ardupilot/ArduPlane/quadplane.h

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#pragma once
#include <AP_Motors/AP_Motors.h>
#include <AC_PID/AC_PID.h>
#include <AC_AttitudeControl/AC_AttitudeControl_Multi.h> // Attitude control library
#include <AP_InertialNav/AP_InertialNav.h>
#include <AC_AttitudeControl/AC_PosControl.h>
#include <AC_WPNav/AC_WPNav.h>
#include <AC_WPNav/AC_Loiter.h>
#include <AC_Fence/AC_Fence.h>
#include <AC_Avoidance/AC_Avoid.h>
#include <AP_Proximity/AP_Proximity.h>
#include "qautotune.h"
#include "defines.h"
/*
QuadPlane specific functionality
*/
class QuadPlane
{
public:
friend class Plane;
friend class AP_Tuning_Plane;
friend class GCS_MAVLINK_Plane;
friend class AP_AdvancedFailsafe_Plane;
friend class QAutoTune;
friend class AP_Arming_Plane;
friend class RC_Channel_Plane;
friend class RC_Channel;
friend class Mode;
friend class ModeAuto;
friend class ModeRTL;
friend class ModeAvoidADSB;
friend class ModeGuided;
friend class ModeQHover;
friend class ModeQLand;
friend class ModeQLoiter;
friend class ModeQRTL;
friend class ModeQStabilize;
friend class ModeQAutotune;
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friend class ModeQAcro;
QuadPlane(AP_AHRS_NavEKF &_ahrs);
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static QuadPlane *get_singleton() {
return _singleton;
}
// var_info for holding Parameter information
static const struct AP_Param::GroupInfo var_info[];
static const struct AP_Param::GroupInfo var_info2[];
void control_run(void);
void control_auto(void);
bool init_mode(void);
bool setup(void);
void vtol_position_controller(void);
void setup_target_position(void);
void takeoff_controller(void);
void waypoint_controller(void);
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void update_throttle_mix(void);
// update transition handling
void update(void);
// set motor arming
void set_armed(bool armed);
// is VTOL available?
bool available(void) const {
return initialised;
}
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// is quadplane assisting?
bool in_assisted_flight(void) const {
return available() && assisted_flight;
}
/*
return true if we are in a transition to fwd flight from hover
*/
bool in_transition(void) const;
/*
return true if we are a tailsitter transitioning to VTOL flight
*/
bool in_tailsitter_vtol_transition(uint32_t now = 0) const;
bool handle_do_vtol_transition(enum MAV_VTOL_STATE state) const;
bool do_vtol_takeoff(const AP_Mission::Mission_Command& cmd);
bool do_vtol_land(const AP_Mission::Mission_Command& cmd);
bool verify_vtol_takeoff(const AP_Mission::Mission_Command &cmd);
bool verify_vtol_land(void);
bool in_vtol_auto(void) const;
bool in_vtol_mode(void) const;
bool in_vtol_posvel_mode(void) const;
void update_throttle_hover();
bool show_vtol_view() const;
// vtol help for is_flying()
bool is_flying(void);
// return current throttle as a percentate
uint8_t throttle_percentage(void) const {
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return last_throttle * 100;
}
// return desired forward throttle percentage
int8_t forward_throttle_pct();
float get_weathervane_yaw_rate_cds(void);
// see if we are flying from vtol point of view
bool is_flying_vtol(void) const;
// return true when tailsitter frame configured
bool is_tailsitter(void) const;
// return true when flying a control surface only tailsitter
bool is_control_surface_tailsitter(void) const;
// true when flying a tilt-vectored tailsitter
bool _is_vectored;
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// return true when flying a tailsitter in VTOL
bool tailsitter_active(void);
// create outputs for tailsitters
void tailsitter_output(void);
// handle different tailsitter input types
void tailsitter_check_input(void);
// check if we have completed transition to fixed wing
bool tailsitter_transition_fw_complete(void);
// return true if we are a tailsitter in FW flight
bool is_tailsitter_in_fw_flight(void) const;
// check if we have completed transition to vtol
bool tailsitter_transition_vtol_complete(void) const;
// account for control surface speed scaling in VTOL modes
void tailsitter_speed_scaling(void);
// user initiated takeoff for guided mode
bool do_user_takeoff(float takeoff_altitude);
// return true if the wp_nav controller is being updated
bool using_wp_nav(void) const;
// return true if the user has set ENABLE
bool enabled(void) const { return enable != 0; }
struct PACKED log_QControl_Tuning {
LOG_PACKET_HEADER;
uint64_t time_us;
float throttle_in;
float angle_boost;
float throttle_out;
float throttle_hover;
float desired_alt;
float inav_alt;
int32_t baro_alt;
int16_t target_climb_rate;
int16_t climb_rate;
float throttle_mix;
float speed_scaler;
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uint8_t transition_state;
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uint8_t assist;
};
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MAV_TYPE get_mav_type(void) const;
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enum Q_ASSIST_STATE_ENUM {
Q_ASSIST_DISABLED,
Q_ASSIST_ENABLED,
Q_ASSIST_FORCE,
};
void set_q_assist_state(Q_ASSIST_STATE_ENUM state) {q_assist_state = state;};
private:
AP_AHRS_NavEKF &ahrs;
AP_Vehicle::MultiCopter aparm;
AP_InertialNav_NavEKF inertial_nav{ahrs};
AP_Enum<AP_Motors::motor_frame_class> frame_class;
AP_Enum<AP_Motors::motor_frame_type> frame_type;
AP_MotorsMulticopter *motors;
const struct AP_Param::GroupInfo *motors_var_info;
AC_AttitudeControl_Multi *attitude_control;
AC_PosControl *pos_control;
AC_WPNav *wp_nav;
AC_Loiter *loiter_nav;
// maximum vertical velocity the pilot may request
AP_Int16 pilot_velocity_z_max;
// vertical acceleration the pilot may request
AP_Int16 pilot_accel_z;
// air mode state: OFF, ON
AirMode air_mode;
// check for quadplane assistance needed
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bool assistance_needed(float aspeed, bool have_airspeed);
// check if it is safe to provide assistance
bool assistance_safe();
// update transition handling
void update_transition(void);
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// check for an EKF yaw reset
void check_yaw_reset(void);
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// hold hover (for transition)
void hold_hover(float target_climb_rate);
// hold stabilize (for transition)
void hold_stabilize(float throttle_in);
// get pilot desired yaw rate in cd/s
float get_pilot_input_yaw_rate_cds(void) const;
// get overall desired yaw rate in cd/s
float get_desired_yaw_rate_cds(void);
// get desired climb rate in cm/s
float get_pilot_desired_climb_rate_cms(void) const;
// get pilot lean angle
void get_pilot_desired_lean_angles(float &roll_out_cd, float &pitch_out_cd, float angle_max_cd, float angle_limit_cd) const;
// initialise throttle_wait when entering mode
void init_throttle_wait();
// use multicopter rate controller
void multicopter_attitude_rate_update(float yaw_rate_cds);
// update yaw target for tiltrotor transition
void update_yaw_target();
// main entry points for VTOL flight modes
void init_stabilize(void);
void control_stabilize(void);
void check_attitude_relax(void);
void init_qacro(void);
float get_pilot_throttle(void);
void control_qacro(void);
void init_hover(void);
void control_hover(void);
void relax_attitude_control();
void init_loiter(void);
void init_qland(void);
void control_loiter(void);
bool check_land_complete(void);
bool land_detector(uint32_t timeout_ms);
bool check_land_final(void);
void init_qrtl(void);
void control_qrtl(void);
float assist_climb_rate_cms(void) const;
// calculate desired yaw rate for assistance
float desired_auto_yaw_rate_cds(void) const;
bool should_relax(void);
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void motors_output(bool run_rate_controller = true);
void Log_Write_QControl_Tuning();
float landing_descent_rate_cms(float height_above_ground) const;
// setup correct aux channels for frame class
void setup_default_channels(uint8_t num_motors);
void guided_start(void);
void guided_update(void);
void update_throttle_suppression(void);
void run_z_controller(void);
void setup_defaults(void);
// calculate a stopping distance for fixed-wing to vtol transitions
float stopping_distance(void);
AP_Int16 transition_time_ms;
// transition deceleration, m/s/s
AP_Float transition_decel;
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// transition failure milliseconds
AP_Int16 transition_failure;
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// Quadplane trim, degrees
AP_Float ahrs_trim_pitch;
float _last_ahrs_trim_pitch;
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// fw landing approach radius
AP_Float fw_land_approach_radius;
AP_Int16 rc_speed;
// min and max PWM for throttle
AP_Int16 thr_min_pwm;
AP_Int16 thr_max_pwm;
// speed below which quad assistance is given
AP_Float assist_speed;
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// angular error at which quad assistance is given
AP_Int8 assist_angle;
uint32_t angle_error_start_ms;
AP_Float assist_delay;
// altitude to trigger assistance
AP_Int16 assist_alt;
uint32_t alt_error_start_ms;
bool in_alt_assist;
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// maximum yaw rate in degrees/second
AP_Float yaw_rate_max;
// landing speed in cm/s
AP_Int16 land_speed_cms;
// QRTL start altitude, meters
AP_Int16 qrtl_alt;
// alt to switch to QLAND_FINAL
AP_Float land_final_alt;
AP_Float vel_forward_alt_cutoff;
AP_Int8 enable;
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AP_Int8 transition_pitch_max;
// control if a VTOL RTL will be used
AP_Int8 rtl_mode;
// control if a VTOL GUIDED will be used
AP_Int8 guided_mode;
// control ESC throttle calibration
AP_Int8 esc_calibration;
void run_esc_calibration(void);
// ICEngine control on landing
AP_Int8 land_icengine_cut;
// HEARTBEAT mav_type override
AP_Int8 mav_type;
// manual throttle curve expo strength
AP_Float throttle_expo;
// manual forward throttle input
AP_Float fwd_thr_max;
RC_Channel *rc_fwd_thr_ch;
// QACRO mode max roll/pitch/yaw rates
AP_Float acro_roll_rate;
AP_Float acro_pitch_rate;
AP_Float acro_yaw_rate;
// time we last got an EKF yaw reset
uint32_t ekfYawReset_ms;
struct {
AP_Float gain;
float integrator;
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uint32_t last_ms;
int8_t last_pct;
} vel_forward;
struct {
AP_Float gain;
AP_Float min_roll;
uint32_t last_pilot_input_ms;
float last_output;
} weathervane;
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bool initialised;
// timer start for transition
uint32_t transition_start_ms;
float transition_initial_pitch;
uint32_t transition_low_airspeed_ms;
Location last_auto_target;
// last throttle value when active
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float last_throttle;
// pitch when we enter loiter mode
int32_t loiter_initial_pitch_cd;
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// when did we last run the attitude controller?
uint32_t last_att_control_ms;
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// true if we have reached the airspeed threshold for transition
enum {
TRANSITION_AIRSPEED_WAIT,
TRANSITION_TIMER,
TRANSITION_ANGLE_WAIT_FW,
TRANSITION_ANGLE_WAIT_VTOL,
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TRANSITION_DONE
} transition_state;
// true when waiting for pilot throttle
bool throttle_wait:1;
// true when quad is assisting a fixed wing mode
bool assisted_flight:1;
// true when in angle assist
bool in_angle_assist:1;
// are we in a guided takeoff?
bool guided_takeoff:1;
struct {
// time when motors reached lower limit
uint32_t lower_limit_start_ms;
uint32_t land_start_ms;
float vpos_start_m;
} landing_detect;
// throttle mix acceleration filter
LowPassFilterVector3f throttle_mix_accel_ef_filter = LowPassFilterVector3f(1.0f);
// time we last set the loiter target
uint32_t last_loiter_ms;
enum position_control_state {
QPOS_POSITION1,
QPOS_POSITION2,
QPOS_LAND_DESCEND,
QPOS_LAND_FINAL,
QPOS_LAND_COMPLETE
};
struct {
enum position_control_state state;
float speed_scale;
Vector2f target_velocity;
float max_speed;
Vector3f target;
bool slow_descent:1;
} poscontrol;
struct {
bool running;
uint32_t start_ms; // system time the motor test began
uint32_t timeout_ms = 0; // test will timeout this many milliseconds after the motor_test_start_ms
uint8_t seq = 0; // motor sequence number of motor being tested
uint8_t throttle_type = 0; // motor throttle type (0=throttle percentage, 1=PWM, 2=pilot throttle channel pass-through)
uint16_t throttle_value = 0; // throttle to be sent to motor, value depends upon it's type
uint8_t motor_count; // number of motors to cycle
} motor_test;
// time of last control log message
uint32_t last_ctrl_log_ms;
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// time of last QTUN log message
uint32_t last_qtun_log_ms;
// types of tilt mechanisms
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enum {TILT_TYPE_CONTINUOUS =0,
TILT_TYPE_BINARY =1,
TILT_TYPE_VECTORED_YAW =2,
TILT_TYPE_BICOPTER =3
};
// tiltrotor control variables
struct {
AP_Int16 tilt_mask;
AP_Int16 max_rate_up_dps;
AP_Int16 max_rate_down_dps;
AP_Int8 max_angle_deg;
AP_Int8 tilt_type;
AP_Float tilt_yaw_angle;
AP_Float fixed_angle;
AP_Float fixed_gain;
float current_tilt;
float current_throttle;
bool motors_active:1;
float transition_yaw_cd;
uint32_t transition_yaw_set_ms;
bool is_vectored;
} tilt;
// bit 0 enables plane mode and bit 1 enables body-frame roll mode
enum tailsitter_input {
TAILSITTER_INPUT_PLANE = (1U<<0),
TAILSITTER_INPUT_BF_ROLL = (1U<<1)
};
enum tailsitter_mask {
TAILSITTER_MASK_AILERON = (1U<<0),
TAILSITTER_MASK_ELEVATOR = (1U<<1),
TAILSITTER_MASK_THROTTLE = (1U<<2),
TAILSITTER_MASK_RUDDER = (1U<<3),
};
enum tailsitter_gscl_mask {
TAILSITTER_GSCL_THROTTLE = (1U<<0),
TAILSITTER_GSCL_ATT_THR = (1U<<1),
TAILSITTER_GSCL_DISK_THEORY = (1U<<2),
TAILSITTER_GSCL_ALTITUDE = (1U<<3),
};
// tailsitter control variables
struct {
AP_Int8 transition_angle;
AP_Int8 input_type;
AP_Int8 input_mask;
AP_Int8 input_mask_chan;
AP_Float vectored_forward_gain;
AP_Float vectored_hover_gain;
AP_Float vectored_hover_power;
AP_Float throttle_scale_max;
AP_Float gain_scaling_min;
AP_Float max_roll_angle;
AP_Int16 motor_mask;
AP_Float scaling_speed_min;
AP_Float scaling_speed_max;
AP_Int16 gain_scaling_mask;
AP_Float disk_loading;
} tailsitter;
// tailsitter speed scaler
float last_spd_scaler = 1.0f; // used to slew rate limiting with TAILSITTER_GSCL_ATT_THR option
float log_spd_scaler; // for QTUN log
// the attitude view of the VTOL attitude controller
AP_AHRS_View *ahrs_view;
// time when motors were last active
uint32_t last_motors_active_ms;
// time when we last ran the vertical accel controller
uint32_t last_pidz_active_ms;
uint32_t last_pidz_init_ms;
// time when we were last in a vtol control mode
uint32_t last_vtol_mode_ms;
void tiltrotor_slew(float tilt);
void tiltrotor_binary_slew(bool forward);
void tiltrotor_update(void);
void tiltrotor_continuous_update(void);
void tiltrotor_binary_update(void);
void tiltrotor_vectoring(void);
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void tiltrotor_bicopter(void);
float tilt_throttle_scaling(void);
void tilt_compensate_angle(float *thrust, uint8_t num_motors, float non_tilted_mul, float tilted_mul);
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void tilt_compensate(float *thrust, uint8_t num_motors);
bool is_motor_tilting(uint8_t motor) const {
return (((uint8_t)tilt.tilt_mask.get()) & (1U<<motor));
}
bool tiltrotor_fully_fwd(void) const;
float tilt_max_change(bool up) const;
void afs_terminate(void);
bool guided_mode_enabled(void);
// set altitude target to current altitude
void set_alt_target_current(void);
// adjust altitude target smoothly
void adjust_alt_target(float target_cm);
// additional options
AP_Int32 options;
enum {
OPTION_LEVEL_TRANSITION=(1<<0),
OPTION_ALLOW_FW_TAKEOFF=(1<<1),
OPTION_ALLOW_FW_LAND=(1<<2),
OPTION_RESPECT_TAKEOFF_FRAME=(1<<3),
OPTION_MISSION_LAND_FW_APPROACH=(1<<4),
OPTION_FS_QRTL=(1<<5),
OPTION_IDLE_GOV_MANUAL=(1<<6),
OPTION_Q_ASSIST_FORCE_ENABLE=(1<<7),
OPTION_TAILSIT_Q_ASSIST_MOTORS_ONLY=(1<<8),
OPTION_AIRMODE=(1<<9),
OPTION_DISARMED_TILT=(1<<10),
OPTION_DELAY_ARMING=(1<<11),
OPTION_DISABLE_SYNTHETIC_AIRSPEED_ASSIST=(1<<12),
OPTION_DISABLE_GROUND_EFFECT_COMP=(1<<13),
OPTION_INGORE_FW_ANGLE_LIMITS_IN_Q_MODES=(1<<14),
};
AP_Float takeoff_failure_scalar;
AP_Float maximum_takeoff_airspeed;
uint32_t takeoff_start_time_ms;
uint32_t takeoff_time_limit_ms;
float last_land_final_agl;
// oneshot with duration ARMING_DELAY_MS used by quadplane to delay spoolup after arming:
// ignored unless OPTION_DELAY_ARMING or OPTION_TILT_DISARMED is set
bool delay_arming;
/*
return true if current mission item is a vtol takeoff
*/
bool is_vtol_takeoff(uint16_t id) const;
/*
return true if current mission item is a vtol landing
*/
bool is_vtol_land(uint16_t id) const;
#if QAUTOTUNE_ENABLED
// qautotune mode
QAutoTune qautotune;
#endif
/*
are we in the approach phase of a VTOL landing?
*/
bool in_vtol_land_approach(void) const;
/*
are we in the descent phase of a VTOL landing?
*/
bool in_vtol_land_descent(void) const;
/*
are we in the final landing phase of a VTOL landing?
*/
bool in_vtol_land_final(void) const;
/*
are we in any of the phases of a VTOL landing?
*/
bool in_vtol_land_sequence(void) const;
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// Q assist state, can be enabled, disabled or force. Default to enabled
Q_ASSIST_STATE_ENUM q_assist_state = Q_ASSIST_STATE_ENUM::Q_ASSIST_ENABLED;
public:
void motor_test_output();
MAV_RESULT mavlink_motor_test_start(mavlink_channel_t chan, uint8_t motor_seq, uint8_t throttle_type,
uint16_t throttle_value, float timeout_sec,
uint8_t motor_count);
private:
void motor_test_stop();
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static QuadPlane *_singleton;
};