ardupilot/ArducopterNG/Attitude.pde

/*
 www.ArduCopter.com - www.DIYDrones.com
 Copyright (c) 2010.  All rights reserved.
 An Open Source Arduino based multicopter.
 
 File     : Attitude.pde
 Version  : v1.0, Aug 27, 2010
 Author(s): ArduCopter Team
             Ted Carancho (aeroquad), Jose Julio, Jordi Muñoz,
             Jani Hirvinen, Ken McEwans, Roberto Navoni,          
             Sandro Benigno, Chris Anderson
 
 This program is free software: you can redistribute it and/or modify
 it under the terms of the GNU General Public License as published by
 the Free Software Foundation, either version 3 of the License, or
 (at your option) any later version.
 
 This program is distributed in the hope that it will be useful,
 but WITHOUT ANY WARRANTY; without even the implied warranty of
 MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
 GNU General Public License for more details.
 
 You should have received a copy of the GNU General Public License
 along with this program. If not, see <http://www.gnu.org/licenses/>.

* ************************************************************** *
ChangeLog:


* ************************************************************** *
TODO:


* ************************************************************** */

/* ************************************************************ */

////////////////////////////////////////////////// 
// Function  : Attitude_control_v3()
//
//             Stable flight mode main algoritms
//
// Parameters: 
//     - none
//
// Returns   : - none
//
// Alters    : 
//  err_roll, roll_rate
//
// Relies    :
//  Radio input, Gyro
//

/* ************************************************************ */
// STABLE MODE
// PI absolute angle control driving a P rate control
// Input : desired Roll, Pitch and Yaw absolute angles. Output : Motor commands
void Attitude_control_v3(int command_roll, int command_pitch, int command_yaw)
{
  float stable_roll,stable_pitch,stable_yaw;
  
  // ROLL CONTROL    
  err_roll = command_roll - ToDeg(roll);
  err_roll = constrain(err_roll,-25,25);  // to limit max roll command...
  
  roll_I += err_roll*G_Dt;
  roll_I = constrain(roll_I,-20,20);

  // PID absolute angle control
  stable_roll = KP_QUAD_ROLL*err_roll + KI_QUAD_ROLL*roll_I;
  
  // PD rate control (we use also the bias corrected gyro rates)
  err_roll = stable_roll - ToDeg(Omega[0]); // Omega[] is the raw gyro reading plus Omega_I, so it´s bias corrected
  control_roll = STABLE_MODE_KP_RATE_ROLL*err_roll;
  
  // PITCH CONTROL
  err_pitch = command_pitch - ToDeg(pitch);
  err_pitch = constrain(err_pitch,-25,25);  // to limit max pitch command...
  
  pitch_I += err_pitch*G_Dt;
  pitch_I = constrain(pitch_I,-20,20);
 
  // PID absolute angle control
  stable_pitch = KP_QUAD_PITCH*err_pitch + KI_QUAD_PITCH*pitch_I;
  
  // P rate control (we use also the bias corrected gyro rates)
  err_pitch = stable_pitch - ToDeg(Omega[1]);
  control_pitch = STABLE_MODE_KP_RATE_PITCH*err_pitch;
  
  // YAW CONTROL
  err_yaw = command_yaw - ToDeg(yaw);
  if (err_yaw > 180)    // Normalize to -180,180
    err_yaw -= 360;
  else if(err_yaw < -180)
    err_yaw += 360;
  err_yaw = constrain(err_yaw,-60,60);  // to limit max yaw command...
  
  yaw_I += err_yaw*G_Dt;
  yaw_I = constrain(yaw_I,-20,20);
 
  // PID absoulte angle control
  stable_yaw = KP_QUAD_YAW*err_yaw + KI_QUAD_YAW*yaw_I;
  // PD rate control (we use also the bias corrected gyro rates)
  err_yaw = stable_yaw - ToDeg(Omega[2]);
  control_yaw = STABLE_MODE_KP_RATE_YAW*err_yaw;
}

// ACRO MODE


////////////////////////////////////////////////// 
// Function  : Rate_control()
//
//             Acro mode main algoritms
//
// Parameters: 
//     - none
//
// Returns   : - none
//
// Alters    : 
//  err_roll, roll_rate
//
// Relies    :
//  Radio input, Gyro
//


// ACRO MODE
void Rate_control_v2()
{
  static float previousRollRate, previousPitchRate, previousYawRate;
  float currentRollRate, currentPitchRate, currentYawRate;
  
  // ROLL CONTROL
  currentRollRate = ToDeg(Omega[0]);  // Omega[] is the raw gyro reading plus Omega_I, so it´s bias corrected
  err_roll = ((ch_roll- roll_mid) * xmitFactor) - currentRollRate;  
  roll_I += err_roll*G_Dt;
  roll_I = constrain(roll_I,-20,20);
  roll_D = (currentRollRate - previousRollRate)/G_Dt;
  previousRollRate = currentRollRate;  
  // PID control
  control_roll = Kp_RateRoll*err_roll + Kd_RateRoll*roll_D + Ki_RateRoll*roll_I; 
  
  // PITCH CONTROL
  currentPitchRate = ToDeg(Omega[1]);  // Omega[] is the raw gyro reading plus Omega_I, so it´s bias corrected
  err_pitch = ((ch_pitch - pitch_mid) * xmitFactor) - currentPitchRate;
  
  pitch_I += err_pitch*G_Dt;
  pitch_I = constrain(pitch_I,-20,20);

  pitch_D = (currentPitchRate - previousPitchRate)/G_Dt;
  previousPitchRate = currentPitchRate;
 
  // PID control
  control_pitch = Kp_RatePitch*err_pitch + Kd_RatePitch*pitch_D + Ki_RatePitch*pitch_I; 
  
  // YAW CONTROL
  currentYawRate = ToDeg(Omega[2]);  // Omega[] is the raw gyro reading plus Omega_I, so it´s bias corrected;
  err_yaw = ((ch_yaw - yaw_mid)* xmitFactor) - currentYawRate;
  
  yaw_I += err_yaw*G_Dt;
  yaw_I = constrain(yaw_I,-20,20);

  yaw_D = (currentYawRate - previousYawRate)/G_Dt;
  previousYawRate = currentYawRate;
 
  // PID control
  control_yaw = Kp_RateYaw*err_yaw + Kd_RateYaw*yaw_D + Ki_RateYaw*yaw_I; 
}