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Copter: consolidate mode state decisions

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bnsgeyer and rmackay9 contributed to these changes

make_safe_shut_down waits for spool down before disarming
remove use of attitude_control::set_throttle_out_unstabilized to consolidate logic between multicopters and tradhelis
This commit is contained in:
Leonard Hall 2019-02-28 18:03:23 +09:00 committed by Randy Mackay
parent d949c80d54
commit 38cc5a817f
20 changed files with 842 additions and 880 deletions
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24
ArduCopter/defines.h
View File

@ -176,30 +176,6 @@ enum SmartRTLState {
SmartRTL_Land SmartRTL_Land
}; };
// Alt_Hold states
enum AltHoldModeState {
AltHold_MotorStopped,
AltHold_Takeoff,
AltHold_Flying,
AltHold_Landed
};
// Loiter states
enum LoiterModeState {
Loiter_MotorStopped,
Loiter_Takeoff,
Loiter_Flying,
Loiter_Landed
};
// Sport states
enum SportModeState {
Sport_MotorStopped,
Sport_Takeoff,
Sport_Flying,
Sport_Landed
};
// Flip states // Flip states
enum FlipState { enum FlipState {
Flip_Start, Flip_Start,

93
ArduCopter/mode.cpp
View File

@ -396,14 +396,43 @@ void Copter::Mode::zero_throttle_and_relax_ac(bool spool_up)
} else { } else {
motors->set_desired_spool_state(AP_Motors::DESIRED_GROUND_IDLE); motors->set_desired_spool_state(AP_Motors::DESIRED_GROUND_IDLE);
} }
#if FRAME_CONFIG == HELI_FRAME
// Helicopters always stabilize roll/pitch/yaw
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(0.0f, 0.0f, 0.0f); attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(0.0f, 0.0f, 0.0f);
attitude_control->set_throttle_out(0.0f, false, copter.g.throttle_filt); attitude_control->set_throttle_out(0.0f, false, copter.g.throttle_filt);
#else }
// multicopters do not stabilize roll/pitch/yaw when disarmed
attitude_control->set_throttle_out_unstabilized(0.0f, true, copter.g.throttle_filt); void Copter::Mode::zero_throttle_and_hold_attitude()
#endif {
// run attitude controller
attitude_control->input_rate_bf_roll_pitch_yaw(0.0f, 0.0f, 0.0f);
attitude_control->set_throttle_out(0.0f, false, copter.g.throttle_filt);
}
void Copter::Mode::make_safe_shut_down()
{
// command aircraft to initiate the shutdown process
motors->set_desired_spool_state(AP_Motors::DESIRED_SHUT_DOWN);
switch (motors->get_spool_mode()) {
case AP_Motors::SHUT_DOWN:
case AP_Motors::GROUND_IDLE:
// relax controllers during idle states
attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading();
break;
default:
// while transitioning though active states continue to operate normally
break;
}
// we may need to move this out
wp_nav->wp_and_spline_init();
// we may need to move this out
loiter_nav->init_target();
pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
pos_control->update_z_controller();
// we may need to move this out
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(0.0f, 0.0f, 0.0f);
} }
/* /*
@ -596,6 +625,58 @@ float Copter::Mode::get_pilot_desired_throttle() const
return throttle_out; return throttle_out;
} }
Copter::Mode::AltHoldModeState Copter::Mode::get_alt_hold_state(float target_climb_rate_cms)
{
// Alt Hold State Machine Determination
if (!motors->armed()) {
// the aircraft should moved to a shut down state
motors->set_desired_spool_state(AP_Motors::DESIRED_SHUT_DOWN);
// transition through states as aircraft spools down
switch (motors->get_spool_mode()) {
case AP_Motors::SHUT_DOWN:
return AltHold_MotorStopped;
case AP_Motors::DESIRED_GROUND_IDLE:
return AltHold_Landed_Ground_Idle;
default:
return AltHold_Landed_Pre_Takeoff;
}
} else if (takeoff.running() || takeoff.triggered(target_climb_rate_cms)) {
// the aircraft is currently landed or taking off, asking for a positive climb rate and in THROTTLE_UNLIMITED
// the aircraft should progress through the take off procedure
return AltHold_Takeoff;
} else if (!ap.auto_armed || ap.land_complete) {
// the aircraft is armed and landed
if (target_climb_rate_cms < 0.0f && !ap.using_interlock) {
// the aircraft should move to a ground idle state
motors->set_desired_spool_state(AP_Motors::DESIRED_GROUND_IDLE);
} else {
// the aircraft should prepare for imminent take off
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
}
if (motors->get_spool_mode() == AP_Motors::GROUND_IDLE) {
// the aircraft is waiting in ground idle
return AltHold_Landed_Ground_Idle;
} else {
// the aircraft can leave the ground at any time
return AltHold_Landed_Pre_Takeoff;
}
} else {
// the aircraft is in a flying state
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
return AltHold_Flying;
}
}
// pass-through functions to reduce code churn on conversion; // pass-through functions to reduce code churn on conversion;
// these are candidates for moving into the Mode base // these are candidates for moving into the Mode base
// class. // class.

12
ArduCopter/mode.h
View File

@ -116,6 +116,8 @@ protected:
// helper functions // helper functions
void zero_throttle_and_relax_ac(bool spool_up = false); void zero_throttle_and_relax_ac(bool spool_up = false);
void zero_throttle_and_hold_attitude();
void make_safe_shut_down();
// functions to control landing // functions to control landing
// in modes that support landing // in modes that support landing
@ -126,6 +128,16 @@ protected:
// return expected input throttle setting to hover: // return expected input throttle setting to hover:
virtual float throttle_hover() const; virtual float throttle_hover() const;
// Alt_Hold based flight mode states used in Alt_Hold, Loiter, and Sport
enum AltHoldModeState {
AltHold_MotorStopped,
AltHold_Takeoff,
AltHold_Landed_Ground_Idle,
AltHold_Landed_Pre_Takeoff,
AltHold_Flying
};
AltHoldModeState get_alt_hold_state(float target_climb_rate_cms);
// convenience references to avoid code churn in conversion: // convenience references to avoid code churn in conversion:
Parameters &g; Parameters &g;
ParametersG2 &g2; ParametersG2 &g2;

35
ArduCopter/mode_acro.cpp
View File

@ -10,21 +10,34 @@
void Copter::ModeAcro::run() void Copter::ModeAcro::run()
{ {
// convert the input to the desired body frame rate
float target_roll, target_pitch, target_yaw; float target_roll, target_pitch, target_yaw;
get_pilot_desired_angle_rates(channel_roll->get_control_in(), channel_pitch->get_control_in(), channel_yaw->get_control_in(), target_roll, target_pitch, target_yaw);
// if not armed set throttle to zero and exit immediately if (!motors->armed()) {
if (!motors->armed() || ap.throttle_zero || !motors->get_interlock()) { // Motors should be Stopped
zero_throttle_and_relax_ac(); motors->set_desired_spool_state(AP_Motors::DESIRED_SHUT_DOWN);
return; } else if (ap.throttle_zero) {
// Attempting to Land
motors->set_desired_spool_state(AP_Motors::DESIRED_GROUND_IDLE);
} else {
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
} }
// clear landing flag if (motors->get_spool_mode() == AP_Motors::SHUT_DOWN) {
set_land_complete(false); // Motors Stopped
attitude_control->set_yaw_target_to_current_heading();
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED); attitude_control->reset_rate_controller_I_terms();
} else if (motors->get_spool_mode() == AP_Motors::GROUND_IDLE) {
// convert the input to the desired body frame rate // Landed
get_pilot_desired_angle_rates(channel_roll->get_control_in(), channel_pitch->get_control_in(), channel_yaw->get_control_in(), target_roll, target_pitch, target_yaw); attitude_control->set_yaw_target_to_current_heading();
attitude_control->reset_rate_controller_I_terms();
} else if (motors->get_spool_mode() == AP_Motors::THROTTLE_UNLIMITED) {
// clear landing flag above zero throttle
if (!motors->limit.throttle_lower) {
set_land_complete(false);
}
}
// run attitude controller // run attitude controller
attitude_control->input_rate_bf_roll_pitch_yaw(target_roll, target_pitch, target_yaw); attitude_control->input_rate_bf_roll_pitch_yaw(target_roll, target_pitch, target_yaw);

78
ArduCopter/mode_althold.cpp
View File

@ -21,7 +21,6 @@ bool Copter::ModeAltHold::init(bool ignore_checks)
// should be called at 100hz or more // should be called at 100hz or more
void Copter::ModeAltHold::run() void Copter::ModeAltHold::run()
{ {
AltHoldModeState althold_state;
float takeoff_climb_rate = 0.0f; float takeoff_climb_rate = 0.0f;
// initialize vertical speeds and acceleration // initialize vertical speeds and acceleration
@ -43,40 +42,30 @@ void Copter::ModeAltHold::run()
target_climb_rate = constrain_float(target_climb_rate, -get_pilot_speed_dn(), g.pilot_speed_up); target_climb_rate = constrain_float(target_climb_rate, -get_pilot_speed_dn(), g.pilot_speed_up);
// Alt Hold State Machine Determination // Alt Hold State Machine Determination
if (!motors->armed() || !motors->get_interlock()) { AltHoldModeState althold_state = get_alt_hold_state(target_climb_rate);
althold_state = AltHold_MotorStopped;
} else if (takeoff.running() || takeoff.triggered(target_climb_rate)) {
althold_state = AltHold_Takeoff;
} else if (!ap.auto_armed || ap.land_complete) {
althold_state = AltHold_Landed;
} else {
althold_state = AltHold_Flying;
}
// Alt Hold State Machine // Alt Hold State Machine
switch (althold_state) { switch (althold_state) {
case AltHold_MotorStopped: case AltHold_MotorStopped:
motors->set_desired_spool_state(AP_Motors::DESIRED_SHUT_DOWN);
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(target_roll, target_pitch, target_yaw_rate);
attitude_control->reset_rate_controller_I_terms(); attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading(); attitude_control->set_yaw_target_to_current_heading();
#if FRAME_CONFIG == HELI_FRAME
// force descent rate and call position controller
pos_control->set_alt_target_from_climb_rate(-abs(g.land_speed), G_Dt, false);
if (ap.land_complete_maybe) {
pos_control->relax_alt_hold_controllers(0.0f);
}
#else
pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
#endif break;
pos_control->update_z_controller();
case AltHold_Landed_Ground_Idle:
attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading();
// FALLTHROUGH
case AltHold_Landed_Pre_Takeoff:
pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
break; break;
case AltHold_Takeoff: case AltHold_Takeoff:
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// initiate take-off // initiate take-off
if (!takeoff.running()) { if (!takeoff.running()) {
@ -93,38 +82,9 @@ void Copter::ModeAltHold::run()
// get avoidance adjusted climb rate // get avoidance adjusted climb rate
target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate); target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate);
// call attitude controller // set position controller targets
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(target_roll, target_pitch, target_yaw_rate);
// call position controller
pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false); pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
pos_control->add_takeoff_climb_rate(takeoff_climb_rate, G_Dt); pos_control->add_takeoff_climb_rate(takeoff_climb_rate, G_Dt);
pos_control->update_z_controller();
break;
case AltHold_Landed:
#if FRAME_CONFIG == HELI_FRAME
// helicopters do not spool down when landed. Only when commanded to go to ground idle by pilot.
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
if (motors->init_targets_on_arming()) {
attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading();
}
#else
// set motors to spin-when-armed if throttle below deadzone, otherwise full range (but motors will only spin at min throttle)
if (target_climb_rate < 0.0f) {
motors->set_desired_spool_state(AP_Motors::DESIRED_GROUND_IDLE);
} else {
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
}
attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading();
#endif
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(target_roll, target_pitch, target_yaw_rate);
pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
pos_control->update_z_controller();
break; break;
case AltHold_Flying: case AltHold_Flying:
@ -135,18 +95,20 @@ void Copter::ModeAltHold::run()
copter.avoid.adjust_roll_pitch(target_roll, target_pitch, copter.aparm.angle_max); copter.avoid.adjust_roll_pitch(target_roll, target_pitch, copter.aparm.angle_max);
#endif #endif
// call attitude controller
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(target_roll, target_pitch, target_yaw_rate);
// adjust climb rate using rangefinder // adjust climb rate using rangefinder
target_climb_rate = get_surface_tracking_climb_rate(target_climb_rate, pos_control->get_alt_target(), G_Dt); target_climb_rate = get_surface_tracking_climb_rate(target_climb_rate, pos_control->get_alt_target(), G_Dt);
// get avoidance adjusted climb rate // get avoidance adjusted climb rate
target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate); target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate);
// call position controller
pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false); pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
pos_control->update_z_controller();
break; break;
} }
// call attitude controller
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(target_roll, target_pitch, target_yaw_rate);
// call z-axis position controller
pos_control->update_z_controller();
} }

48
ArduCopter/mode_auto.cpp
View File

@ -729,16 +729,6 @@ void Copter::ModeAuto::takeoff_run()
// called by auto_run at 100hz or more // called by auto_run at 100hz or more
void Copter::ModeAuto::wp_run() void Copter::ModeAuto::wp_run()
{ {
// if not auto armed or motor interlock not enabled set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || !motors->get_interlock()) {
// To-Do: reset waypoint origin to current location because copter is probably on the ground so we don't want it lurching left or right on take-off
// (of course it would be better if people just used take-off)
zero_throttle_and_relax_ac();
// clear i term when we're taking off
set_throttle_takeoff();
return;
}
// process pilot's yaw input // process pilot's yaw input
float target_yaw_rate = 0; float target_yaw_rate = 0;
if (!copter.failsafe.radio) { if (!copter.failsafe.radio) {
@ -749,6 +739,12 @@ void Copter::ModeAuto::wp_run()
} }
} }
// if not armed set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || ap.land_complete) {
make_safe_shut_down();
return;
}
// set motors to full range // set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED); motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
@ -772,13 +768,9 @@ void Copter::ModeAuto::wp_run()
// called by auto_run at 100hz or more // called by auto_run at 100hz or more
void Copter::ModeAuto::spline_run() void Copter::ModeAuto::spline_run()
{ {
// if not auto armed or motor interlock not enabled set throttle to zero and exit immediately // if not armed set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || !motors->get_interlock()) { if (!motors->armed() || !ap.auto_armed || ap.land_complete) {
// To-Do: reset waypoint origin to current location because copter is probably on the ground so we don't want it lurching left or right on take-off make_safe_shut_down();
// (of course it would be better if people just used take-off)
zero_throttle_and_relax_ac();
// clear i term when we're taking off
set_throttle_takeoff();
return; return;
} }
@ -815,12 +807,14 @@ void Copter::ModeAuto::spline_run()
// called by auto_run at 100hz or more // called by auto_run at 100hz or more
void Copter::ModeAuto::land_run() void Copter::ModeAuto::land_run()
{ {
// if not auto armed or landed or motor interlock not enabled set throttle to zero and exit immediately // disarm when the landing detector says we've landed
if (!motors->armed() || !ap.auto_armed || ap.land_complete || !motors->get_interlock()) { if (ap.land_complete) {
zero_throttle_and_relax_ac(); copter.init_disarm_motors();
// set target to current position }
loiter_nav->clear_pilot_desired_acceleration();
loiter_nav->init_target(); // if not armed set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || ap.land_complete) {
make_safe_shut_down();
return; return;
} }
@ -872,9 +866,9 @@ void Copter::ModeAuto::nav_guided_run()
// called by auto_run at 100hz or more // called by auto_run at 100hz or more
void Copter::ModeAuto::loiter_run() void Copter::ModeAuto::loiter_run()
{ {
// if not auto armed or motor interlock not enabled set throttle to zero and exit immediately // if not armed set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || ap.land_complete || !motors->get_interlock()) { if (!motors->armed() || !ap.auto_armed || ap.land_complete) {
zero_throttle_and_relax_ac(); make_safe_shut_down();
return; return;
} }
@ -1515,7 +1509,7 @@ bool Copter::ModeAuto::verify_land()
case LandStateType_Descending: case LandStateType_Descending:
// rely on THROTTLE_LAND mode to correctly update landing status // rely on THROTTLE_LAND mode to correctly update landing status
retval = ap.land_complete; retval = ap.land_complete && (motors->get_spool_mode() == AP_Motors::GROUND_IDLE);
break; break;
default: default:

19
ArduCopter/mode_brake.cpp
View File

@ -31,27 +31,20 @@ bool Copter::ModeBrake::init(bool ignore_checks)
// should be called at 100hz or more // should be called at 100hz or more
void Copter::ModeBrake::run() void Copter::ModeBrake::run()
{ {
// if not auto armed set throttle to zero and exit immediately // if not armed set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || !motors->get_interlock()) { if (!motors->armed() || !ap.auto_armed || ap.land_complete) {
wp_nav->init_brake_target(BRAKE_MODE_DECEL_RATE); make_safe_shut_down();
zero_throttle_and_relax_ac();
pos_control->relax_alt_hold_controllers(0.0f);
return; return;
} }
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// relax stop target if we might be landed // relax stop target if we might be landed
if (ap.land_complete_maybe) { if (ap.land_complete_maybe) {
loiter_nav->soften_for_landing(); loiter_nav->soften_for_landing();
} }
// if landed immediately disarm
if (ap.land_complete) {
copter.init_disarm_motors();
}
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// run brake controller // run brake controller
wp_nav->update_brake(); wp_nav->update_brake();

46
ArduCopter/mode_circle.cpp
View File

@ -27,41 +27,30 @@ bool Copter::ModeCircle::init(bool ignore_checks)
// should be called at 100hz or more // should be called at 100hz or more
void Copter::ModeCircle::run() void Copter::ModeCircle::run()
{ {
float target_yaw_rate = 0;
float target_climb_rate = 0;
// initialize speeds and accelerations // initialize speeds and accelerations
pos_control->set_max_speed_xy(wp_nav->get_default_speed_xy()); pos_control->set_max_speed_xy(wp_nav->get_default_speed_xy());
pos_control->set_max_accel_xy(wp_nav->get_wp_acceleration()); pos_control->set_max_accel_xy(wp_nav->get_wp_acceleration());
pos_control->set_max_speed_z(-get_pilot_speed_dn(), g.pilot_speed_up); pos_control->set_max_speed_z(-get_pilot_speed_dn(), g.pilot_speed_up);
pos_control->set_max_accel_z(g.pilot_accel_z); pos_control->set_max_accel_z(g.pilot_accel_z);
// if not auto armed or motor interlock not enabled set throttle to zero and exit immediately // get pilot's desired yaw rate (or zero if in radio failsafe)
if (!motors->armed() || !ap.auto_armed || ap.land_complete || !motors->get_interlock()) { float target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->get_control_in());
// To-Do: add some initialisation of position controllers if (!is_zero(target_yaw_rate)) {
zero_throttle_and_relax_ac(); pilot_yaw_override = true;
pos_control->set_alt_target_to_current_alt();
return;
} }
// process pilot inputs // get pilot desired climb rate (or zero if in radio failsafe)
if (!copter.failsafe.radio) { float target_climb_rate = get_pilot_desired_climb_rate(channel_throttle->get_control_in());
// get pilot's desired yaw rate // adjust climb rate using rangefinder
target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->get_control_in()); if (copter.rangefinder_alt_ok()) {
if (!is_zero(target_yaw_rate)) { // if rangefinder is ok, use surface tracking
pilot_yaw_override = true; target_climb_rate = get_surface_tracking_climb_rate(target_climb_rate, pos_control->get_alt_target(), G_Dt);
} }
// get pilot desired climb rate // if not armed set throttle to zero and exit immediately
target_climb_rate = get_pilot_desired_climb_rate(channel_throttle->get_control_in()); if (!motors->armed() || !ap.auto_armed || ap.land_complete) {
make_safe_shut_down();
// check for pilot requested take-off return;
if (ap.land_complete && target_climb_rate > 0) {
// indicate we are taking off
set_land_complete(false);
// clear i term when we're taking off
set_throttle_takeoff();
}
} }
// set motors to full range // set motors to full range
@ -81,9 +70,6 @@ void Copter::ModeCircle::run()
copter.circle_nav->get_yaw(), true); copter.circle_nav->get_yaw(), true);
} }
// adjust climb rate using rangefinder
target_climb_rate = get_surface_tracking_climb_rate(target_climb_rate, pos_control->get_alt_target(), G_Dt);
// update altitude target and call position controller // update altitude target and call position controller
// protects heli's from inflight motor interlock disable // protects heli's from inflight motor interlock disable
if (motors->get_desired_spool_state() == AP_Motors::DESIRED_GROUND_IDLE && !ap.land_complete) { if (motors->get_desired_spool_state() == AP_Motors::DESIRED_GROUND_IDLE && !ap.land_complete) {

42
ArduCopter/mode_drift.cpp
View File

@ -40,21 +40,9 @@ void Copter::ModeDrift::run()
{ {
static float braker = 0.0f; static float braker = 0.0f;
static float roll_input = 0.0f; static float roll_input = 0.0f;
float target_roll, target_pitch;
float target_yaw_rate;
// if landed and throttle at zero, set throttle to zero and exit immediately
if (!motors->armed() || !motors->get_interlock() || (ap.land_complete && ap.throttle_zero)) {
zero_throttle_and_relax_ac(copter.is_tradheli() && motors->get_interlock());
return;
}
// clear landing flag above zero throttle
if (!ap.throttle_zero) {
set_land_complete(false);
}
// convert pilot input to lean angles // convert pilot input to lean angles
float target_roll, target_pitch;
get_pilot_desired_lean_angles(target_roll, target_pitch, copter.aparm.angle_max, copter.aparm.angle_max); get_pilot_desired_lean_angles(target_roll, target_pitch, copter.aparm.angle_max, copter.aparm.angle_max);
// Grab inertial velocity // Grab inertial velocity
@ -66,7 +54,7 @@ void Copter::ModeDrift::run()
// gain sceduling for Yaw // gain sceduling for Yaw
float pitch_vel2 = MIN(fabsf(pitch_vel), 2000); float pitch_vel2 = MIN(fabsf(pitch_vel), 2000);
target_yaw_rate = ((float)target_roll/1.0f) * (1.0f - (pitch_vel2 / 5000.0f)) * g.acro_yaw_p; float target_yaw_rate = ((float)target_roll/1.0f) * (1.0f - (pitch_vel2 / 5000.0f)) * g.acro_yaw_p;
roll_vel = constrain_float(roll_vel, -DRIFT_SPEEDLIMIT, DRIFT_SPEEDLIMIT); roll_vel = constrain_float(roll_vel, -DRIFT_SPEEDLIMIT, DRIFT_SPEEDLIMIT);
pitch_vel = constrain_float(pitch_vel, -DRIFT_SPEEDLIMIT, DRIFT_SPEEDLIMIT); pitch_vel = constrain_float(pitch_vel, -DRIFT_SPEEDLIMIT, DRIFT_SPEEDLIMIT);
@ -90,8 +78,30 @@ void Copter::ModeDrift::run()
braker = 0.0f; braker = 0.0f;
} }
// set motors to full range if (!motors->armed()) {
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED); // Motors should be Stopped
motors->set_desired_spool_state(AP_Motors::DESIRED_SHUT_DOWN);
} else if (ap.throttle_zero) {
// Attempting to Land
motors->set_desired_spool_state(AP_Motors::DESIRED_GROUND_IDLE);
} else {
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
}
if (motors->get_spool_mode() == AP_Motors::SHUT_DOWN) {
// Motors Stopped
attitude_control->set_yaw_target_to_current_heading();
attitude_control->reset_rate_controller_I_terms();
} else if (motors->get_spool_mode() == AP_Motors::GROUND_IDLE) {
// Landed
attitude_control->set_yaw_target_to_current_heading();
attitude_control->reset_rate_controller_I_terms();
} else if (motors->get_spool_mode() == AP_Motors::THROTTLE_UNLIMITED) {
// clear landing flag above zero throttle
if (!motors->limit.throttle_lower) {
set_land_complete(false);
}
}
// call attitude controller // call attitude controller
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(target_roll, target_pitch, target_yaw_rate); attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(target_roll, target_pitch, target_yaw_rate);

6
ArduCopter/mode_flip.cpp
View File

@ -102,6 +102,9 @@ void Copter::ModeFlip::run()
// get pilot's desired throttle // get pilot's desired throttle
float throttle_out = get_pilot_desired_throttle(); float throttle_out = get_pilot_desired_throttle();
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// get corrected angle based on direction and axis of rotation // get corrected angle based on direction and axis of rotation
// we flip the sign of flip_angle to minimize the code repetition // we flip the sign of flip_angle to minimize the code repetition
int32_t flip_angle; int32_t flip_angle;
@ -209,9 +212,6 @@ void Copter::ModeFlip::run()
break; break;
} }
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// output pilot's throttle without angle boost // output pilot's throttle without angle boost
attitude_control->set_throttle_out(throttle_out, false, g.throttle_filt); attitude_control->set_throttle_out(throttle_out, false, g.throttle_filt);
} }

120
ArduCopter/mode_flowhold.cpp
View File

@ -217,7 +217,6 @@ void Copter::ModeFlowHold::flowhold_flow_to_angle(Vector2f &bf_angles, bool stic
// should be called at 100hz or more // should be called at 100hz or more
void Copter::ModeFlowHold::run() void Copter::ModeFlowHold::run()
{ {
FlowHoldModeState flowhold_state;
float takeoff_climb_rate = 0.0f; float takeoff_climb_rate = 0.0f;
update_height_estimate(); update_height_estimate();
@ -241,15 +240,8 @@ void Copter::ModeFlowHold::run()
// get pilot's desired yaw rate // get pilot's desired yaw rate
float target_yaw_rate = copter.get_pilot_desired_yaw_rate(copter.channel_yaw->get_control_in()); float target_yaw_rate = copter.get_pilot_desired_yaw_rate(copter.channel_yaw->get_control_in());
if (!copter.motors->armed() || !copter.motors->get_interlock()) { // Flow Hold State Machine Determination
flowhold_state = FlowHold_MotorStopped; AltHoldModeState flowhold_state = get_alt_hold_state(target_climb_rate);
} else if (takeoff.running() || takeoff.triggered(target_climb_rate)) {
flowhold_state = FlowHold_Takeoff;
} else if (!copter.ap.auto_armed || copter.ap.land_complete) {
flowhold_state = FlowHold_Landed;
} else {
flowhold_state = FlowHold_Flying;
}
if (copter.optflow.healthy()) { if (copter.optflow.healthy()) {
const float filter_constant = 0.95; const float filter_constant = 0.95;
@ -258,47 +250,19 @@ void Copter::ModeFlowHold::run()
quality_filtered = 0; quality_filtered = 0;
} }
Vector2f bf_angles;
// calculate alt-hold angles
int16_t roll_in = copter.channel_roll->get_control_in();
int16_t pitch_in = copter.channel_pitch->get_control_in();
float angle_max = copter.attitude_control->get_althold_lean_angle_max();
get_pilot_desired_lean_angles(bf_angles.x, bf_angles.y,angle_max, attitude_control->get_althold_lean_angle_max());
if (quality_filtered >= flow_min_quality &&
AP_HAL::millis() - copter.arm_time_ms > 3000) {
// don't use for first 3s when we are just taking off
Vector2f flow_angles;
flowhold_flow_to_angle(flow_angles, (roll_in != 0) || (pitch_in != 0));
flow_angles.x = constrain_float(flow_angles.x, -angle_max/2, angle_max/2);
flow_angles.y = constrain_float(flow_angles.y, -angle_max/2, angle_max/2);
bf_angles += flow_angles;
}
bf_angles.x = constrain_float(bf_angles.x, -angle_max, angle_max);
bf_angles.y = constrain_float(bf_angles.y, -angle_max, angle_max);
// Flow Hold State Machine // Flow Hold State Machine
switch (flowhold_state) { switch (flowhold_state) {
case FlowHold_MotorStopped: case AltHold_MotorStopped:
copter.motors->set_desired_spool_state(AP_Motors::DESIRED_SHUT_DOWN); copter.motors->set_desired_spool_state(AP_Motors::DESIRED_SHUT_DOWN);
copter.attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(bf_angles.x, bf_angles.y, target_yaw_rate);
#if FRAME_CONFIG == HELI_FRAME
// force descent rate and call position controller
copter.pos_control->set_alt_target_from_climb_rate(-abs(copter.g.land_speed), copter.G_Dt, false);
#else
copter.attitude_control->reset_rate_controller_I_terms(); copter.attitude_control->reset_rate_controller_I_terms();
copter.attitude_control->set_yaw_target_to_current_heading(); copter.attitude_control->set_yaw_target_to_current_heading();
copter.pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero copter.pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
#endif
flow_pi_xy.reset_I(); flow_pi_xy.reset_I();
copter.pos_control->update_z_controller();
break; break;
case FlowHold_Takeoff: case AltHold_Takeoff:
// set motors to full range // set motors to full range
copter.motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED); copter.motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
@ -317,56 +281,66 @@ void Copter::ModeFlowHold::run()
// get avoidance adjusted climb rate // get avoidance adjusted climb rate
target_climb_rate = copter.get_avoidance_adjusted_climbrate(target_climb_rate); target_climb_rate = copter.get_avoidance_adjusted_climbrate(target_climb_rate);
// call attitude controller
copter.attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(bf_angles.x, bf_angles.y, target_yaw_rate);
// call position controller // call position controller
copter.pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, copter.G_Dt, false); copter.pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, copter.G_Dt, false);
copter.pos_control->add_takeoff_climb_rate(takeoff_climb_rate, copter.G_Dt); copter.pos_control->add_takeoff_climb_rate(takeoff_climb_rate, copter.G_Dt);
copter.pos_control->update_z_controller();
break; break;
case FlowHold_Landed: case AltHold_Landed_Ground_Idle:
#if FRAME_CONFIG == HELI_FRAME attitude_control->reset_rate_controller_I_terms();
// helicopters do not spool down when landed. Only when commanded to go to ground idle by pilot. attitude_control->set_yaw_target_to_current_heading();
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED); // FALLTHROUGH
#else
// set motors to spin-when-armed if throttle below deadzone, otherwise full range (but motors will only spin at min throttle) case AltHold_Landed_Pre_Takeoff:
if (target_climb_rate < 0.0f) {
copter.motors->set_desired_spool_state(AP_Motors::DESIRED_GROUND_IDLE); pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
} else {
copter.motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
}
#endif
copter.attitude_control->reset_rate_controller_I_terms();
copter.attitude_control->set_yaw_target_to_current_heading();
copter.attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(bf_angles.x, bf_angles.y, target_yaw_rate);
copter.pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
copter.pos_control->update_z_controller();
break; break;
case FlowHold_Flying: case AltHold_Flying:
copter.motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED); copter.motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
#if AC_AVOID_ENABLED == ENABLED
// apply avoidance
copter.avoid.adjust_roll_pitch(bf_angles.x, bf_angles.y, copter.aparm.angle_max);
#endif
// call attitude controller
copter.attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(bf_angles.x, bf_angles.y, target_yaw_rate);
// adjust climb rate using rangefinder // adjust climb rate using rangefinder
target_climb_rate = copter.get_surface_tracking_climb_rate(target_climb_rate, copter.pos_control->get_alt_target(), copter.G_Dt); target_climb_rate = copter.get_surface_tracking_climb_rate(target_climb_rate, copter.pos_control->get_alt_target(), copter.G_Dt);
// get avoidance adjusted climb rate // get avoidance adjusted climb rate
target_climb_rate = copter.get_avoidance_adjusted_climbrate(target_climb_rate); target_climb_rate = copter.get_avoidance_adjusted_climbrate(target_climb_rate);
// call position controller copter.pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
copter.pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, copter.G_Dt, false);
copter.pos_control->update_z_controller();
break; break;
} }
// flowhold attitude target calculations
Vector2f bf_angles;
// calculate alt-hold angles
int16_t roll_in = copter.channel_roll->get_control_in();
int16_t pitch_in = copter.channel_pitch->get_control_in();
float angle_max = copter.attitude_control->get_althold_lean_angle_max();
get_pilot_desired_lean_angles(bf_angles.x, bf_angles.y, angle_max, attitude_control->get_althold_lean_angle_max());
if (quality_filtered >= flow_min_quality &&
AP_HAL::millis() - copter.arm_time_ms > 3000) {
// don't use for first 3s when we are just taking off
Vector2f flow_angles;
flowhold_flow_to_angle(flow_angles, (roll_in != 0) || (pitch_in != 0));
flow_angles.x = constrain_float(flow_angles.x, -angle_max/2, angle_max/2);
flow_angles.y = constrain_float(flow_angles.y, -angle_max/2, angle_max/2);
bf_angles += flow_angles;
}
bf_angles.x = constrain_float(bf_angles.x, -angle_max, angle_max);
bf_angles.y = constrain_float(bf_angles.y, -angle_max, angle_max);
#if AC_AVOID_ENABLED == ENABLED
// apply avoidance
copter.avoid.adjust_roll_pitch(bf_angles.x, bf_angles.y, copter.aparm.angle_max);
#endif
// call attitude controller
copter.attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(bf_angles.x, bf_angles.y, target_yaw_rate);
// call z-axis position controller
pos_control->update_z_controller();
} }
/* /*

9
ArduCopter/mode_follow.cpp
View File

@ -26,12 +26,15 @@ bool Copter::ModeFollow::init(const bool ignore_checks)
void Copter::ModeFollow::run() void Copter::ModeFollow::run()
{ {
// if not auto armed or motor interlock not enabled set throttle to zero and exit immediately // if not armed set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || !motors->get_interlock()) { if (!motors->armed() || !ap.auto_armed || ap.land_complete) {
zero_throttle_and_relax_ac(); make_safe_shut_down();
return; return;
} }
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// re-use guided mode's velocity controller // re-use guided mode's velocity controller
// Note: this is safe from interference from GCSs and companion computer's whose guided mode // Note: this is safe from interference from GCSs and companion computer's whose guided mode
// position and velocity requests will be ignored while the vehicle is not in guided mode // position and velocity requests will be ignored while the vehicle is not in guided mode

84
ArduCopter/mode_guided.cpp
View File

@ -377,13 +377,9 @@ void Copter::ModeGuided::takeoff_run()
void Copter::Mode::auto_takeoff_run() void Copter::Mode::auto_takeoff_run()
{ {
// if not auto armed or motor interlock not enabled set throttle to zero and exit immediately // if not armed set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || !motors->get_interlock()) { if (!motors->armed() || !ap.auto_armed) {
// initialise wpnav targets make_safe_shut_down();
wp_nav->shift_wp_origin_to_current_pos();
zero_throttle_and_relax_ac();
// clear i term when we're taking off
set_throttle_takeoff();
return; return;
} }
@ -394,17 +390,12 @@ void Copter::Mode::auto_takeoff_run()
target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->get_control_in()); target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->get_control_in());
} }
#if FRAME_CONFIG == HELI_FRAME
// aircraft stays in landed state until rotor speed runup has finished // aircraft stays in landed state until rotor speed runup has finished
if (motors->get_spool_mode() == AP_Motors::THROTTLE_UNLIMITED) { if (motors->get_spool_mode() == AP_Motors::THROTTLE_UNLIMITED) {
set_land_complete(false); set_land_complete(false);
} else { } else {
// initialise wpnav targets
wp_nav->shift_wp_origin_to_current_pos(); wp_nav->shift_wp_origin_to_current_pos();
} }
#else
set_land_complete(false);
#endif
// set motors to full range // set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED); motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
@ -423,12 +414,6 @@ void Copter::Mode::auto_takeoff_run()
// called from guided_run // called from guided_run
void Copter::ModeGuided::pos_control_run() void Copter::ModeGuided::pos_control_run()
{ {
// if not auto armed or motors not enabled set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || !motors->get_interlock() || ap.land_complete) {
zero_throttle_and_relax_ac();
return;
}
// process pilot's yaw input // process pilot's yaw input
float target_yaw_rate = 0; float target_yaw_rate = 0;
if (!copter.failsafe.radio) { if (!copter.failsafe.radio) {
@ -439,6 +424,12 @@ void Copter::ModeGuided::pos_control_run()
} }
} }
// if not armed set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || ap.land_complete) {
make_safe_shut_down();
return;
}
// set motors to full range // set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED); motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
@ -465,14 +456,6 @@ void Copter::ModeGuided::pos_control_run()
// called from guided_run // called from guided_run
void Copter::ModeGuided::vel_control_run() void Copter::ModeGuided::vel_control_run()
{ {
// if not auto armed or motors not enabled set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || !motors->get_interlock() || ap.land_complete) {
// initialise velocity controller
pos_control->init_vel_controller_xyz();
zero_throttle_and_relax_ac();
return;
}
// process pilot's yaw input // process pilot's yaw input
float target_yaw_rate = 0; float target_yaw_rate = 0;
if (!copter.failsafe.radio) { if (!copter.failsafe.radio) {
@ -483,6 +466,12 @@ void Copter::ModeGuided::vel_control_run()
} }
} }
// if not armed set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || ap.land_complete) {
make_safe_shut_down();
return;
}
// set motors to full range // set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED); motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
@ -519,15 +508,6 @@ void Copter::ModeGuided::vel_control_run()
// called from guided_run // called from guided_run
void Copter::ModeGuided::posvel_control_run() void Copter::ModeGuided::posvel_control_run()
{ {
// if not auto armed or motors not enabled set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || !motors->get_interlock() || ap.land_complete) {
// set target position and velocity to current position and velocity
pos_control->set_pos_target(inertial_nav.get_position());
pos_control->set_desired_velocity(Vector3f(0,0,0));
zero_throttle_and_relax_ac();
return;
}
// process pilot's yaw input // process pilot's yaw input
float target_yaw_rate = 0; float target_yaw_rate = 0;
@ -539,6 +519,12 @@ void Copter::ModeGuided::posvel_control_run()
} }
} }
// if not armed set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || ap.land_complete) {
make_safe_shut_down();
return;
}
// set motors to full range // set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED); motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
@ -587,16 +573,6 @@ void Copter::ModeGuided::posvel_control_run()
// called from guided_run // called from guided_run
void Copter::ModeGuided::angle_control_run() void Copter::ModeGuided::angle_control_run()
{ {
// if not auto armed or motors not enabled set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || !motors->get_interlock() || (ap.land_complete && guided_angle_state.climb_rate_cms <= 0.0f)) {
#if FRAME_CONFIG == HELI_FRAME
attitude_control->set_yaw_target_to_current_heading();
#endif
zero_throttle_and_relax_ac();
pos_control->relax_alt_hold_controllers(0.0f);
return;
}
// constrain desired lean angles // constrain desired lean angles
float roll_in = guided_angle_state.roll_cd; float roll_in = guided_angle_state.roll_cd;
float pitch_in = guided_angle_state.pitch_cd; float pitch_in = guided_angle_state.pitch_cd;
@ -627,6 +603,24 @@ void Copter::ModeGuided::angle_control_run()
yaw_rate_in = 0.0f; yaw_rate_in = 0.0f;
} }
// if not armed set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || (ap.land_complete && (guided_angle_state.climb_rate_cms <= 0.0f))) {
make_safe_shut_down();
return;
}
// TODO: use get_alt_hold_state
// landed with positive desired climb rate, takeoff
if (ap.land_complete && (guided_angle_state.climb_rate_cms > 0.0f)) {
zero_throttle_and_relax_ac();
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
if (motors->get_spool_mode() == AP_Motors::THROTTLE_UNLIMITED) {
set_land_complete(false);
set_throttle_takeoff();
}
return;
}
// set motors to full range // set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED); motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);

80
ArduCopter/mode_land.cpp
View File

@ -53,29 +53,26 @@ void Copter::ModeLand::run()
// should be called at 100hz or more // should be called at 100hz or more
void Copter::ModeLand::gps_run() void Copter::ModeLand::gps_run()
{ {
// if not auto armed or landed or motor interlock not enabled set throttle to zero and exit immediately // disarm when the landing detector says we've landed
if (!motors->armed() || !ap.auto_armed || ap.land_complete || !motors->get_interlock()) { if (ap.land_complete) {
zero_throttle_and_relax_ac(); copter.init_disarm_motors();
loiter_nav->clear_pilot_desired_acceleration(); }
loiter_nav->init_target();
// disarm when the landing detector says we've landed // Land State Machine Determination
if (ap.land_complete) { if (!motors->armed() || !ap.auto_armed || ap.land_complete) {
copter.init_disarm_motors(); make_safe_shut_down();
} else {
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// pause before beginning land descent
if(land_pause && millis()-land_start_time >= LAND_WITH_DELAY_MS) {
land_pause = false;
} }
return;
land_run_horizontal_control();
land_run_vertical_control(land_pause);
} }
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// pause before beginning land descent
if (land_pause && millis()-land_start_time >= LAND_WITH_DELAY_MS) {
land_pause = false;
}
land_run_horizontal_control();
land_run_vertical_control(land_pause);
} }
// land_nogps_run - runs the land controller // land_nogps_run - runs the land controller
@ -106,37 +103,28 @@ void Copter::ModeLand::nogps_run()
target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->get_control_in()); target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->get_control_in());
} }
// if not auto armed or landed or motor interlock not enabled set throttle to zero and exit immediately // disarm when the landing detector says we've landed
if (!motors->armed() || !ap.auto_armed || ap.land_complete || !motors->get_interlock()) { if (ap.land_complete) {
#if FRAME_CONFIG == HELI_FRAME // Helicopters always stabilize roll/pitch/yaw copter.init_disarm_motors();
// call attitude controller
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(target_roll, target_pitch, target_yaw_rate);
attitude_control->set_throttle_out(0,false,g.throttle_filt);
#else
motors->set_desired_spool_state(AP_Motors::DESIRED_GROUND_IDLE);
// multicopters do not stabilize roll/pitch/yaw when disarmed
attitude_control->set_throttle_out_unstabilized(0,true,g.throttle_filt);
#endif
// disarm when the landing detector says we've landed
if (ap.land_complete) {
copter.init_disarm_motors();
}
return;
} }
// set motors to full range // Land State Machine Determination
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED); if (!motors->armed() || !ap.auto_armed || ap.land_complete) {
make_safe_shut_down();
} else {
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// pause before beginning land descent
if(land_pause && millis()-land_start_time >= LAND_WITH_DELAY_MS) {
land_pause = false;
}
land_run_vertical_control(land_pause);
}
// call attitude controller // call attitude controller
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(target_roll, target_pitch, target_yaw_rate); attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(target_roll, target_pitch, target_yaw_rate);
// pause before beginning land descent
if (land_pause && millis()-land_start_time >= LAND_WITH_DELAY_MS) {
land_pause = false;
}
land_run_vertical_control(land_pause);
} }
// do_not_use_GPS - forces land-mode to not use the GPS but instead rely on pilot input for roll and pitch // do_not_use_GPS - forces land-mode to not use the GPS but instead rely on pilot input for roll and pitch

57
ArduCopter/mode_loiter.cpp
View File

@ -74,8 +74,6 @@ void Copter::ModeLoiter::precision_loiter_xy()
// should be called at 100hz or more // should be called at 100hz or more
void Copter::ModeLoiter::run() void Copter::ModeLoiter::run()
{ {
LoiterModeState loiter_state;
float target_roll, target_pitch; float target_roll, target_pitch;
float target_yaw_rate = 0.0f; float target_yaw_rate = 0.0f;
float target_climb_rate = 0.0f; float target_climb_rate = 0.0f;
@ -113,42 +111,22 @@ void Copter::ModeLoiter::run()
} }
// Loiter State Machine Determination // Loiter State Machine Determination
if (!motors->armed() || !motors->get_interlock()) { AltHoldModeState loiter_state = get_alt_hold_state(target_climb_rate);
loiter_state = Loiter_MotorStopped;
} else if (takeoff.running() || takeoff.triggered(target_climb_rate)) {
loiter_state = Loiter_Takeoff;
} else if (!ap.auto_armed || ap.land_complete) {
loiter_state = Loiter_Landed;
} else {
loiter_state = Loiter_Flying;
}
// Loiter State Machine // Loiter State Machine
switch (loiter_state) { switch (loiter_state) {
case Loiter_MotorStopped: case AltHold_MotorStopped:
motors->set_desired_spool_state(AP_Motors::DESIRED_SHUT_DOWN);
#if FRAME_CONFIG == HELI_FRAME
// force descent rate and call position controller
pos_control->set_alt_target_from_climb_rate(-abs(g.land_speed), G_Dt, false);
if (ap.land_complete_maybe) {
pos_control->relax_alt_hold_controllers(0.0f);
}
#else
loiter_nav->init_target();
attitude_control->reset_rate_controller_I_terms(); attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading(); attitude_control->set_yaw_target_to_current_heading();
pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
#endif loiter_nav->init_target();
loiter_nav->update(); attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(wp_nav->get_roll(), wp_nav->get_pitch(), target_yaw_rate);
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(loiter_nav->get_roll(), loiter_nav->get_pitch(), target_yaw_rate);
pos_control->update_z_controller(); pos_control->update_z_controller();
break; break;
case Loiter_Takeoff: case AltHold_Takeoff:
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// initiate take-off // initiate take-off
if (!takeoff.running()) { if (!takeoff.running()) {
@ -177,27 +155,21 @@ void Copter::ModeLoiter::run()
pos_control->update_z_controller(); pos_control->update_z_controller();
break; break;
case Loiter_Landed: case AltHold_Landed_Ground_Idle:
#if FRAME_CONFIG == HELI_FRAME
// helicopters do not spool down when landed. Only when commanded to go to ground idle by pilot.
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
#else
// set motors to spin-when-armed if throttle below deadzone, otherwise full range (but motors will only spin at min throttle)
if (target_climb_rate < 0.0f) {
motors->set_desired_spool_state(AP_Motors::DESIRED_GROUND_IDLE);
} else {
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
}
#endif
loiter_nav->init_target();
attitude_control->reset_rate_controller_I_terms(); attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading(); attitude_control->set_yaw_target_to_current_heading();
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(0, 0, 0); // FALLTHROUGH
case AltHold_Landed_Pre_Takeoff:
loiter_nav->init_target();
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(0.0f, 0.0f, 0.0f);
pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
pos_control->update_z_controller(); pos_control->update_z_controller();
break; break;
case Loiter_Flying: case AltHold_Flying:
// set motors to full range // set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED); motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
@ -220,7 +192,6 @@ void Copter::ModeLoiter::run()
// get avoidance adjusted climb rate // get avoidance adjusted climb rate
target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate); target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate);
// update altitude target and call position controller
pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false); pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
pos_control->update_z_controller(); pos_control->update_z_controller();
break; break;

809
ArduCopter/mode_poshold.cpp
View File

@ -23,6 +23,14 @@
#define POSHOLD_STICK_RELEASE_SMOOTH_ANGLE 1800 // max angle required (in centi-degrees) after which the smooth stick release effect is applied #define POSHOLD_STICK_RELEASE_SMOOTH_ANGLE 1800 // max angle required (in centi-degrees) after which the smooth stick release effect is applied
#define POSHOLD_WIND_COMP_ESTIMATE_SPEED_MAX 10 // wind compensation estimates will only run when velocity is at or below this speed in cm/s #define POSHOLD_WIND_COMP_ESTIMATE_SPEED_MAX 10 // wind compensation estimates will only run when velocity is at or below this speed in cm/s
// PosHold states
enum PosHoldModeState {
PosHold_MotorStopped,
PosHold_Takeoff,
PosHold_Flying,
PosHold_Landed
};
// mission state enumeration // mission state enumeration
enum poshold_rp_mode { enum poshold_rp_mode {
POSHOLD_PILOT_OVERRIDE=0, // pilot is controlling this axis (i.e. roll or pitch) POSHOLD_PILOT_OVERRIDE=0, // pilot is controlling this axis (i.e. roll or pitch)
@ -34,8 +42,8 @@ enum poshold_rp_mode {
}; };
static struct { static struct {
poshold_rp_mode roll_mode : 3; // roll mode: pilot override, brake or loiter poshold_rp_mode roll_mode : 3; // roll mode: pilot override, brake or loiter
poshold_rp_mode pitch_mode : 3; // pitch mode: pilot override, brake or loiter poshold_rp_mode pitch_mode : 3; // pitch mode: pilot override, brake or loiter
uint8_t braking_time_updated_roll : 1; // true once we have re-estimated the braking time. This is done once as the vehicle begins to flatten out after braking uint8_t braking_time_updated_roll : 1; // true once we have re-estimated the braking time. This is done once as the vehicle begins to flatten out after braking
uint8_t braking_time_updated_pitch : 1; // true once we have re-estimated the braking time. This is done once as the vehicle begins to flatten out after braking uint8_t braking_time_updated_pitch : 1; // true once we have re-estimated the braking time. This is done once as the vehicle begins to flatten out after braking
@ -95,16 +103,16 @@ bool Copter::ModePosHold::init(bool ignore_checks)
// if landed begin in loiter mode // if landed begin in loiter mode
poshold.roll_mode = POSHOLD_LOITER; poshold.roll_mode = POSHOLD_LOITER;
poshold.pitch_mode = POSHOLD_LOITER; poshold.pitch_mode = POSHOLD_LOITER;
// set target to current position
// only init here as we can switch to PosHold in flight with a velocity <> 0 that will be used as _last_vel in PosControl and never updated again as we inhibit Reset_I
loiter_nav->clear_pilot_desired_acceleration();
loiter_nav->init_target();
}else{ }else{
// if not landed start in pilot override to avoid hard twitch // if not landed start in pilot override to avoid hard twitch
poshold.roll_mode = POSHOLD_PILOT_OVERRIDE; poshold.roll_mode = POSHOLD_PILOT_OVERRIDE;
poshold.pitch_mode = POSHOLD_PILOT_OVERRIDE; poshold.pitch_mode = POSHOLD_PILOT_OVERRIDE;
} }
// initialise loiter
loiter_nav->clear_pilot_desired_acceleration();
loiter_nav->init_target();
// initialise wind_comp each time PosHold is switched on // initialise wind_comp each time PosHold is switched on
poshold.wind_comp_ef.zero(); poshold.wind_comp_ef.zero();
poshold.wind_comp_roll = 0; poshold.wind_comp_roll = 0;
@ -118,14 +126,10 @@ bool Copter::ModePosHold::init(bool ignore_checks)
// should be called at 100hz or more // should be called at 100hz or more
void Copter::ModePosHold::run() void Copter::ModePosHold::run()
{ {
float target_roll, target_pitch; // pilot's roll and pitch angle inputs float takeoff_climb_rate = 0.0f;
float target_yaw_rate = 0; // pilot desired yaw rate in centi-degrees/sec
float target_climb_rate = 0; // pilot desired climb rate in centimeters/sec
float takeoff_climb_rate = 0.0f; // takeoff induced climb rate
float brake_to_loiter_mix; // mix of brake and loiter controls. 0 = fully brake controls, 1 = fully loiter controls float brake_to_loiter_mix; // mix of brake and loiter controls. 0 = fully brake controls, 1 = fully loiter controls
float controller_to_pilot_roll_mix; // mix of controller and pilot controls. 0 = fully last controller controls, 1 = fully pilot controls float controller_to_pilot_roll_mix; // mix of controller and pilot controls. 0 = fully last controller controls, 1 = fully pilot controls
float controller_to_pilot_pitch_mix; // mix of controller and pilot controls. 0 = fully last controller controls, 1 = fully pilot controls float controller_to_pilot_pitch_mix; // mix of controller and pilot controls. 0 = fully last controller controls, 1 = fully pilot controls
float vel_fw, vel_right; // vehicle's current velocity in body-frame forward and right directions
const Vector3f& vel = inertial_nav.get_velocity(); const Vector3f& vel = inertial_nav.get_velocity();
// initialize vertical speeds and acceleration // initialize vertical speeds and acceleration
@ -133,406 +137,437 @@ void Copter::ModePosHold::run()
pos_control->set_max_accel_z(g.pilot_accel_z); pos_control->set_max_accel_z(g.pilot_accel_z);
loiter_nav->clear_pilot_desired_acceleration(); loiter_nav->clear_pilot_desired_acceleration();
// if not auto armed or motor interlock not enabled set throttle to zero and exit immediately // apply SIMPLE mode transform to pilot inputs
if (!motors->armed() || !ap.auto_armed || !motors->get_interlock()) { update_simple_mode();
loiter_nav->init_target();
zero_throttle_and_relax_ac(copter.is_tradheli() && motors->get_interlock());
pos_control->relax_alt_hold_controllers(0.0f);
return;
}
// process pilot inputs // convert pilot input to lean angles
if (!copter.failsafe.radio) { float target_roll, target_pitch;
// apply SIMPLE mode transform to pilot inputs get_pilot_desired_lean_angles(target_roll, target_pitch, copter.aparm.angle_max, attitude_control->get_althold_lean_angle_max());
update_simple_mode();
// get pilot's desired yaw rate // get pilot's desired yaw rate
target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->get_control_in()); float target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->get_control_in());
// get pilot desired climb rate (for alt-hold mode and take-off) // get pilot desired climb rate (for alt-hold mode and take-off)
target_climb_rate = get_pilot_desired_climb_rate(channel_throttle->get_control_in()); float target_climb_rate = get_pilot_desired_climb_rate(channel_throttle->get_control_in());
target_climb_rate = constrain_float(target_climb_rate, -get_pilot_speed_dn(), g.pilot_speed_up); target_climb_rate = constrain_float(target_climb_rate, -get_pilot_speed_dn(), g.pilot_speed_up);
// get takeoff adjusted pilot and takeoff climb rates
takeoff.get_climb_rates(target_climb_rate, takeoff_climb_rate);
// check for take-off
#if FRAME_CONFIG == HELI_FRAME
// helicopters are held on the ground until rotor speed runup has finished
if (ap.land_complete && (takeoff.running() || (target_climb_rate > 0.0f && motors->rotor_runup_complete()))) {
#else
if (ap.land_complete && (takeoff.running() || target_climb_rate > 0.0f)) {
#endif
if (!takeoff.running()) {
takeoff.start(constrain_float(g.pilot_takeoff_alt,0.0f,1000.0f));
}
// indicate we are taking off
set_land_complete(false);
// clear i term when we're taking off
set_throttle_takeoff();
}
}
// relax loiter target if we might be landed // relax loiter target if we might be landed
if (ap.land_complete_maybe) { if (ap.land_complete_maybe) {
loiter_nav->soften_for_landing(); loiter_nav->soften_for_landing();
} }
// if landed initialise loiter targets, set throttle to zero and exit // Pos Hold State Machine Determination
if (ap.land_complete) { AltHoldModeState poshold_state = get_alt_hold_state(target_climb_rate);
#if FRAME_CONFIG == HELI_FRAME
// helicopters do not spool down when landed. Only when commanded to go to ground idle by pilot. // state machine
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED); switch (poshold_state) {
#else
// set motors to spin-when-armed if throttle below deadzone, otherwise full range (but motors will only spin at min throttle) case AltHold_MotorStopped:
if (target_climb_rate < 0.0f) {
motors->set_desired_spool_state(AP_Motors::DESIRED_GROUND_IDLE);
} else {
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
}
#endif
loiter_nav->init_target();
attitude_control->reset_rate_controller_I_terms(); attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading(); attitude_control->set_yaw_target_to_current_heading();
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(0, 0, 0);
pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
pos_control->update_z_controller(); loiter_nav->init_target();
return; loiter_nav->update();
}else{
// convert pilot input to lean angles
get_pilot_desired_lean_angles(target_roll, target_pitch, copter.aparm.angle_max, attitude_control->get_althold_lean_angle_max());
// convert inertial nav earth-frame velocities to body-frame // set poshold state to pilot override
// To-Do: move this to AP_Math (or perhaps we already have a function to do this) poshold.roll_mode = POSHOLD_PILOT_OVERRIDE;
vel_fw = vel.x*ahrs.cos_yaw() + vel.y*ahrs.sin_yaw(); poshold.pitch_mode = POSHOLD_PILOT_OVERRIDE;
vel_right = -vel.x*ahrs.sin_yaw() + vel.y*ahrs.cos_yaw(); break;
// If not in LOITER, retrieve latest wind compensation lean angles related to current yaw
if (poshold.roll_mode != POSHOLD_LOITER || poshold.pitch_mode != POSHOLD_LOITER)
poshold_get_wind_comp_lean_angles(poshold.wind_comp_roll, poshold.wind_comp_pitch);
// Roll state machine case AltHold_Takeoff:
// Each state (aka mode) is responsible for:
// 1. dealing with pilot input
// 2. calculating the final roll output to the attitude controller
// 3. checking if the state (aka mode) should be changed and if 'yes' perform any required initialisation for the new state
switch (poshold.roll_mode) {
case POSHOLD_PILOT_OVERRIDE: // initiate take-off
// update pilot desired roll angle using latest radio input if (!takeoff.running()) {
// this filters the input so that it returns to zero no faster than the brake-rate takeoff.start(constrain_float(g.pilot_takeoff_alt,0.0f,1000.0f));
poshold_update_pilot_lean_angle(poshold.pilot_roll, target_roll); // indicate we are taking off
set_land_complete(false);
// switch to BRAKE mode for next iteration if no pilot input // clear i terms
if (is_zero(target_roll) && (fabsf(poshold.pilot_roll) < 2 * g.poshold_brake_rate)) { set_throttle_takeoff();
// initialise BRAKE mode
poshold.roll_mode = POSHOLD_BRAKE; // Set brake roll mode
poshold.brake_roll = 0; // initialise braking angle to zero
poshold.brake_angle_max_roll = 0; // reset brake_angle_max so we can detect when vehicle begins to flatten out during braking
poshold.brake_timeout_roll = POSHOLD_BRAKE_TIME_ESTIMATE_MAX; // number of cycles the brake will be applied, updated during braking mode.
poshold.braking_time_updated_roll = false; // flag the braking time can be re-estimated
}
// final lean angle should be pilot input plus wind compensation
poshold.roll = poshold.pilot_roll + poshold.wind_comp_roll;
break;
case POSHOLD_BRAKE:
case POSHOLD_BRAKE_READY_TO_LOITER:
// calculate brake_roll angle to counter-act velocity
poshold_update_brake_angle_from_velocity(poshold.brake_roll, vel_right);
// update braking time estimate
if (!poshold.braking_time_updated_roll) {
// check if brake angle is increasing
if (abs(poshold.brake_roll) >= poshold.brake_angle_max_roll) {
poshold.brake_angle_max_roll = abs(poshold.brake_roll);
} else {
// braking angle has started decreasing so re-estimate braking time
poshold.brake_timeout_roll = 1+(uint16_t)(LOOP_RATE_FACTOR*15L*(int32_t)(abs(poshold.brake_roll))/(10L*(int32_t)g.poshold_brake_rate)); // the 1.2 (12/10) factor has to be tuned in flight, here it means 120% of the "normal" time.
poshold.braking_time_updated_roll = true;
}
}
// if velocity is very low reduce braking time to 0.5seconds
if ((fabsf(vel_right) <= POSHOLD_SPEED_0) && (poshold.brake_timeout_roll > 50*LOOP_RATE_FACTOR)) {
poshold.brake_timeout_roll = 50*LOOP_RATE_FACTOR;
}
// reduce braking timer
if (poshold.brake_timeout_roll > 0) {
poshold.brake_timeout_roll--;
} else {
// indicate that we are ready to move to Loiter.
// Loiter will only actually be engaged once both roll_mode and pitch_mode are changed to POSHOLD_BRAKE_READY_TO_LOITER
// logic for engaging loiter is handled below the roll and pitch mode switch statements
poshold.roll_mode = POSHOLD_BRAKE_READY_TO_LOITER;
}
// final lean angle is braking angle + wind compensation angle
poshold.roll = poshold.brake_roll + poshold.wind_comp_roll;
// check for pilot input
if (!is_zero(target_roll)) {
// init transition to pilot override
poshold_roll_controller_to_pilot_override();
}
break;
case POSHOLD_BRAKE_TO_LOITER:
case POSHOLD_LOITER:
// these modes are combined roll-pitch modes and are handled below
break;
case POSHOLD_CONTROLLER_TO_PILOT_OVERRIDE:
// update pilot desired roll angle using latest radio input
// this filters the input so that it returns to zero no faster than the brake-rate
poshold_update_pilot_lean_angle(poshold.pilot_roll, target_roll);
// count-down loiter to pilot timer
if (poshold.controller_to_pilot_timer_roll > 0) {
poshold.controller_to_pilot_timer_roll--;
} else {
// when timer runs out switch to full pilot override for next iteration
poshold.roll_mode = POSHOLD_PILOT_OVERRIDE;
}
// calculate controller_to_pilot mix ratio
controller_to_pilot_roll_mix = (float)poshold.controller_to_pilot_timer_roll / (float)POSHOLD_CONTROLLER_TO_PILOT_MIX_TIMER;
// mix final loiter lean angle and pilot desired lean angles
poshold.roll = poshold_mix_controls(controller_to_pilot_roll_mix, poshold.controller_final_roll, poshold.pilot_roll + poshold.wind_comp_roll);
break;
} }
// Pitch state machine // get take-off adjusted pilot and takeoff climb rates
// Each state (aka mode) is responsible for: takeoff.get_climb_rates(target_climb_rate, takeoff_climb_rate);
// 1. dealing with pilot input
// 2. calculating the final pitch output to the attitude contpitcher
// 3. checking if the state (aka mode) should be changed and if 'yes' perform any required initialisation for the new state
switch (poshold.pitch_mode) {
case POSHOLD_PILOT_OVERRIDE:
// update pilot desired pitch angle using latest radio input
// this filters the input so that it returns to zero no faster than the brake-rate
poshold_update_pilot_lean_angle(poshold.pilot_pitch, target_pitch);
// switch to BRAKE mode for next iteration if no pilot input
if (is_zero(target_pitch) && (fabsf(poshold.pilot_pitch) < 2 * g.poshold_brake_rate)) {
// initialise BRAKE mode
poshold.pitch_mode = POSHOLD_BRAKE; // set brake pitch mode
poshold.brake_pitch = 0; // initialise braking angle to zero
poshold.brake_angle_max_pitch = 0; // reset brake_angle_max so we can detect when vehicle begins to flatten out during braking
poshold.brake_timeout_pitch = POSHOLD_BRAKE_TIME_ESTIMATE_MAX; // number of cycles the brake will be applied, updated during braking mode.
poshold.braking_time_updated_pitch = false; // flag the braking time can be re-estimated
}
// final lean angle should be pilot input plus wind compensation
poshold.pitch = poshold.pilot_pitch + poshold.wind_comp_pitch;
break;
case POSHOLD_BRAKE:
case POSHOLD_BRAKE_READY_TO_LOITER:
// calculate brake_pitch angle to counter-act velocity
poshold_update_brake_angle_from_velocity(poshold.brake_pitch, -vel_fw);
// update braking time estimate
if (!poshold.braking_time_updated_pitch) {
// check if brake angle is increasing
if (abs(poshold.brake_pitch) >= poshold.brake_angle_max_pitch) {
poshold.brake_angle_max_pitch = abs(poshold.brake_pitch);
} else {
// braking angle has started decreasing so re-estimate braking time
poshold.brake_timeout_pitch = 1+(uint16_t)(LOOP_RATE_FACTOR*15L*(int32_t)(abs(poshold.brake_pitch))/(10L*(int32_t)g.poshold_brake_rate)); // the 1.2 (12/10) factor has to be tuned in flight, here it means 120% of the "normal" time.
poshold.braking_time_updated_pitch = true;
}
}
// if velocity is very low reduce braking time to 0.5seconds
if ((fabsf(vel_fw) <= POSHOLD_SPEED_0) && (poshold.brake_timeout_pitch > 50*LOOP_RATE_FACTOR)) {
poshold.brake_timeout_pitch = 50*LOOP_RATE_FACTOR;
}
// reduce braking timer
if (poshold.brake_timeout_pitch > 0) {
poshold.brake_timeout_pitch--;
} else {
// indicate that we are ready to move to Loiter.
// Loiter will only actually be engaged once both pitch_mode and pitch_mode are changed to POSHOLD_BRAKE_READY_TO_LOITER
// logic for engaging loiter is handled below the pitch and pitch mode switch statements
poshold.pitch_mode = POSHOLD_BRAKE_READY_TO_LOITER;
}
// final lean angle is braking angle + wind compensation angle
poshold.pitch = poshold.brake_pitch + poshold.wind_comp_pitch;
// check for pilot input
if (!is_zero(target_pitch)) {
// init transition to pilot override
poshold_pitch_controller_to_pilot_override();
}
break;
case POSHOLD_BRAKE_TO_LOITER:
case POSHOLD_LOITER:
// these modes are combined pitch-pitch modes and are handled below
break;
case POSHOLD_CONTROLLER_TO_PILOT_OVERRIDE:
// update pilot desired pitch angle using latest radio input
// this filters the input so that it returns to zero no faster than the brake-rate
poshold_update_pilot_lean_angle(poshold.pilot_pitch, target_pitch);
// count-down loiter to pilot timer
if (poshold.controller_to_pilot_timer_pitch > 0) {
poshold.controller_to_pilot_timer_pitch--;
} else {
// when timer runs out switch to full pilot override for next iteration
poshold.pitch_mode = POSHOLD_PILOT_OVERRIDE;
}
// calculate controller_to_pilot mix ratio
controller_to_pilot_pitch_mix = (float)poshold.controller_to_pilot_timer_pitch / (float)POSHOLD_CONTROLLER_TO_PILOT_MIX_TIMER;
// mix final loiter lean angle and pilot desired lean angles
poshold.pitch = poshold_mix_controls(controller_to_pilot_pitch_mix, poshold.controller_final_pitch, poshold.pilot_pitch + poshold.wind_comp_pitch);
break;
}
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
//
// Shared roll & pitch states (POSHOLD_BRAKE_TO_LOITER and POSHOLD_LOITER)
//
// switch into LOITER mode when both roll and pitch are ready
if (poshold.roll_mode == POSHOLD_BRAKE_READY_TO_LOITER && poshold.pitch_mode == POSHOLD_BRAKE_READY_TO_LOITER) {
poshold.roll_mode = POSHOLD_BRAKE_TO_LOITER;
poshold.pitch_mode = POSHOLD_BRAKE_TO_LOITER;
poshold.brake_to_loiter_timer = POSHOLD_BRAKE_TO_LOITER_TIMER;
// init loiter controller
loiter_nav->init_target(inertial_nav.get_position());
// set delay to start of wind compensation estimate updates
poshold.wind_comp_start_timer = POSHOLD_WIND_COMP_START_TIMER;
}
// roll-mode is used as the combined roll+pitch mode when in BRAKE_TO_LOITER or LOITER modes
if (poshold.roll_mode == POSHOLD_BRAKE_TO_LOITER || poshold.roll_mode == POSHOLD_LOITER) {
// force pitch mode to be same as roll_mode just to keep it consistent (it's not actually used in these states)
poshold.pitch_mode = poshold.roll_mode;
// handle combined roll+pitch mode
switch (poshold.roll_mode) {
case POSHOLD_BRAKE_TO_LOITER:
// reduce brake_to_loiter timer
if (poshold.brake_to_loiter_timer > 0) {
poshold.brake_to_loiter_timer--;
} else {
// progress to full loiter on next iteration
poshold.roll_mode = POSHOLD_LOITER;
poshold.pitch_mode = POSHOLD_LOITER;
}
// calculate percentage mix of loiter and brake control
brake_to_loiter_mix = (float)poshold.brake_to_loiter_timer / (float)POSHOLD_BRAKE_TO_LOITER_TIMER;
// calculate brake_roll and pitch angles to counter-act velocity
poshold_update_brake_angle_from_velocity(poshold.brake_roll, vel_right);
poshold_update_brake_angle_from_velocity(poshold.brake_pitch, -vel_fw);
// run loiter controller
loiter_nav->update();
// calculate final roll and pitch output by mixing loiter and brake controls
poshold.roll = poshold_mix_controls(brake_to_loiter_mix, poshold.brake_roll + poshold.wind_comp_roll, loiter_nav->get_roll());
poshold.pitch = poshold_mix_controls(brake_to_loiter_mix, poshold.brake_pitch + poshold.wind_comp_pitch, loiter_nav->get_pitch());
// check for pilot input
if (!is_zero(target_roll) || !is_zero(target_pitch)) {
// if roll input switch to pilot override for roll
if (!is_zero(target_roll)) {
// init transition to pilot override
poshold_roll_controller_to_pilot_override();
// switch pitch-mode to brake (but ready to go back to loiter anytime)
// no need to reset poshold.brake_pitch here as wind comp has not been updated since last brake_pitch computation
poshold.pitch_mode = POSHOLD_BRAKE_READY_TO_LOITER;
}
// if pitch input switch to pilot override for pitch
if (!is_zero(target_pitch)) {
// init transition to pilot override
poshold_pitch_controller_to_pilot_override();
if (is_zero(target_roll)) {
// switch roll-mode to brake (but ready to go back to loiter anytime)
// no need to reset poshold.brake_roll here as wind comp has not been updated since last brake_roll computation
poshold.roll_mode = POSHOLD_BRAKE_READY_TO_LOITER;
}
}
}
break;
case POSHOLD_LOITER:
// run loiter controller
loiter_nav->update();
// set roll angle based on loiter controller outputs
poshold.roll = loiter_nav->get_roll();
poshold.pitch = loiter_nav->get_pitch();
// update wind compensation estimate
poshold_update_wind_comp_estimate();
// check for pilot input
if (!is_zero(target_roll) || !is_zero(target_pitch)) {
// if roll input switch to pilot override for roll
if (!is_zero(target_roll)) {
// init transition to pilot override
poshold_roll_controller_to_pilot_override();
// switch pitch-mode to brake (but ready to go back to loiter anytime)
poshold.pitch_mode = POSHOLD_BRAKE_READY_TO_LOITER;
// reset brake_pitch because wind_comp is now different and should give the compensation of the whole previous loiter angle
poshold.brake_pitch = 0;
}
// if pitch input switch to pilot override for pitch
if (!is_zero(target_pitch)) {
// init transition to pilot override
poshold_pitch_controller_to_pilot_override();
// if roll not overridden switch roll-mode to brake (but be ready to go back to loiter any time)
if (is_zero(target_roll)) {
poshold.roll_mode = POSHOLD_BRAKE_READY_TO_LOITER;
poshold.brake_roll = 0;
}
}
}
break;
default:
// do nothing for uncombined roll and pitch modes
break;
}
}
// constrain target pitch/roll angles
float angle_max = copter.aparm.angle_max;
poshold.roll = constrain_int16(poshold.roll, -angle_max, angle_max);
poshold.pitch = constrain_int16(poshold.pitch, -angle_max, angle_max);
// update attitude controller targets
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(poshold.roll, poshold.pitch, target_yaw_rate);
// adjust climb rate using rangefinder
target_climb_rate = get_surface_tracking_climb_rate(target_climb_rate, pos_control->get_alt_target(), G_Dt);
// get avoidance adjusted climb rate // get avoidance adjusted climb rate
target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate); target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate);
// update altitude target and call position controller // init and update loiter although pilot is controlling lean angles
loiter_nav->init_target();
loiter_nav->update();
// set position controller targets
pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false); pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
pos_control->add_takeoff_climb_rate(takeoff_climb_rate, G_Dt); pos_control->add_takeoff_climb_rate(takeoff_climb_rate, G_Dt);
pos_control->update_z_controller();
// set poshold state to pilot override
poshold.roll_mode = POSHOLD_PILOT_OVERRIDE;
poshold.pitch_mode = POSHOLD_PILOT_OVERRIDE;
break;
case AltHold_Landed_Ground_Idle:
loiter_nav->init_target();
loiter_nav->update();
attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading();
// FALLTHROUGH
case AltHold_Landed_Pre_Takeoff:
pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
// set poshold state to pilot override
poshold.roll_mode = POSHOLD_PILOT_OVERRIDE;
poshold.pitch_mode = POSHOLD_PILOT_OVERRIDE;
break;
case AltHold_Flying:
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
#if AC_AVOID_ENABLED == ENABLED
// apply avoidance
copter.avoid.adjust_roll_pitch(target_roll, target_pitch, copter.aparm.angle_max);
#endif
// adjust climb rate using rangefinder
if (copter.rangefinder_alt_ok()) {
// if rangefinder is ok, use surface tracking
target_climb_rate = get_surface_tracking_climb_rate(target_climb_rate, pos_control->get_alt_target(), G_Dt);
}
// get avoidance adjusted climb rate
target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate);
pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
break;
} }
// poshold specific behaviour to calculate desired roll, pitch angles
// convert inertial nav earth-frame velocities to body-frame
// To-Do: move this to AP_Math (or perhaps we already have a function to do this)
float vel_fw = vel.x*ahrs.cos_yaw() + vel.y*ahrs.sin_yaw();
float vel_right = -vel.x*ahrs.sin_yaw() + vel.y*ahrs.cos_yaw();
// If not in LOITER, retrieve latest wind compensation lean angles related to current yaw
if (poshold.roll_mode != POSHOLD_LOITER || poshold.pitch_mode != POSHOLD_LOITER) {
poshold_get_wind_comp_lean_angles(poshold.wind_comp_roll, poshold.wind_comp_pitch);
}
// Roll state machine
// Each state (aka mode) is responsible for:
// 1. dealing with pilot input
// 2. calculating the final roll output to the attitude controller
// 3. checking if the state (aka mode) should be changed and if 'yes' perform any required initialisation for the new state
switch (poshold.roll_mode) {
case POSHOLD_PILOT_OVERRIDE:
// update pilot desired roll angle using latest radio input
// this filters the input so that it returns to zero no faster than the brake-rate
poshold_update_pilot_lean_angle(poshold.pilot_roll, target_roll);
// switch to BRAKE mode for next iteration if no pilot input
if (is_zero(target_roll) && (fabsf(poshold.pilot_roll) < 2 * g.poshold_brake_rate)) {
// initialise BRAKE mode
poshold.roll_mode = POSHOLD_BRAKE; // Set brake roll mode
poshold.brake_roll = 0; // initialise braking angle to zero
poshold.brake_angle_max_roll = 0; // reset brake_angle_max so we can detect when vehicle begins to flatten out during braking
poshold.brake_timeout_roll = POSHOLD_BRAKE_TIME_ESTIMATE_MAX; // number of cycles the brake will be applied, updated during braking mode.
poshold.braking_time_updated_roll = false; // flag the braking time can be re-estimated
}
// final lean angle should be pilot input plus wind compensation
poshold.roll = poshold.pilot_roll + poshold.wind_comp_roll;
break;
case POSHOLD_BRAKE:
case POSHOLD_BRAKE_READY_TO_LOITER:
// calculate brake_roll angle to counter-act velocity
poshold_update_brake_angle_from_velocity(poshold.brake_roll, vel_right);
// update braking time estimate
if (!poshold.braking_time_updated_roll) {
// check if brake angle is increasing
if (abs(poshold.brake_roll) >= poshold.brake_angle_max_roll) {
poshold.brake_angle_max_roll = abs(poshold.brake_roll);
} else {
// braking angle has started decreasing so re-estimate braking time
poshold.brake_timeout_roll = 1+(uint16_t)(LOOP_RATE_FACTOR*15L*(int32_t)(abs(poshold.brake_roll))/(10L*(int32_t)g.poshold_brake_rate)); // the 1.2 (12/10) factor has to be tuned in flight, here it means 120% of the "normal" time.
poshold.braking_time_updated_roll = true;
}
}
// if velocity is very low reduce braking time to 0.5seconds
if ((fabsf(vel_right) <= POSHOLD_SPEED_0) && (poshold.brake_timeout_roll > 50*LOOP_RATE_FACTOR)) {
poshold.brake_timeout_roll = 50*LOOP_RATE_FACTOR;
}
// reduce braking timer
if (poshold.brake_timeout_roll > 0) {
poshold.brake_timeout_roll--;
} else {
// indicate that we are ready to move to Loiter.
// Loiter will only actually be engaged once both roll_mode and pitch_mode are changed to POSHOLD_BRAKE_READY_TO_LOITER
// logic for engaging loiter is handled below the roll and pitch mode switch statements
poshold.roll_mode = POSHOLD_BRAKE_READY_TO_LOITER;
}
// final lean angle is braking angle + wind compensation angle
poshold.roll = poshold.brake_roll + poshold.wind_comp_roll;
// check for pilot input
if (!is_zero(target_roll)) {
// init transition to pilot override
poshold_roll_controller_to_pilot_override();
}
break;
case POSHOLD_BRAKE_TO_LOITER:
case POSHOLD_LOITER:
// these modes are combined roll-pitch modes and are handled below
break;
case POSHOLD_CONTROLLER_TO_PILOT_OVERRIDE:
// update pilot desired roll angle using latest radio input
// this filters the input so that it returns to zero no faster than the brake-rate
poshold_update_pilot_lean_angle(poshold.pilot_roll, target_roll);
// count-down loiter to pilot timer
if (poshold.controller_to_pilot_timer_roll > 0) {
poshold.controller_to_pilot_timer_roll--;
} else {
// when timer runs out switch to full pilot override for next iteration
poshold.roll_mode = POSHOLD_PILOT_OVERRIDE;
}
// calculate controller_to_pilot mix ratio
controller_to_pilot_roll_mix = (float)poshold.controller_to_pilot_timer_roll / (float)POSHOLD_CONTROLLER_TO_PILOT_MIX_TIMER;
// mix final loiter lean angle and pilot desired lean angles
poshold.roll = poshold_mix_controls(controller_to_pilot_roll_mix, poshold.controller_final_roll, poshold.pilot_roll + poshold.wind_comp_roll);
break;
}
// Pitch state machine
// Each state (aka mode) is responsible for:
// 1. dealing with pilot input
// 2. calculating the final pitch output to the attitude contpitcher
// 3. checking if the state (aka mode) should be changed and if 'yes' perform any required initialisation for the new state
switch (poshold.pitch_mode) {
case POSHOLD_PILOT_OVERRIDE:
// update pilot desired pitch angle using latest radio input
// this filters the input so that it returns to zero no faster than the brake-rate
poshold_update_pilot_lean_angle(poshold.pilot_pitch, target_pitch);
// switch to BRAKE mode for next iteration if no pilot input
if (is_zero(target_pitch) && (fabsf(poshold.pilot_pitch) < 2 * g.poshold_brake_rate)) {
// initialise BRAKE mode
poshold.pitch_mode = POSHOLD_BRAKE; // set brake pitch mode
poshold.brake_pitch = 0; // initialise braking angle to zero
poshold.brake_angle_max_pitch = 0; // reset brake_angle_max so we can detect when vehicle begins to flatten out during braking
poshold.brake_timeout_pitch = POSHOLD_BRAKE_TIME_ESTIMATE_MAX; // number of cycles the brake will be applied, updated during braking mode.
poshold.braking_time_updated_pitch = false; // flag the braking time can be re-estimated
}
// final lean angle should be pilot input plus wind compensation
poshold.pitch = poshold.pilot_pitch + poshold.wind_comp_pitch;
break;
case POSHOLD_BRAKE:
case POSHOLD_BRAKE_READY_TO_LOITER:
// calculate brake_pitch angle to counter-act velocity
poshold_update_brake_angle_from_velocity(poshold.brake_pitch, -vel_fw);
// update braking time estimate
if (!poshold.braking_time_updated_pitch) {
// check if brake angle is increasing
if (abs(poshold.brake_pitch) >= poshold.brake_angle_max_pitch) {
poshold.brake_angle_max_pitch = abs(poshold.brake_pitch);
} else {
// braking angle has started decreasing so re-estimate braking time
poshold.brake_timeout_pitch = 1+(uint16_t)(LOOP_RATE_FACTOR*15L*(int32_t)(abs(poshold.brake_pitch))/(10L*(int32_t)g.poshold_brake_rate)); // the 1.2 (12/10) factor has to be tuned in flight, here it means 120% of the "normal" time.
poshold.braking_time_updated_pitch = true;
}
}
// if velocity is very low reduce braking time to 0.5seconds
if ((fabsf(vel_fw) <= POSHOLD_SPEED_0) && (poshold.brake_timeout_pitch > 50*LOOP_RATE_FACTOR)) {
poshold.brake_timeout_pitch = 50*LOOP_RATE_FACTOR;
}
// reduce braking timer
if (poshold.brake_timeout_pitch > 0) {
poshold.brake_timeout_pitch--;
} else {
// indicate that we are ready to move to Loiter.
// Loiter will only actually be engaged once both pitch_mode and pitch_mode are changed to POSHOLD_BRAKE_READY_TO_LOITER
// logic for engaging loiter is handled below the pitch and pitch mode switch statements
poshold.pitch_mode = POSHOLD_BRAKE_READY_TO_LOITER;
}
// final lean angle is braking angle + wind compensation angle
poshold.pitch = poshold.brake_pitch + poshold.wind_comp_pitch;
// check for pilot input
if (!is_zero(target_pitch)) {
// init transition to pilot override
poshold_pitch_controller_to_pilot_override();
}
break;
case POSHOLD_BRAKE_TO_LOITER:
case POSHOLD_LOITER:
// these modes are combined pitch-pitch modes and are handled below
break;
case POSHOLD_CONTROLLER_TO_PILOT_OVERRIDE:
// update pilot desired pitch angle using latest radio input
// this filters the input so that it returns to zero no faster than the brake-rate
poshold_update_pilot_lean_angle(poshold.pilot_pitch, target_pitch);
// count-down loiter to pilot timer
if (poshold.controller_to_pilot_timer_pitch > 0) {
poshold.controller_to_pilot_timer_pitch--;
} else {
// when timer runs out switch to full pilot override for next iteration
poshold.pitch_mode = POSHOLD_PILOT_OVERRIDE;
}
// calculate controller_to_pilot mix ratio
controller_to_pilot_pitch_mix = (float)poshold.controller_to_pilot_timer_pitch / (float)POSHOLD_CONTROLLER_TO_PILOT_MIX_TIMER;
// mix final loiter lean angle and pilot desired lean angles
poshold.pitch = poshold_mix_controls(controller_to_pilot_pitch_mix, poshold.controller_final_pitch, poshold.pilot_pitch + poshold.wind_comp_pitch);
break;
}
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
//
// Shared roll & pitch states (POSHOLD_BRAKE_TO_LOITER and POSHOLD_LOITER)
//
// switch into LOITER mode when both roll and pitch are ready
if (poshold.roll_mode == POSHOLD_BRAKE_READY_TO_LOITER && poshold.pitch_mode == POSHOLD_BRAKE_READY_TO_LOITER) {
poshold.roll_mode = POSHOLD_BRAKE_TO_LOITER;
poshold.pitch_mode = POSHOLD_BRAKE_TO_LOITER;
poshold.brake_to_loiter_timer = POSHOLD_BRAKE_TO_LOITER_TIMER;
// init loiter controller
loiter_nav->init_target(inertial_nav.get_position());
// set delay to start of wind compensation estimate updates
poshold.wind_comp_start_timer = POSHOLD_WIND_COMP_START_TIMER;
}
// roll-mode is used as the combined roll+pitch mode when in BRAKE_TO_LOITER or LOITER modes
if (poshold.roll_mode == POSHOLD_BRAKE_TO_LOITER || poshold.roll_mode == POSHOLD_LOITER) {
// force pitch mode to be same as roll_mode just to keep it consistent (it's not actually used in these states)
poshold.pitch_mode = poshold.roll_mode;
// handle combined roll+pitch mode
switch (poshold.roll_mode) {
case POSHOLD_BRAKE_TO_LOITER:
// reduce brake_to_loiter timer
if (poshold.brake_to_loiter_timer > 0) {
poshold.brake_to_loiter_timer--;
} else {
// progress to full loiter on next iteration
poshold.roll_mode = POSHOLD_LOITER;
poshold.pitch_mode = POSHOLD_LOITER;
}
// calculate percentage mix of loiter and brake control
brake_to_loiter_mix = (float)poshold.brake_to_loiter_timer / (float)POSHOLD_BRAKE_TO_LOITER_TIMER;
// calculate brake_roll and pitch angles to counter-act velocity
poshold_update_brake_angle_from_velocity(poshold.brake_roll, vel_right);
poshold_update_brake_angle_from_velocity(poshold.brake_pitch, -vel_fw);
// run loiter controller
loiter_nav->update();
// calculate final roll and pitch output by mixing loiter and brake controls
poshold.roll = poshold_mix_controls(brake_to_loiter_mix, poshold.brake_roll + poshold.wind_comp_roll, loiter_nav->get_roll());
poshold.pitch = poshold_mix_controls(brake_to_loiter_mix, poshold.brake_pitch + poshold.wind_comp_pitch, loiter_nav->get_pitch());
// check for pilot input
if (!is_zero(target_roll) || !is_zero(target_pitch)) {
// if roll input switch to pilot override for roll
if (!is_zero(target_roll)) {
// init transition to pilot override
poshold_roll_controller_to_pilot_override();
// switch pitch-mode to brake (but ready to go back to loiter anytime)
// no need to reset poshold.brake_pitch here as wind comp has not been updated since last brake_pitch computation
poshold.pitch_mode = POSHOLD_BRAKE_READY_TO_LOITER;
}
// if pitch input switch to pilot override for pitch
if (!is_zero(target_pitch)) {
// init transition to pilot override
poshold_pitch_controller_to_pilot_override();
if (is_zero(target_roll)) {
// switch roll-mode to brake (but ready to go back to loiter anytime)
// no need to reset poshold.brake_roll here as wind comp has not been updated since last brake_roll computation
poshold.roll_mode = POSHOLD_BRAKE_READY_TO_LOITER;
}
}
}
break;
case POSHOLD_LOITER:
// run loiter controller
loiter_nav->update();
// set roll angle based on loiter controller outputs
poshold.roll = loiter_nav->get_roll();
poshold.pitch = loiter_nav->get_pitch();
// update wind compensation estimate
poshold_update_wind_comp_estimate();
// check for pilot input
if (!is_zero(target_roll) || !is_zero(target_pitch)) {
// if roll input switch to pilot override for roll
if (!is_zero(target_roll)) {
// init transition to pilot override
poshold_roll_controller_to_pilot_override();
// switch pitch-mode to brake (but ready to go back to loiter anytime)
poshold.pitch_mode = POSHOLD_BRAKE_READY_TO_LOITER;
// reset brake_pitch because wind_comp is now different and should give the compensation of the whole previous loiter angle
poshold.brake_pitch = 0;
}
// if pitch input switch to pilot override for pitch
if (!is_zero(target_pitch)) {
// init transition to pilot override
poshold_pitch_controller_to_pilot_override();
// if roll not overriden switch roll-mode to brake (but be ready to go back to loiter any time)
if (is_zero(target_roll)) {
poshold.roll_mode = POSHOLD_BRAKE_READY_TO_LOITER;
poshold.brake_roll = 0;
}
// if roll not overridden switch roll-mode to brake (but be ready to go back to loiter any time)
}
}
break;
default:
// do nothing for uncombined roll and pitch modes
break;
}
}
// constrain target pitch/roll angles
float angle_max = copter.aparm.angle_max;
poshold.roll = constrain_int16(poshold.roll, -angle_max, angle_max);
poshold.pitch = constrain_int16(poshold.pitch, -angle_max, angle_max);
// call attitude controller
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(poshold.roll, poshold.pitch, target_yaw_rate);
// call z-axis position controller
pos_control->update_z_controller();
} }
// poshold_update_pilot_lean_angle - update the pilot's filtered lean angle with the latest raw input received // poshold_update_pilot_lean_angle - update the pilot's filtered lean angle with the latest raw input received

47
ArduCopter/mode_rtl.cpp
View File

@ -127,10 +127,9 @@ void Copter::ModeRTL::return_start()
// called by rtl_run at 100hz or more // called by rtl_run at 100hz or more
void Copter::ModeRTL::climb_return_run() void Copter::ModeRTL::climb_return_run()
{ {
// if not auto armed or motor interlock not enabled set throttle to zero and exit immediately // if not armed set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || !motors->get_interlock()) { if (!motors->armed() || !ap.auto_armed || ap.land_complete) {
zero_throttle_and_relax_ac(); make_safe_shut_down();
// To-Do: re-initialise wpnav targets
return; return;
} }
@ -185,10 +184,9 @@ void Copter::ModeRTL::loiterathome_start()
// called by rtl_run at 100hz or more // called by rtl_run at 100hz or more
void Copter::ModeRTL::loiterathome_run() void Copter::ModeRTL::loiterathome_run()
{ {
// if not auto armed or motor interlock not enabled set throttle to zero and exit immediately // if not armed set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || !motors->get_interlock()) { if (!motors->armed() || !ap.auto_armed || ap.land_complete) {
zero_throttle_and_relax_ac(); make_safe_shut_down();
// To-Do: re-initialise wpnav targets
return; return;
} }
@ -258,12 +256,9 @@ void Copter::ModeRTL::descent_run()
float target_pitch = 0.0f; float target_pitch = 0.0f;
float target_yaw_rate = 0.0f; float target_yaw_rate = 0.0f;
// if not auto armed or motor interlock not enabled set throttle to zero and exit immediately // if not armed set throttle to zero and exit immediately
if (!motors->armed() || !ap.auto_armed || !motors->get_interlock()) { if (!motors->armed() || !ap.auto_armed || ap.land_complete) {
zero_throttle_and_relax_ac(); make_safe_shut_down();
// set target to current position
loiter_nav->clear_pilot_desired_acceleration();
loiter_nav->init_target();
return; return;
} }
@ -358,20 +353,17 @@ bool Copter::ModeRTL::landing_gear_should_be_deployed() const
// called by rtl_run at 100hz or more // called by rtl_run at 100hz or more
void Copter::ModeRTL::land_run(bool disarm_on_land) void Copter::ModeRTL::land_run(bool disarm_on_land)
{ {
// if not auto armed or landing completed or motor interlock not enabled set throttle to zero and exit immediately // check if we've completed this stage of RTL
if (!motors->armed() || !ap.auto_armed || ap.land_complete || !motors->get_interlock()) { _state_complete = ap.land_complete;
zero_throttle_and_relax_ac();
// set target to current position
loiter_nav->clear_pilot_desired_acceleration();
loiter_nav->init_target();
// disarm when the landing detector says we've landed // disarm when the landing detector says we've landed
if (ap.land_complete && disarm_on_land) { if (disarm_on_land && ap.land_complete) {
copter.init_disarm_motors(); copter.init_disarm_motors();
} }
// check if we've completed this stage of RTL // if not armed set throttle to zero and exit immediately
_state_complete = ap.land_complete; if (!motors->armed() || !ap.auto_armed || ap.land_complete) {
make_safe_shut_down();
return; return;
} }
@ -380,9 +372,6 @@ void Copter::ModeRTL::land_run(bool disarm_on_land)
land_run_horizontal_control(); land_run_horizontal_control();
land_run_vertical_control(); land_run_vertical_control();
// check if we've completed this stage of RTL
_state_complete = ap.land_complete;
} }
void Copter::ModeRTL::build_path(bool terrain_following_allowed) void Copter::ModeRTL::build_path(bool terrain_following_allowed)

63
ArduCopter/mode_sport.cpp
View File

@ -26,7 +26,6 @@ bool Copter::ModeSport::init(bool ignore_checks)
// should be called at 100hz or more // should be called at 100hz or more
void Copter::ModeSport::run() void Copter::ModeSport::run()
{ {
SportModeState sport_state;
float takeoff_climb_rate = 0.0f; float takeoff_climb_rate = 0.0f;
// initialize vertical speed and acceleration // initialize vertical speed and acceleration
@ -73,39 +72,20 @@ void Copter::ModeSport::run()
float target_climb_rate = get_pilot_desired_climb_rate(channel_throttle->get_control_in()); float target_climb_rate = get_pilot_desired_climb_rate(channel_throttle->get_control_in());
target_climb_rate = constrain_float(target_climb_rate, -get_pilot_speed_dn(), g.pilot_speed_up); target_climb_rate = constrain_float(target_climb_rate, -get_pilot_speed_dn(), g.pilot_speed_up);
// State Machine Determination // Sport State Machine Determination
if (!motors->armed() || !motors->get_interlock()) { AltHoldModeState sport_state = get_alt_hold_state(target_climb_rate);
sport_state = Sport_MotorStopped;
} else if (takeoff.running() || takeoff.triggered(target_climb_rate)) {
sport_state = Sport_Takeoff;
} else if (!ap.auto_armed || ap.land_complete) {
sport_state = Sport_Landed;
} else {
sport_state = Sport_Flying;
}
// State Machine // State Machine
switch (sport_state) { switch (sport_state) {
case Sport_MotorStopped: case AltHold_MotorStopped:
motors->set_desired_spool_state(AP_Motors::DESIRED_SHUT_DOWN);
attitude_control->input_euler_rate_roll_pitch_yaw(target_roll_rate, target_pitch_rate, target_yaw_rate);
#if FRAME_CONFIG == HELI_FRAME
// force descent rate and call position controller
pos_control->set_alt_target_from_climb_rate(-abs(g.land_speed), G_Dt, false);
#else
attitude_control->relax_attitude_controllers();
attitude_control->reset_rate_controller_I_terms(); attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading(); attitude_control->set_yaw_target_to_current_heading();
pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
#endif
pos_control->update_z_controller();
break; break;
case Sport_Takeoff: case AltHold_Takeoff:
// set motors to full range
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// initiate take-off // initiate take-off
if (!takeoff.running()) { if (!takeoff.running()) {
@ -122,38 +102,23 @@ void Copter::ModeSport::run()
// get avoidance adjusted climb rate // get avoidance adjusted climb rate
target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate); target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate);
// call attitude controller
attitude_control->input_euler_rate_roll_pitch_yaw(target_roll_rate, target_pitch_rate, target_yaw_rate);
// call position controller // call position controller
pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false); pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
pos_control->add_takeoff_climb_rate(takeoff_climb_rate, G_Dt); pos_control->add_takeoff_climb_rate(takeoff_climb_rate, G_Dt);
pos_control->update_z_controller();
break; break;
case Sport_Landed: case AltHold_Landed_Ground_Idle:
#if FRAME_CONFIG == HELI_FRAME
// helicopters do not spool down when landed. Only when commanded to go to ground idle by pilot.
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
#else
// set motors to spin-when-armed if throttle below deadzone, otherwise full range (but motors will only spin at min throttle)
if (target_climb_rate < 0.0f) {
motors->set_desired_spool_state(AP_Motors::DESIRED_GROUND_IDLE);
} else {
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
}
#endif
attitude_control->reset_rate_controller_I_terms(); attitude_control->reset_rate_controller_I_terms();
attitude_control->set_yaw_target_to_current_heading(); attitude_control->set_yaw_target_to_current_heading();
attitude_control->input_euler_rate_roll_pitch_yaw(target_roll_rate, target_pitch_rate, target_yaw_rate); // FALLTHROUGH
case AltHold_Landed_Pre_Takeoff:
pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero pos_control->relax_alt_hold_controllers(0.0f); // forces throttle output to go to zero
pos_control->update_z_controller();
break; break;
case Sport_Flying: case AltHold_Flying:
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED); motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// call attitude controller
attitude_control->input_euler_rate_roll_pitch_yaw(target_roll_rate, target_pitch_rate, target_yaw_rate);
// adjust climb rate using rangefinder // adjust climb rate using rangefinder
target_climb_rate = get_surface_tracking_climb_rate(target_climb_rate, pos_control->get_alt_target(), G_Dt); target_climb_rate = get_surface_tracking_climb_rate(target_climb_rate, pos_control->get_alt_target(), G_Dt);
@ -161,11 +126,15 @@ void Copter::ModeSport::run()
// get avoidance adjusted climb rate // get avoidance adjusted climb rate
target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate); target_climb_rate = get_avoidance_adjusted_climbrate(target_climb_rate);
// call position controller
pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false); pos_control->set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
pos_control->update_z_controller();
break; break;
} }
// call attitude controller
attitude_control->input_euler_rate_roll_pitch_yaw(target_roll_rate, target_pitch_rate, target_yaw_rate);
// call z-axis position controller
pos_control->update_z_controller();
} }
#endif #endif

44
ArduCopter/mode_stabilize.cpp
View File

@ -8,28 +8,40 @@
// should be called at 100hz or more // should be called at 100hz or more
void Copter::ModeStabilize::run() void Copter::ModeStabilize::run()
{ {
float target_roll, target_pitch; // apply simple mode transform to pilot inputs
float target_yaw_rate;
// if not armed set throttle to zero and exit immediately
if (!motors->armed() || ap.throttle_zero || !motors->get_interlock()) {
zero_throttle_and_relax_ac();
return;
}
// clear landing flag
set_land_complete(false);
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// apply SIMPLE mode transform to pilot inputs
update_simple_mode(); update_simple_mode();
// convert pilot input to lean angles // convert pilot input to lean angles
float target_roll, target_pitch;
get_pilot_desired_lean_angles(target_roll, target_pitch, copter.aparm.angle_max, copter.aparm.angle_max); get_pilot_desired_lean_angles(target_roll, target_pitch, copter.aparm.angle_max, copter.aparm.angle_max);
// get pilot's desired yaw rate // get pilot's desired yaw rate
target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->get_control_in()); float target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->get_control_in());
if (!motors->armed()) {
// Motors should be Stopped
motors->set_desired_spool_state(AP_Motors::DESIRED_SHUT_DOWN);
} else if (ap.throttle_zero) {
// Attempting to Land
motors->set_desired_spool_state(AP_Motors::DESIRED_GROUND_IDLE);
} else {
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
}
if (motors->get_spool_mode() == AP_Motors::SHUT_DOWN) {
// Motors Stopped
attitude_control->set_yaw_target_to_current_heading();
attitude_control->reset_rate_controller_I_terms();
} else if (motors->get_spool_mode() == AP_Motors::GROUND_IDLE) {
// Landed
attitude_control->set_yaw_target_to_current_heading();
attitude_control->reset_rate_controller_I_terms();
} else if (motors->get_spool_mode() == AP_Motors::THROTTLE_UNLIMITED) {
// clear landing flag above zero throttle
if (!motors->limit.throttle_lower) {
set_land_complete(false);
}
}
// call attitude controller // call attitude controller
attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(target_roll, target_pitch, target_yaw_rate); attitude_control->input_euler_angle_roll_pitch_euler_rate_yaw(target_roll, target_pitch, target_yaw_rate);

6
ArduCopter/mode_throw.cpp
View File

@ -35,7 +35,7 @@ void Copter::ModeThrow::run()
*/ */
// Don't enter THROW mode if interlock will prevent motors running // Don't enter THROW mode if interlock will prevent motors running
if (!motors->armed() && motors->get_interlock()) { if (!motors->armed()) {
// state machine entry is always from a disarmed state // state machine entry is always from a disarmed state
stage = Throw_Disarmed; stage = Throw_Disarmed;
@ -116,7 +116,7 @@ void Copter::ModeThrow::run()
} }
// demand zero throttle (motors will be stopped anyway) and continually reset the attitude controller // demand zero throttle (motors will be stopped anyway) and continually reset the attitude controller
attitude_control->set_throttle_out_unstabilized(0,true,g.throttle_filt); attitude_control->set_throttle_out(0,true,g.throttle_filt);
break; break;
case Throw_Detecting: case Throw_Detecting:
@ -129,7 +129,7 @@ void Copter::ModeThrow::run()
} }
// Hold throttle at zero during the throw and continually reset the attitude controller // Hold throttle at zero during the throw and continually reset the attitude controller
attitude_control->set_throttle_out_unstabilized(0,true,g.throttle_filt); attitude_control->set_throttle_out(0,true,g.throttle_filt);
// Play the waiting for throw tone sequence to alert the user // Play the waiting for throw tone sequence to alert the user
AP_Notify::flags.waiting_for_throw = true; AP_Notify::flags.waiting_for_throw = true;