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ardupilot/ArduPlane/Log.cpp

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#include "Plane.h"
#if LOGGING_ENABLED == ENABLED
// Write an attitude packet
void Plane::Log_Write_Attitude(void)
{
Vector3f targets; // Package up the targets into a vector for commonality with Copter usage of Log_Wrote_Attitude
targets.x = nav_roll_cd;
targets.y = nav_pitch_cd;
if (quadplane.in_vtol_mode() || quadplane.in_assisted_flight()) {
// when VTOL active log the copter target yaw
targets.z = wrap_360_cd(quadplane.attitude_control->get_att_target_euler_cd().z);
} else {
//Plane does not have the concept of navyaw. This is a placeholder.
targets.z = 0;
}
if (quadplane.tailsitter_active() || quadplane.in_vtol_mode()) {
// we need the attitude targets from the AC_AttitudeControl controller, as they
// account for the acceleration limits.
// Also, for bodyframe roll input types, _attitude_target_euler_angle is not maintained
// since Euler angles are not used and it is a waste of cpu to compute them at the loop rate.
// Get them from the quaternion instead:
quadplane.attitude_control->get_attitude_target_quat().to_euler(targets.x, targets.y, targets.z);
targets *= degrees(100.0f);
logger.Write_AttitudeView(*quadplane.ahrs_view, targets);
} else {
logger.Write_Attitude(targets);
}
if (quadplane.in_vtol_mode() || quadplane.in_assisted_flight()) {
// log quadplane PIDs separately from fixed wing PIDs
logger.Write_PID(LOG_PIQR_MSG, quadplane.attitude_control->get_rate_roll_pid().get_pid_info());
logger.Write_PID(LOG_PIQP_MSG, quadplane.attitude_control->get_rate_pitch_pid().get_pid_info());
logger.Write_PID(LOG_PIQY_MSG, quadplane.attitude_control->get_rate_yaw_pid().get_pid_info());
logger.Write_PID(LOG_PIQA_MSG, quadplane.pos_control->get_accel_z_pid().get_pid_info() );
}
logger.Write_PID(LOG_PIDR_MSG, rollController.get_pid_info());
logger.Write_PID(LOG_PIDP_MSG, pitchController.get_pid_info());
logger.Write_PID(LOG_PIDY_MSG, yawController.get_pid_info());
logger.Write_PID(LOG_PIDS_MSG, steerController.get_pid_info());
#if AP_AHRS_NAVEKF_AVAILABLE
AP::ahrs_navekf().Log_Write();
logger.Write_AHRS2();
#endif
#if CONFIG_HAL_BOARD == HAL_BOARD_SITL
sitl.Log_Write_SIMSTATE();
#endif
logger.Write_POS();
}
// do logging at loop rate
void Plane::Log_Write_Fast(void)
{
if (should_log(MASK_LOG_ATTITUDE_FAST)) {
Log_Write_Attitude();
}
}
struct PACKED log_Startup {
LOG_PACKET_HEADER;
uint64_t time_us;
uint8_t startup_type;
uint16_t command_total;
};
void Plane::Log_Write_Startup(uint8_t type)
{
struct log_Startup pkt = {
LOG_PACKET_HEADER_INIT(LOG_STARTUP_MSG),
time_us : AP_HAL::micros64(),
startup_type : type,
command_total : mission.num_commands()
};
logger.WriteCriticalBlock(&pkt, sizeof(pkt));
}
struct PACKED log_Control_Tuning {
LOG_PACKET_HEADER;
uint64_t time_us;
int16_t nav_roll_cd;
int16_t roll;
int16_t nav_pitch_cd;
int16_t pitch;
int16_t throttle_out;
int16_t rudder_out;
int16_t throttle_dem;
float airspeed_estimate;
};
// Write a control tuning packet. Total length : 22 bytes
void Plane::Log_Write_Control_Tuning()
{
float est_airspeed = 0;
ahrs.airspeed_estimate(est_airspeed);
struct log_Control_Tuning pkt = {
LOG_PACKET_HEADER_INIT(LOG_CTUN_MSG),
time_us : AP_HAL::micros64(),
nav_roll_cd : (int16_t)nav_roll_cd,
roll : (int16_t)ahrs.roll_sensor,
nav_pitch_cd : (int16_t)nav_pitch_cd,
pitch : (int16_t)ahrs.pitch_sensor,
throttle_out : (int16_t)SRV_Channels::get_output_scaled(SRV_Channel::k_throttle),
rudder_out : (int16_t)SRV_Channels::get_output_scaled(SRV_Channel::k_rudder),
throttle_dem : (int16_t)SpdHgt_Controller->get_throttle_demand(),
airspeed_estimate : est_airspeed
};
logger.WriteBlock(&pkt, sizeof(pkt));
}
struct PACKED log_Nav_Tuning {
LOG_PACKET_HEADER;
uint64_t time_us;
float wp_distance;
int16_t target_bearing_cd;
int16_t nav_bearing_cd;
int16_t altitude_error_cm;
float xtrack_error;
float xtrack_error_i;
float airspeed_error;
int32_t target_lat;
int32_t target_lng;
int32_t target_alt;
int32_t target_airspeed;
};
// Write a navigation tuning packet
void Plane::Log_Write_Nav_Tuning()
{
struct log_Nav_Tuning pkt = {
LOG_PACKET_HEADER_INIT(LOG_NTUN_MSG),
time_us : AP_HAL::micros64(),
wp_distance : auto_state.wp_distance,
target_bearing_cd : (int16_t)nav_controller->target_bearing_cd(),
nav_bearing_cd : (int16_t)nav_controller->nav_bearing_cd(),
altitude_error_cm : (int16_t)altitude_error_cm,
xtrack_error : nav_controller->crosstrack_error(),
xtrack_error_i : nav_controller->crosstrack_error_integrator(),
airspeed_error : airspeed_error,
target_lat : next_WP_loc.lat,
target_lng : next_WP_loc.lng,
target_alt : next_WP_loc.alt,
target_airspeed : target_airspeed_cm,
};
logger.WriteBlock(&pkt, sizeof(pkt));
}
struct PACKED log_Status {
LOG_PACKET_HEADER;
uint64_t time_us;
uint8_t is_flying;
float is_flying_probability;
uint8_t armed;
uint8_t safety;
bool is_crashed;
bool is_still;
uint8_t stage;
bool impact;
};
void Plane::Log_Write_Status()
{
struct log_Status pkt = {
LOG_PACKET_HEADER_INIT(LOG_STATUS_MSG)
,time_us : AP_HAL::micros64()
,is_flying : is_flying()
,is_flying_probability : isFlyingProbability
,armed : hal.util->get_soft_armed()
,safety : static_cast<uint8_t>(hal.util->safety_switch_state())
,is_crashed : crash_state.is_crashed
,is_still : AP::ins().is_still()
,stage : static_cast<uint8_t>(flight_stage)
,impact : crash_state.impact_detected
};
logger.WriteBlock(&pkt, sizeof(pkt));
}
struct PACKED log_AETR {
LOG_PACKET_HEADER;
uint64_t time_us;
int16_t aileron;
int16_t elevator;
int16_t throttle;
int16_t rudder;
int16_t flap;
};
void Plane::Log_Write_AETR()
{
struct log_AETR pkt = {
LOG_PACKET_HEADER_INIT(LOG_AETR_MSG)
,time_us : AP_HAL::micros64()
,aileron : SRV_Channels::get_output_scaled(SRV_Channel::k_aileron)
,elevator : SRV_Channels::get_output_scaled(SRV_Channel::k_elevator)
,throttle : SRV_Channels::get_output_scaled(SRV_Channel::k_throttle)
,rudder : SRV_Channels::get_output_scaled(SRV_Channel::k_rudder)
,flap : SRV_Channels::get_output_scaled(SRV_Channel::k_flap_auto)
};
logger.WriteBlock(&pkt, sizeof(pkt));
}
void Plane::Log_Write_RC(void)
{
logger.Write_RCIN();
logger.Write_RCOUT();
if (rssi.enabled()) {
logger.Write_RSSI();
}
Log_Write_AETR();
}
// type and unit information can be found in
// libraries/AP_Logger/Logstructure.h; search for "log_Units" for
// units and "Format characters" for field type information
const struct LogStructure Plane::log_structure[] = {
LOG_COMMON_STRUCTURES,
{ LOG_STARTUP_MSG, sizeof(log_Startup),
"STRT", "QBH", "TimeUS,SType,CTot", "s--", "F--" },
// @LoggerMessage: CTUN
// @Description: Control Tuning information
// @Field: TimeUS: microseconds since system startup
// @Field: NavRoll: desired roll
// @Field: Roll: achieved roll
// @Field: NavPitch: desired pitch
// @Field: Pitch: achieved pitch
// @Field: ThrOut: scaled output throttle
// @Field: RdrOut: scaled output rudder
// @Field: ThrDem: demanded speed-height-controller throttle
// @Field: Aspd: airspeed estimate
{ LOG_CTUN_MSG, sizeof(log_Control_Tuning),
"CTUN", "Qcccchhhf", "TimeUS,NavRoll,Roll,NavPitch,Pitch,ThrOut,RdrOut,ThrDem,Aspd", "sdddd---n", "FBBBB---0" },
// @LoggerMessage: NTUN
// @Description: Navigation Tuning information - e.g. vehicle destination
// @URL: http://ardupilot.org/rover/docs/navigation.html
// @Field: TimeUS: Microseconds since system startup
// @Field: Dist: distance to the current navigation waypoint
// @Field: TBrg: bearing to the current navigation waypoint
// @Field: NavBrg: the vehicle's desired heading
// @Field: AltErr: difference between current vehicle height and target height
// @Field: XT: the vehicle's current distance from the current travel segment
// @Field: XTi: integration of the vehicle's crosstrack error
// @Field: AspdE: difference between vehicle's airspeed and desired airspeed
// @Field: AspdE: difference between vehicle's airspeed and desired airspeed
// @Field: TLat: target latitude
// @Field: TLng: target longitude
// @Field: TAlt: target altitude
// @Field: TAspd: target airspeed
{ LOG_NTUN_MSG, sizeof(log_Nav_Tuning),
"NTUN", "QfcccfffLLii", "TimeUS,Dist,TBrg,NavBrg,AltErr,XT,XTi,AspdE,TLat,TLng,TAlt,TAspd", "smddmmmnDUmn", "F0BBB0B0GGBB" },
// @LoggerMessage: ATRP
// @Description: Pitch/Roll AutoTune messages for Plane
// @Field: TimeUS: Microseconds since system startup
// @Field: Type: Type of autotune (0 = Roll/ 1 = Pitch)
// @Field: State: AutoTune state
// @Field: Servo: Normalised control surface output (between -4500 to 4500)
// @Field: Demanded: Desired Pitch/Roll rate
// @Field: Achieved: Achieved Pitch/Roll rate
// @Field: P: Proportional part of PID
{ LOG_ATRP_MSG, sizeof(AP_AutoTune::log_ATRP),
"ATRP", "QBBcfff", "TimeUS,Type,State,Servo,Demanded,Achieved,P", "s---dd-", "F---00-" },
// @LoggerMessage: STAT
// @Description: Current status of the aircraft
// @Field: TimeUS: Microseconds since system startup
// @Field: isFlying: True if aircraft is probably flying
// @Field: isFlyProb: Probabilty that the aircraft is flying
// @Field: Armed: Arm status of the aircraft
// @Field: Safety: State of the safety switch
// @Field: Crash: True if crash is detected
// @Field: Still: True when vehicle is not moving in any axis
// @Field: Stage: Current stage of the flight
// @Field: Hit: True if impact is detected
{ LOG_STATUS_MSG, sizeof(log_Status),
"STAT", "QBfBBBBBB", "TimeUS,isFlying,isFlyProb,Armed,Safety,Crash,Still,Stage,Hit", "s--------", "F--------" },
// @LoggerMessage: QTUN
// @Description: QuadPlane vertical tuning message
// @Field: TimeUS: microseconds since system startup
// @Field: ThI: throttle input
// @Field: ABst: angle boost
// @Field: ThO: throttle output
// @Field: ThH: calculated hover throttle
// @Field: DAlt: desired altitude
// @Field: Alt: achieved altitude
// @Field: BAlt: barometric altitude
// @Field: DCRt: desired climb rate
// @Field: CRt: climb rate
// @Field: TMix: transition throttle mix value
// @Field: Sscl: speed scalar for surfaces
{ LOG_QTUN_MSG, sizeof(QuadPlane::log_QControl_Tuning),
"QTUN", "Qffffffeccff", "TimeUS,ThI,ABst,ThO,ThH,DAlt,Alt,BAlt,DCRt,CRt,TMix,Sscl", "s----mmmnn--", "F----00000-0" },
// @LoggerMessage: AOA
// @Description: Angle of attack and Side Slip Angle values
// @Field: TimeUS: Microseconds since system startup
// @Field: AOA: Angle of Attack calculated from airspeed, wind vector,velocity vector
// @Field: SSA: Side Slip Angle calculated from airspeed, wind vector,velocity vector
{ LOG_AOA_SSA_MSG, sizeof(log_AOA_SSA),
"AOA", "Qff", "TimeUS,AOA,SSA", "sdd", "F00" },
// @LoggerMessage: PIQR,PIQP,PIQY,PIQA
// @Description: QuadPlane Proportional/Integral/Derivative gain values for Roll/Pitch/Yaw/Z
// @Field: TimeUS: microseconds since system startup
// @Field: Tar: desired value
// @Field: Act: achieved value
// @Field: Err: error between target and achieved
// @Field: P: proportional part of PID
// @Field: I: integral part of PID
// @Field: D: derivative part of PID
// @Field: FF: controller feed-forward portion of response
{ LOG_PIQR_MSG, sizeof(log_PID),
"PIQR", PID_FMT, PID_LABELS, PID_UNITS, PID_MULTS },
{ LOG_PIQP_MSG, sizeof(log_PID),
"PIQP", PID_FMT, PID_LABELS, PID_UNITS, PID_MULTS },
{ LOG_PIQY_MSG, sizeof(log_PID),
"PIQY", PID_FMT, PID_LABELS, PID_UNITS, PID_MULTS },
{ LOG_PIQA_MSG, sizeof(log_PID),
"PIQA", PID_FMT, PID_LABELS, PID_UNITS, PID_MULTS },
// @LoggerMessage: AETR
// @Description: Normalised pre-mixer control surface outputs
// @Field: TimeUS: Microseconds since system startup
// @Field: Ail: Pre-mixer value for aileron output (between -4500 to 4500)
// @Field: Elev: Pre-mixer value for elevator output (between -4500 to 4500)
// @Field: Thr: Pre-mixer value for throttle output (between -4500 to 4500)
// @Field: Rudd: Pre-mixer value for rudder output (between -4500 to 4500)
// @Field: Flap: Pre-mixer value for flaps output (between -4500 to 4500)
{ LOG_AETR_MSG, sizeof(log_AETR),
"AETR", "Qhhhhh", "TimeUS,Ail,Elev,Thr,Rudd,Flap", "s-----", "F-----" },
};
void Plane::Log_Write_Vehicle_Startup_Messages()
{
// only 200(?) bytes are guaranteed by AP_Logger
Log_Write_Startup(TYPE_GROUNDSTART_MSG);
logger.Write_Mode(control_mode->mode_number(), control_mode_reason);
ahrs.Log_Write_Home_And_Origin();
gps.Write_AP_Logger_Log_Startup_messages();
}
/*
initialise logging subsystem
*/
void Plane::log_init(void)
{
logger.Init(log_structure, ARRAY_SIZE(log_structure));
}
#else // LOGGING_ENABLED
void Plane::Log_Write_Attitude(void) {}
void Plane::Log_Write_Fast(void) {}
void Plane::Log_Write_Performance() {}
void Plane::Log_Write_Startup(uint8_t type) {}
void Plane::Log_Write_Control_Tuning() {}
void Plane::Log_Write_Nav_Tuning() {}
void Plane::Log_Write_Status() {}
void Plane::Log_Write_RC(void) {}
void Plane::Log_Write_Vehicle_Startup_Messages() {}
void Plane::log_init(void) {}
#endif // LOGGING_ENABLED
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