void stabilisation_wing_cascade_stabilise(stabilisation_wing_t* stabilisation_wing)
{
float rpyt_errors[4];
control_command_t input;
int32_t i;
float feedforward[4];
float nav_heading, current_heading, heading_error;
float gps_speed_global[3], gps_speed_semi_local[3];
float input_turn_rate;
float input_roll_angle;
aero_attitude_t attitude, attitude_yaw;
quat_t q_rot;
float airspeed_desired;
float clipping_factor;
// Get up vector in body frame
quat_t up = {0.0f, {UPVECTOR_X, UPVECTOR_Y, UPVECTOR_Z}};
quat_t up_vec = quaternions_global_to_local(stabilisation_wing->ahrs->qe,
up);
// set the controller input
input= *stabilisation_wing->controls;
switch (stabilisation_wing->controls->control_mode)
{
case VELOCITY_COMMAND_MODE:
// Get current attitude
attitude_yaw = coord_conventions_quat_to_aero(stabilisation_wing->ahrs->qe);
/////////////
// HEADING //
/////////////
// Compute the heading angle corresponding to the given input velocity vector (input from remote/vector field should be in semi-local frame).
nav_heading = heading_from_velocity_vector(input.tvel);
// Overwrite command if in remote
if(stabilisation_wing->controls->yaw_mode == YAW_RELATIVE)
{
nav_heading = maths_calc_smaller_angle(input.rpy[YAW] - attitude_yaw.rpy[YAW]);
}
// Compute current heading
gps_speed_global[X] = stabilisation_wing->gps->velocity_lf()[0];
gps_speed_global[Y] = stabilisation_wing->gps->velocity_lf()[1];
gps_speed_global[Z] = stabilisation_wing->pos_est->vel[Z];
// Transform global to semi-local
attitude_yaw.rpy[0] = 0.0f;
attitude_yaw.rpy[1] = 0.0f;
attitude_yaw.rpy[2] = -attitude_yaw.rpy[2];
q_rot = coord_conventions_quaternion_from_aero(attitude_yaw);
quaternions_rotate_vector(q_rot, gps_speed_global, gps_speed_semi_local);
current_heading = heading_from_velocity_vector(gps_speed_semi_local);
// Compute heading error
heading_error = maths_calc_smaller_angle(nav_heading - current_heading);
///////////////
// PID INPUT //
///////////////
// Vector field normalize vector in plane x-y to cruise_speed value ==> airspeed should be done only on the x-y composants
airspeed_desired = sqrtf(input.tvel[X]*input.tvel[X] + input.tvel[Y]*input.tvel[Y]);
// Compute errors
rpyt_errors[0] = heading_error; // Heading
rpyt_errors[1] = input.tvel[Z] - gps_speed_global[Z]; // Vertical speed
rpyt_errors[2] = 0.0f;
rpyt_errors[3] = airspeed_desired - stabilisation_wing->airspeed_analog->get_airspeed(); // Airspeed
// Compute the feedforward
feedforward[0] = 0.0f;
feedforward[1] = 0.0f;
feedforward[2] = 0.0f;
feedforward[3] = (airspeed_desired - 13.0f)/8.0f + 0.2f;
// run PID update on all velocity controllers
stabilisation_run_feedforward(&stabilisation_wing->stabiliser_stack.velocity_stabiliser, stabilisation_wing->ahrs->dt_s, rpyt_errors, feedforward);
////////////////
// PID OUTPUT //
////////////////
// Get turn rate command and transform it into a roll angle command for next layer
input_turn_rate = stabilisation_wing->stabiliser_stack.velocity_stabiliser.output.rpy[0];
// TODO: Fix this in case of bad airspeed readings...
clipping_factor = stabilisation_wing->max_roll_angle / (PI/2.0f);
if(clipping_factor == 0.0f)
{
input_roll_angle = 0.0f;
}
else
{
input_roll_angle = clipping_factor * atanf( (1.0f/clipping_factor) * (stabilisation_wing->airspeed_analog->get_airspeed() * input_turn_rate / 9.81f) );
}
// Set input for next layer
input = stabilisation_wing->stabiliser_stack.velocity_stabiliser.output;
input.rpy[0] = input_roll_angle;
input.rpy[1] = - stabilisation_wing->stabiliser_stack.velocity_stabiliser.output.rpy[1];
input.thrust = stabilisation_wing->stabiliser_stack.velocity_stabiliser.output.thrust;
// Overwrite the commands during different key phases (take-off and landing)
if(stabilisation_wing->navigation->internal_state_ == Navigation::NAV_TAKEOFF)
{
// Take-off: fixed 0 roll angle, fixed defined pitch angle and fixed defined constant thrust value.
input.rpy[0] = 0.0f;
input.rpy[1] = stabilisation_wing->take_off_pitch;
input.thrust = stabilisation_wing->take_off_thrust;
}
else if(stabilisation_wing->navigation->internal_state_ == Navigation::NAV_LANDING)
{
// Landing: Limit the roll computed by the velocity layer (navigation), shut down the motor and impose a little pitch down to assure gliding without stall.
if(input.rpy[0] > stabilisation_wing->landing_max_roll)
{
input.rpy[0] = stabilisation_wing->landing_max_roll;
}
else if(input.rpy[0] < -stabilisation_wing->landing_max_roll)
{
input.rpy[0] = -stabilisation_wing->landing_max_roll;
}
input.rpy[1] = stabilisation_wing->landing_pitch;
input.thrust = -1.0f;
}
// -- no break here - we want to run the lower level modes as well! --
case ATTITUDE_COMMAND_MODE:
// Add "a priori on the pitch" to fly horizontally and to compensate for roll angle
attitude = coord_conventions_quat_to_aero(stabilisation_wing->ahrs->qe);
input.rpy[1] += stabilisation_wing->pitch_angle_apriori; // Constant compensation for horizontal
if(maths_f_abs(attitude.rpy[ROLL]) < PI/2.0f) // Compensation for the roll bank angle
{
input.rpy[1] += stabilisation_wing->pitch_angle_apriori_gain * maths_f_abs(input.rpy[0]*input.rpy[0]*input.rpy[0]);
}
// run absolute attitude_filter controller
rpyt_errors[0]= sinf(input.rpy[0]) + up_vec.v[1]; // Roll
rpyt_errors[1]= sinf(input.rpy[1]) - up_vec.v[0]; // Pitch
rpyt_errors[2]= 0.0f; // Yaw
rpyt_errors[3]= input.thrust; // no feedback for thrust at this level
// run PID update on all attitude_filter controllers
stabilisation_run(&stabilisation_wing->stabiliser_stack.attitude_stabiliser, stabilisation_wing->ahrs->dt_s, rpyt_errors);
// use output of attitude_filter controller to set rate setpoints for rate controller
input = stabilisation_wing->stabiliser_stack.attitude_stabiliser.output;
// -- no break here - we want to run the lower level modes as well! --
case RATE_COMMAND_MODE: // this level is always run
// get rate measurements from IMU (filtered angular rates)
for (i=0; i<3; i++)
{
rpyt_errors[i]= input.rpy[i]- stabilisation_wing->ahrs->angular_speed[i];
}
rpyt_errors[3] = input.thrust ; // no feedback for thrust at this level
// run PID update on all rate controllers
stabilisation_run(&stabilisation_wing->stabiliser_stack.rate_stabiliser, stabilisation_wing->ahrs->dt_s, rpyt_errors);
}
stabilisation_wing->torque_command->xyz[0] = stabilisation_wing->stabiliser_stack.rate_stabiliser.output.rpy[ROLL];
stabilisation_wing->torque_command->xyz[1] = stabilisation_wing->stabiliser_stack.rate_stabiliser.output.rpy[PITCH];
stabilisation_wing->thrust_command->thrust = stabilisation_wing->stabiliser_stack.rate_stabiliser.output.thrust;
}
void stabilisation_copter_cascade_stabilise(stabilisation_copter_t* stabilisation_copter)
{
float rpyt_errors[4];
control_command_t input;
int32_t i;
quat_t qtmp, q_rot;
aero_attitude_t attitude_yaw_inverse;
// set the controller input
input= *stabilisation_copter->controls;
switch (stabilisation_copter->controls->control_mode)
{
case VELOCITY_COMMAND_MODE:
attitude_yaw_inverse = coord_conventions_quat_to_aero(stabilisation_copter->ahrs->qe);
attitude_yaw_inverse.rpy[0] = 0.0f;
attitude_yaw_inverse.rpy[1] = 0.0f;
attitude_yaw_inverse.rpy[2] = attitude_yaw_inverse.rpy[2];
//qtmp=quaternions_create_from_vector(input.tvel);
//quat_t input_global = quaternions_local_to_global(stabilisation_copter->ahrs->qe, qtmp);
q_rot = coord_conventions_quaternion_from_aero(attitude_yaw_inverse);
quat_t input_global;
quaternions_rotate_vector(q_rot, input.tvel, input_global.v);
input.tvel[X] = input_global.v[X];
input.tvel[Y] = input_global.v[Y];
input.tvel[Z] = input_global.v[Z];
rpyt_errors[X] = input.tvel[X] - stabilisation_copter->pos_est->vel[X];
rpyt_errors[Y] = input.tvel[Y] - stabilisation_copter->pos_est->vel[Y];
rpyt_errors[3] = -(input.tvel[Z] - stabilisation_copter->pos_est->vel[Z]);
if (stabilisation_copter->controls->yaw_mode == YAW_COORDINATED)
{
float rel_heading_coordinated;
if ((maths_f_abs(stabilisation_copter->pos_est->vel_bf[X])<0.001f)&&(maths_f_abs(stabilisation_copter->pos_est->vel_bf[Y])<0.001f))
{
rel_heading_coordinated = 0.0f;
}
else
{
rel_heading_coordinated = atan2(stabilisation_copter->pos_est->vel_bf[Y], stabilisation_copter->pos_est->vel_bf[X]);
}
float w = 0.5f * (maths_sigmoid(vectors_norm(stabilisation_copter->pos_est->vel_bf)-stabilisation_copter->stabiliser_stack.yaw_coordination_velocity) + 1.0f);
input.rpy[YAW] = (1.0f - w) * input.rpy[YAW] + w * rel_heading_coordinated;
}
rpyt_errors[YAW]= input.rpy[YAW];
// run PID update on all velocity controllers
stabilisation_run(&stabilisation_copter->stabiliser_stack.velocity_stabiliser, stabilisation_copter->imu->dt, rpyt_errors);
//velocity_stabiliser.output.thrust = maths_f_min(velocity_stabiliser.output.thrust,stabilisation_param.controls->thrust);
stabilisation_copter->stabiliser_stack.velocity_stabiliser.output.thrust += stabilisation_copter->thrust_hover_point;
stabilisation_copter->stabiliser_stack.velocity_stabiliser.output.theading = input.theading;
input = stabilisation_copter->stabiliser_stack.velocity_stabiliser.output;
qtmp=quaternions_create_from_vector(stabilisation_copter->stabiliser_stack.velocity_stabiliser.output.rpy);
//quat_t rpy_local = quaternions_global_to_local(stabilisation_copter->ahrs->qe, qtmp);
quat_t rpy_local;
quaternions_rotate_vector(quaternions_inverse(q_rot), qtmp.v, rpy_local.v);
input.rpy[ROLL] = rpy_local.v[Y];
input.rpy[PITCH] = -rpy_local.v[X];
//input.thrust = stabilisation_copter->controls->tvel[Z];
// -- no break here - we want to run the lower level modes as well! --
case ATTITUDE_COMMAND_MODE:
// run absolute attitude_filter controller
rpyt_errors[0]= input.rpy[0] - ( - stabilisation_copter->ahrs->up_vec.v[1] );
rpyt_errors[1]= input.rpy[1] - stabilisation_copter->ahrs->up_vec.v[0];
if ((stabilisation_copter->controls->yaw_mode == YAW_ABSOLUTE) )
{
rpyt_errors[2] =maths_calc_smaller_angle(input.theading- stabilisation_copter->pos_est->local_position.heading);
}
else
{ // relative yaw
rpyt_errors[2]= input.rpy[2];
}
rpyt_errors[3]= input.thrust; // no feedback for thrust at this level
// run PID update on all attitude_filter controllers
stabilisation_run(&stabilisation_copter->stabiliser_stack.attitude_stabiliser, stabilisation_copter->imu->dt, rpyt_errors);
// use output of attitude_filter controller to set rate setpoints for rate controller
input = stabilisation_copter->stabiliser_stack.attitude_stabiliser.output;
// -- no break here - we want to run the lower level modes as well! --
case RATE_COMMAND_MODE: // this level is always run
// get rate measurements from IMU (filtered angular rates)
for (i=0; i<3; i++)
{
rpyt_errors[i]= input.rpy[i]- stabilisation_copter->ahrs->angular_speed[i];
}
rpyt_errors[3] = input.thrust ; // no feedback for thrust at this level
// run PID update on all rate controllers
stabilisation_run(&stabilisation_copter->stabiliser_stack.rate_stabiliser, stabilisation_copter->imu->dt, rpyt_errors);
}
// mix to servo outputs depending on configuration
if( stabilisation_copter->motor_layout == QUADCOPTER_MOTOR_LAYOUT_DIAG )
{
stabilisation_copter_mix_to_servos_diag_quad(&stabilisation_copter->stabiliser_stack.rate_stabiliser.output, stabilisation_copter->servos);
}
else if( stabilisation_copter->motor_layout == QUADCOPTER_MOTOR_LAYOUT_CROSS )
{
stabilisation_copter_mix_to_servos_cross_quad(&stabilisation_copter->stabiliser_stack.rate_stabiliser.output, stabilisation_copter->servos);
}
}
