 3.3V. After investigating the hardware that is used on the Quadcopter project, it was decided that this could work. A logic analyzer capture of the receiver output is shown below, as well as the output of the or gate. As is shown, the pulse train does not overlap, so the or gate is sufficient to handle both the level shift to 3.3V and the combining of signals.

Cmpe240 f13 quadcopter pwm input.png

Below is a logical representation of how the or gate is wired.

Cmpe240 f13 quadcopter or gate pwm in.png

PWM Out

Quadcopters by nature need fast refresh rate on current position, and need low latency thru the control loop to actual commands to the motors. To help keep the latency low, the output PWM was ran at a faster than normal rate. The output PWM is running at 400hz instead of the normal 50hz refresh rate. The minimum pulse width is approx 1ms and the maximum pulse width is about 2 ms.

I2C Sensor Bus

The sensors all run off of a single I2C bus. The accelerometers base address is 0xE5, the magnetometer base address is 0x48, and the gyroscope base address is 0xD3. The I2C bus clock rate is 400kHz to help minimize the control loop latency.

Hardware Implementation

Here is the board layout.

Cmpe240 f13 quadcopter board layout.png

Here is a picture of the fully assembled quadcopter

Cmpe240 f13 quadcopter assembled.jpg

Software Design & Implementation

The top level software block diagram is shown below. The quadcopter project utilized free RTOS to help with scheduling. The following sections will go into the details on each block shown.


Cmpe240 f13 quadcopter sw block diagram.png

RX Capture ISR

The PWM input is connected to Capture pin CAP1.1 on gpio P1.19. The CAP input is setup to trigger an interrupt on each rising edge and each falling edge of the input PWM pulse train. The TIMER1_IRQHandler is setup to give a semaphore to get_remote_ctrl_values task, and then quickly clears the current interrupt. The get_remote_ctrl_values task is shown in the block diagram below.

Cmpe240 f13 quadcopter isr flowcharg.png

Remote Command Translator

The remote command translator task is a straight forward look up table. The throttle value is passed unchanged to the PWM output. All of the other inputs (roll, pitch, and yaw) are decoded and passed to the PID task as the new set point for the control loop. As a design decision, there is a hard limit of 30 degrees for each input. If the remote ctrl sets roll to be max value, the angle offset that is sent to the PID is limited to 30 degrees.

I2C Driver

The I2C Driver task calls low level I2C functions to read and write registers on the I2C slave devices. The I2C Driver is tasked with initialization of all I2C slave devices. It also handles burst reading of sensor registers. This driver task reads the sensor values every 5ms. All delta t values used in algorithms down stream use the delta t values measured this task. It is measured with internal timer 0.

This task is the driver for all tasks except the PWM input task. All downstream tasks are waiting for the output queue from this task to be written, and will then process the data.

This driver currently reads without checking to see if data is available. A possible optimization that would be to utilize the data ready interrupt from the gyro and accelerometer. Another optimization would be to increase the burst value from 2 8bit registers to 6 8bit registers.

Data Smoothing

Due to vibrational noise, an additional lowpass filter was added before the sensor fusion and after the I2C input. The filter acts on the raw sensor data after it has been scaled correctly. The code for the filter is quite simple:

    smoothed_value = smoothed_value + alpha * (input - smoothed_value);

There is very little latency thru the filter, and it really seemed to help with data noise.

Sensor Fusion

Sensor fusion is the act of taking reading from two or more sensors, and combining them in a meaningfull way. Sensor fusion is used in this case because we are taking data from a noisy accelerometer, and from a gyroscope that shows accumulated error on readings over a long time (more than a sec). We combine them such that we are taking the stable instantaneous values from the gyro and combining them with the long term stable values from the accelerometer. We manage this via a Complementary Filter. A complementary filter takes the angle values from both the accelerometer and the gyroscope and low pass filters the accelerometer,and high pass filters the integrated angular velocity from the gyroscope. See the figure below.

Cmpe240 f13 quadcopter complementary filter 3.jpg

This function can be implemented in a couple of lines of code for each axis.

    // Complementary Filter Implementation
    filtered_angle = (A)*(filtered_angle+gyro_rate*dt);
    filtered_angle += (1-A)*acc_angle;

There is a complementary filter for both the X and the Y axis. It was decided as the project was winding down to not implement yaw control due to schedule constraints. When there is time, there will be a complementary filter taking in gyro values and values from magnetometer to measure yaw and feed that into an additional PID stage to control the yaw.

PID

A PID controller is a flexible control loop often used when the impulse response of the system under control is unknown. A generic block diagram for a PID is shown below. PID is an acronym for Proportional, Integral, and Derivative control loop.

Cmpe240 f13 quadcopter pid 2.jpg

Proportional

The proportional leg of the control loop is simply the setpoint (from the rx input) and the current state of the quadcopter from the sensor fusion section. The equation is given by Kp*e(t) where Kp is the gain, and e(t) is the error term at time t.

The code is very simple:

    x_proportional_error = setpoint.thetaX - angle.thetaX;

If there were no inertia, or no friction, then the P would be all that was needed. The exact amount of error is subtracted from the controls, and would fix the error in an ideal world. Since the real world has both of those items, a control loop needs one or both of the other types of control.

Integral

The integral leg of the control loop is a running sum of the current proportional error multiplied by delta t, which is the time since the last sample.

The code looks like:

    x_integral_error += x_proportional_error*dt;

The integral portion of the control loop is there to account for environmental influences over the quadcopter. An example would be an unbalanced quadcopter such that one corner is heavier than the others. The control loop without an I would see that the quadcopter is not level and make the changes it is programed to do, but it still stays unbalances. The integral term of the loop will continually add error to the motors until it increases such that it levels the quadcopter.

Derivative

The derivative leg of the control loop is the change in error from the last sample to the current sample divided by the time interval.

This code looks like:

    x_derivative_error = (x_proportional_error - x_prev_error)/dt;

The derivative portion of the control loop predicts future errors based on the rate of change of past errors. It can speed up error correction or can put the brakes on as well helping stop over correction if tuned correctly.

PID Loop Implementation

The entire control loop for a single axis looks like this:

           x_proportional_error = setpoint.thetaX - angle.thetaX;
           x_integral_error += x_proportional_error*dt;
           x_derivative_error = (x_proportional_error - x_prev_error)/dt;
           x_error = x_proportional_error*proportional_gain + x_integral_error*integral_gain + x_derivative_error*derivative_gain;
           x_prev_error = x_proportional_error;

PWM Out

The error values out of the PID section are applied directly to the PWM pulse width math. See the code below:

           motor_front_sum = throttle_in +  error_in.errorX;
           motor_back_sum  = throttle_in + -error_in.errorX;
           motor_left_sum  = throttle_in +  error_in.errorY;
           motor_right_sum = throttle_in + -error_in.errorY;

Note, what was added to one half of front/back is subtracted from the other half. Same holds true for the left/right pair. This is done to keep the power coming out of props the same, and to keep the elevation control only come from the throttle.

The design also has limitations of pulse widths min and max to make sure not to disable the motors. If the throttle in + error is larger than the max value for pulse width, it clips at the max value. The same is true if throttle in + error is less than min pulse width. It holds the minimum value.

Testing & Technical Challenges

Testing

The first testing attempted was I2C read/write testing. Once the sensors were wired up, a quick while loop with a delay was implemented to show that the sensors could be read reliably.

The next portion of testing was the PWM input testing. This took a while to get right due to ISR issues. Once the ISR was working, it was possible to printf the pulsewidth values calculated and compare to what the input controls were set to.

To test the ability to run the motors correctly, a test task was created that would drive the motors at 25%, 50%, 75%, and 100% depending upon which button on the SJ One board was pressed.

The angle calculation for X, Y, and Z was tested by having the data_smoothing task print to the console 1 time out of every 100 calculations. The test consisted of holding the quadcopter in my hand and rotating it around each axis and watch the value of angle match the correct sign, as well as test if the magnitude was in the correct ballpark.

Once the angle calculation seemed correct, the feedback loop was closed by adding in the PID with a guess of the values. To do this testing, we attached the quadcopter between two saw horses so that it could only rotate in a single plane. The majority of testing was of this type. PID gain values were tested until the X axis was quasi stable. We then switched to the Y axis and set the PID gains to the same values. After fixing some sign errors, and other math errors, we were able to make the Y axis mostly stable as well. A video of some 2D testing can be found at the link below.

The final bit of testing attempted was flight testing. This testing showed that we need to make sure to implement the yaw control. Once the quadcopter lifted off, it started to yaw, which made it hard to fly correctly. Video of flight testing can be found in the section marked Project Video.

Technical Challenges

One of the largest technical challenges found was getting the PWM input ISR to not crash the processor, and to operate correctly. After long hours of debugging it was found that there was a low level driver that was using the same timer interrupt. Once this was solved, the development went a lot smoother, and we were able to reliably receive the commands from the remote control, and have the flight control software act upon these commands.

The largest technical challenge found is still being investigated. There seem to be some issues with the data coming out of the sensors. In an attempt to clean this up, there was some additional data smoothing added to both the gyro output and the accel output. This did help the stability of the flight correction, but there are still issues.

Another technical challenge found was the process of tuning the PID gain values. This will continue to be a work in progress until the sensor reads are clean and accurate.

Conclusion

The quadcopter was a very challenging project. While I was not able to achieve the stable flight I had been hoping for, the quadcopter did fly. The project was a great learning experience. I learned a lot about the LPC1758. I learned a lot about interrupt service routines. I learned a lot about IMU's and flight control software. I learned a lot about how to implement and tune a PID control loop.

The next step for the quadcopter project will be to implement the yaw control and yaw portion of the PID. I also want to continue attempting to clean up the data from the sensors. There may be some issues with noise and or discontinuities on the I2C reads. This will be facilitated by getting data logging to the mico SD card working. I will then be able to characterize any data problems off line via matlab, and target filtering and or changes to sensor reads to fix the issues. Another possible upgrade on the I2C reads will be to enable the data ready interrupts from the sensors, and only read them when I know data is ready.

Project Video

Project Source Code

References

Acknowledgement

I would like to acknowledge and thank my patient wife Sandie for putting up with all the time spent on the project.

I would like to acknowledge and thank Brandon for loaning me his logic analyzer and being there to field my software questions.

I would like to acknowledge and thank Rob for lending me his RC expertise, and answering all of my silly questions.

I would like to acknowledge and thank Preet for the help with the ISR issues encountered and for teaching a very interesting class.

References Used

LPC1758 Datasheet
LPC1758 User Manual
Gyro Datasheet
Accel Datasheet<br\> Magno Datasheet<br\> Bluetooth Datasheet <br\> http://nicisdigital.wordpress.com/category/quadcopter/
http://web.mit.edu/scolton/www/filter.pdf
http://theboredengineers.com/2012/05/the-quadcopter-basics/
http://theboredengineers.com/2012/05/the-quadcopter-part-1-genesis-of-the-project/
http://www.instructables.com/id/RC-Quadrotor-Helicopter/?ALLSTEPS
http://blog.oscarliang.net/quadcopter-pid-explained-tuning/