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Merge pull request #1493 from PX4/fwposcontrolmode

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Fw pos control: small mode cleanup
This commit is contained in:
Thomas Gubler
2014-12-19 11:04:56 +01:00
parent 5becd2227a 6f89514beb
commit 19d5383c56
1 changed files with 69 additions and 57 deletions
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src/modules/fw_pos_control_l1/fw_pos_control_l1_main.cpp
+69 -57
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@@ -200,9 +200,11 @@ private:
ECL_L1_Pos_Controller _l1_control;
TECS _tecs;
fwPosctrl::mTecs _mTecs;
bool _was_pos_control_mode;
bool _was_velocity_control_mode;
bool _was_alt_control_mode;
enum FW_POSCTRL_MODE {
FW_POSCTRL_MODE_AUTO,
FW_POSCTRL_MODE_POSITION,
FW_POSCTRL_MODE_OTHER
} _control_mode_current; ///< used to check the mode in the last control loop iteration. Use to check if the last iteration was in the same mode.
struct {
float l1_period;
@@ -471,7 +473,7 @@ FixedwingPositionControl::FixedwingPositionControl() :
_global_pos_valid(false),
_l1_control(),
_mTecs(),
_was_pos_control_mode(false)
_control_mode_current(FW_POSCTRL_MODE_OTHER)
{
_nav_capabilities.turn_distance = 0.0f;
@@ -908,22 +910,19 @@ FixedwingPositionControl::control_position(const math::Vector<2> &current_positi
/* no throttle limit as default */
float throttle_max = 1.0f;
/* AUTONOMOUS FLIGHT */
if (_control_mode.flag_control_auto_enabled &&
pos_sp_triplet.current.valid) {
/* AUTONOMOUS FLIGHT */
// XXX this should only execute if auto AND safety off (actuators active),
// else integrators should be constantly reset.
if (pos_sp_triplet.current.valid) {
if (!_was_pos_control_mode) {
/* Reset integrators if switching to this mode from a other mode in which posctl was not active */
if (_control_mode_current == FW_POSCTRL_MODE_OTHER) {
/* reset integrators */
if (_mTecs.getEnabled()) {
_mTecs.resetIntegrators();
_mTecs.resetDerivatives(_airspeed.true_airspeed_m_s);
}
}
_was_pos_control_mode = true;
_was_velocity_control_mode = false;
_control_mode_current = FW_POSCTRL_MODE_AUTO;
/* reset hold altitude */
_hold_alt = _global_pos.alt;
@@ -1208,15 +1207,15 @@ FixedwingPositionControl::control_position(const math::Vector<2> &current_positi
tecs_update_pitch_throttle(_pos_sp_triplet.current.alt,
calculate_target_airspeed(_parameters.airspeed_trim),
eas2tas,
math::radians(_parameters.pitch_limit_min),
math::radians(_parameters.pitch_limit_max),
_parameters.throttle_min,
takeoff_throttle,
_parameters.throttle_cruise,
false,
math::radians(_parameters.pitch_limit_min),
_global_pos.alt,
ground_speed);
math::radians(_parameters.pitch_limit_min),
math::radians(_parameters.pitch_limit_max),
_parameters.throttle_min,
takeoff_throttle,
_parameters.throttle_cruise,
false,
math::radians(_parameters.pitch_limit_min),
_global_pos.alt,
ground_speed);
}
} else {
/* Tell the attitude controller to stop integrating while we are waiting
@@ -1248,53 +1247,63 @@ FixedwingPositionControl::control_position(const math::Vector<2> &current_positi
_att_sp.roll_reset_integral = true;
}
} else if (_control_mode.flag_control_velocity_enabled) {
} else if (_control_mode.flag_control_velocity_enabled &&
_control_mode.flag_control_altitude_enabled) {
/* POSITION CONTROL: pitch stick moves altitude setpoint, throttle stick sets airspeed */
const float deadBand = (60.0f/1000.0f);
const float factor = 1.0f - deadBand;
if (!_was_velocity_control_mode) {
if (_control_mode_current != FW_POSCTRL_MODE_POSITION) {
/* Need to init because last loop iteration was in a different mode */
_hold_alt = _global_pos.alt;
_was_alt_control_mode = false;
}
_was_velocity_control_mode = true;
_was_pos_control_mode = false;
// Get demanded airspeed
/* Reset integrators if switching to this mode from a other mode in which posctl was not active */
if (_control_mode_current == FW_POSCTRL_MODE_OTHER) {
/* reset integrators */
if (_mTecs.getEnabled()) {
_mTecs.resetIntegrators();
_mTecs.resetDerivatives(_airspeed.true_airspeed_m_s);
}
}
_control_mode_current = FW_POSCTRL_MODE_POSITION;
/* Get demanded airspeed */
float altctrl_airspeed = _parameters.airspeed_min +
(_parameters.airspeed_max - _parameters.airspeed_min) *
_manual.z;
// Get demanded vertical velocity from pitch control
float pitch = 0.0f;
/* Get demanded vertical velocity from pitch control */
static bool was_in_deadband = false;
if (_manual.x > deadBand) {
pitch = (_manual.x - deadBand) / factor;
} else if (_manual.x < - deadBand) {
pitch = (_manual.x + deadBand) / factor;
}
if (pitch > 0.0f) {
float pitch = (_manual.x - deadBand) / factor;
_hold_alt -= (_parameters.max_climb_rate * dt) * pitch;
_was_alt_control_mode = false;
} else if (pitch < 0.0f) {
was_in_deadband = false;
} else if (_manual.x < - deadBand) {
float pitch = (_manual.x + deadBand) / factor;
_hold_alt -= (_parameters.max_sink_rate * dt) * pitch;
_was_alt_control_mode = false;
} else if (!_was_alt_control_mode) {
was_in_deadband = false;
} else if (!was_in_deadband) {
/* store altitude at which manual.x was inside deadBand
* The aircraft should immediately try to fly at this altitude
* as this is what the pilot expects when he moves the stick to the center */
_hold_alt = _global_pos.alt;
_was_alt_control_mode = true;
was_in_deadband = true;
}
tecs_update_pitch_throttle(_hold_alt,
altctrl_airspeed,
eas2tas,
math::radians(_parameters.pitch_limit_min),
math::radians(_parameters.pitch_limit_max),
_parameters.throttle_min,
_parameters.throttle_max,
_parameters.throttle_cruise,
false,
math::radians(_parameters.pitch_limit_min),
_global_pos.alt,
ground_speed,
TECS_MODE_NORMAL);
altctrl_airspeed,
eas2tas,
math::radians(_parameters.pitch_limit_min),
math::radians(_parameters.pitch_limit_max),
_parameters.throttle_min,
_parameters.throttle_max,
_parameters.throttle_cruise,
false,
math::radians(_parameters.pitch_limit_min),
_global_pos.alt,
ground_speed,
TECS_MODE_NORMAL);
} else {
_was_velocity_control_mode = false;
_was_pos_control_mode = false;
_control_mode_current = FW_POSCTRL_MODE_OTHER;
/** MANUAL FLIGHT **/
@@ -1311,10 +1320,12 @@ FixedwingPositionControl::control_position(const math::Vector<2> &current_positi
}
}
/* Copy thrust output for publication */
if (_vehicle_status.engine_failure || _vehicle_status.engine_failure_cmd) {
/* Set thrust to 0 to minimize damage */
_att_sp.thrust = 0.0f;
} else if (pos_sp_triplet.current.type == SETPOINT_TYPE_TAKEOFF &&
} else if (_control_mode_current == FW_POSCTRL_MODE_AUTO && // launchdetector only available in auto
pos_sp_triplet.current.type == SETPOINT_TYPE_TAKEOFF &&
launch_detection_state != LAUNCHDETECTION_RES_DETECTED_ENABLEMOTORS) {
/* making sure again that the correct thrust is used,
* without depending on library calls for safety reasons */
@@ -1327,8 +1338,9 @@ FixedwingPositionControl::control_position(const math::Vector<2> &current_positi
/* During a takeoff waypoint while waiting for launch the pitch sp is set
* already (not by tecs) */
if (!(pos_sp_triplet.current.type == SETPOINT_TYPE_TAKEOFF &&
launch_detection_state == LAUNCHDETECTION_RES_NONE)) {
if (!(_control_mode_current == FW_POSCTRL_MODE_AUTO &&
pos_sp_triplet.current.type == SETPOINT_TYPE_TAKEOFF &&
launch_detection_state == LAUNCHDETECTION_RES_NONE)) {
_att_sp.pitch_body = _mTecs.getEnabled() ? _mTecs.getPitchSetpoint() : _tecs.get_pitch_demand();
}