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ardupilot/libraries/AP_Airspeed/AP_Airspeed.cpp

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/*
This program is free software: you can redistribute it and/or modify
it under the terms of the GNU General Public License as published by
the Free Software Foundation, either version 3 of the License, or
(at your option) any later version.
This program is distributed in the hope that it will be useful,
but WITHOUT ANY WARRANTY; without even the implied warranty of
MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
GNU General Public License for more details.
You should have received a copy of the GNU General Public License
along with this program. If not, see <http://www.gnu.org/licenses/>.
*/
/*
* AP_Airspeed.cpp - airspeed (pitot) driver
*/
#include "AP_Airspeed.h"
#include <AP_Vehicle/AP_Vehicle_Type.h>
// Dummy the AP_Airspeed class to allow building Airspeed only for plane, rover, sub, and copter & heli 2MB boards
// This could be removed once the build system allows for APM_BUILD_TYPE in header files
#ifndef AP_AIRSPEED_DUMMY_METHODS_ENABLED
#define AP_AIRSPEED_DUMMY_METHODS_ENABLED ((APM_BUILD_COPTER_OR_HELI && BOARD_FLASH_SIZE <= 1024) || \
APM_BUILD_TYPE(APM_BUILD_AntennaTracker) || APM_BUILD_TYPE(APM_BUILD_Blimp))
#endif
#if !AP_AIRSPEED_DUMMY_METHODS_ENABLED
#include <AP_Common/AP_Common.h>
#include <AP_HAL/AP_HAL.h>
#include <AP_HAL/I2CDevice.h>
#include <AP_Math/AP_Math.h>
#include <GCS_MAVLink/GCS.h>
#include <SRV_Channel/SRV_Channel.h>
#include <AP_Logger/AP_Logger.h>
#include <utility>
#include "AP_Airspeed_MS4525.h"
#include "AP_Airspeed_MS5525.h"
#include "AP_Airspeed_SDP3X.h"
#include "AP_Airspeed_DLVR.h"
#include "AP_Airspeed_analog.h"
#include "AP_Airspeed_ASP5033.h"
#include "AP_Airspeed_Backend.h"
#include "AP_Airspeed_UAVCAN.h"
#include "AP_Airspeed_NMEA.h"
#include "AP_Airspeed_MSP.h"
#include "AP_Airspeed_SITL.h"
extern const AP_HAL::HAL &hal;
#include <AP_Vehicle/AP_FixedWing.h>
#ifdef HAL_AIRSPEED_TYPE_DEFAULT
#define ARSPD_DEFAULT_TYPE HAL_AIRSPEED_TYPE_DEFAULT
#ifndef ARSPD_DEFAULT_PIN
#define ARSPD_DEFAULT_PIN 1
#endif
#elif APM_BUILD_TYPE(APM_BUILD_ArduPlane)
// The HAL_BOARD_SITL setting is required because of current probe process for MS4525 will
// connect and find the SIM_DLVR sensors & fault as there is no way to tell them apart
#if CONFIG_HAL_BOARD == HAL_BOARD_SITL
#define ARSPD_DEFAULT_TYPE TYPE_ANALOG
#define ARSPD_DEFAULT_PIN 1
#else
#define ARSPD_DEFAULT_TYPE TYPE_I2C_MS4525
#ifdef HAL_DEFAULT_AIRSPEED_PIN
#define ARSPD_DEFAULT_PIN HAL_DEFAULT_AIRSPEED_PIN
#else
#define ARSPD_DEFAULT_PIN 15
#endif
#endif //CONFIG_HAL_BOARD
#else // All Other Vehicle Types
#define ARSPD_DEFAULT_TYPE TYPE_NONE
#define ARSPD_DEFAULT_PIN 15
#endif
#ifndef HAL_AIRSPEED_BUS_DEFAULT
#define HAL_AIRSPEED_BUS_DEFAULT 1
#endif
#if CONFIG_HAL_BOARD_SUBTYPE == HAL_BOARD_SUBTYPE_LINUX_DISCO
#define PSI_RANGE_DEFAULT 0.05
#endif
#ifndef PSI_RANGE_DEFAULT
#define PSI_RANGE_DEFAULT 1.0f
#endif
#define OPTIONS_DEFAULT AP_Airspeed::OptionsMask::ON_FAILURE_AHRS_WIND_MAX_DO_DISABLE | AP_Airspeed::OptionsMask::ON_FAILURE_AHRS_WIND_MAX_RECOVERY_DO_REENABLE | AP_Airspeed::OptionsMask::USE_EKF_CONSISTENCY
// table of user settable parameters
const AP_Param::GroupInfo AP_Airspeed::var_info[] = {
// @Param: _TYPE
// @DisplayName: Airspeed type
// @Description: Type of airspeed sensor
// @Values: 0:None,1:I2C-MS4525D0,2:Analog,3:I2C-MS5525,4:I2C-MS5525 (0x76),5:I2C-MS5525 (0x77),6:I2C-SDP3X,7:I2C-DLVR-5in,8:DroneCAN,9:I2C-DLVR-10in,10:I2C-DLVR-20in,11:I2C-DLVR-30in,12:I2C-DLVR-60in,13:NMEA water speed,14:MSP,15:ASP5033,100:SITL
// @User: Standard
AP_GROUPINFO_FLAGS("_TYPE", 0, AP_Airspeed, param[0].type, ARSPD_DEFAULT_TYPE, AP_PARAM_FLAG_ENABLE), // NOTE: Index 0 is actually used as index 63 here
// @Param: _DEVID
// @DisplayName: Airspeed ID
// @Description: Airspeed sensor ID, taking into account its type, bus and instance
// @ReadOnly: True
// @User: Advanced
AP_GROUPINFO_FLAGS("_DEVID", 24, AP_Airspeed, param[0].bus_id, 0, AP_PARAM_FLAG_INTERNAL_USE_ONLY),
#ifndef HAL_BUILD_AP_PERIPH
// @Param: _USE
// @DisplayName: Airspeed use
// @Description: Enables airspeed use for automatic throttle modes and replaces control from THR_TRIM. Continues to display and log airspeed if set to 0. Uses airspeed for control if set to 1. Only uses airspeed when throttle = 0 if set to 2 (useful for gliders with airspeed sensors behind propellers).
// @Description{Copter, Blimp, Rover, Sub}: This parameter is not used by this vehicle. Always set to 0.
// @Values: 0:DoNotUse,1:Use,2:UseWhenZeroThrottle
// @User: Standard
AP_GROUPINFO("_USE", 1, AP_Airspeed, param[0].use, 0),
// @Param: _OFFSET
// @DisplayName: Airspeed offset
// @Description: Airspeed calibration offset
// @Increment: 0.1
// @User: Advanced
AP_GROUPINFO("_OFFSET", 2, AP_Airspeed, param[0].offset, 0),
// @Param: _RATIO
// @DisplayName: Airspeed ratio
// @Description: Calibrates pitot tube pressure to velocity. Increasing this value will indicate a higher airspeed at any given dynamic pressure.
// @Increment: 0.1
// @User: Advanced
AP_GROUPINFO("_RATIO", 3, AP_Airspeed, param[0].ratio, 1.9936f),
// @Param: _PIN
// @DisplayName: Airspeed pin
// @Description: The pin number that the airspeed sensor is connected to for analog sensors. Set to 15 on the Pixhawk for the analog airspeed port.
// @User: Advanced
AP_GROUPINFO("_PIN", 4, AP_Airspeed, param[0].pin, ARSPD_DEFAULT_PIN),
#endif // HAL_BUILD_AP_PERIPH
#if AP_AIRSPEED_AUTOCAL_ENABLE
// @Param: _AUTOCAL
// @DisplayName: Automatic airspeed ratio calibration
// @DisplayName{Copter, Blimp, Rover, Sub}: This parameter and function is not used by this vehicle. Always set to 0.
// @Description: Enables automatic adjustment of ARSPD_RATIO during a calibration flight based on estimation of ground speed and true airspeed. New ratio saved every 2 minutes if change is > 5%. Should not be left enabled.
// @User: Advanced
AP_GROUPINFO("_AUTOCAL", 5, AP_Airspeed, param[0].autocal, 0),
#endif
#ifndef HAL_BUILD_AP_PERIPH
// @Param: _TUBE_ORDER
// @DisplayName: Control pitot tube order
// @Description: This parameter allows you to control whether the order in which the tubes are attached to your pitot tube matters. If you set this to 0 then the first (often the top) connector on the sensor needs to be the stagnation pressure (the pressure at the tip of the pitot tube). If set to 1 then the second (often the bottom) connector needs to be the stagnation pressure. If set to 2 (the default) then the airspeed driver will accept either order. The reason you may wish to specify the order is it will allow your airspeed sensor to detect if the aircraft is receiving excessive pressure on the static port compared to the stagnation port such as during a stall, which would otherwise be seen as a positive airspeed.
// @User: Advanced
// @Values: 0:Normal,1:Swapped,2:Auto Detect
AP_GROUPINFO("_TUBE_ORDER", 6, AP_Airspeed, param[0].tube_order, 2),
// @Param: _SKIP_CAL
// @DisplayName: Skip airspeed offset calibration on startup
// @Description: This parameter allows you to skip airspeed offset calibration on startup, instead using the offset from the last calibration. This may be desirable if the offset variance between flights for your sensor is low and you want to avoid having to cover the pitot tube on each boot.
// @Values: 0:Disable,1:Enable
// @User: Advanced
AP_GROUPINFO("_SKIP_CAL", 7, AP_Airspeed, param[0].skip_cal, 0),
#endif // HAL_BUILD_AP_PERIPH
// @Param: _PSI_RANGE
// @DisplayName: The PSI range of the device
// @Description: This parameter allows you to set the PSI (pounds per square inch) range for your sensor. You should not change this unless you examine the datasheet for your device
// @User: Advanced
AP_GROUPINFO("_PSI_RANGE", 8, AP_Airspeed, param[0].psi_range, PSI_RANGE_DEFAULT),
#ifndef HAL_BUILD_AP_PERIPH
// @Param: _BUS
// @DisplayName: Airspeed I2C bus
// @Description: Bus number of the I2C bus where the airspeed sensor is connected. May not correspond to board's I2C bus number labels. Retry another bus and reboot if airspeed sensor fails to initialize.
// @Values: 0:Bus0,1:Bus1,2:Bus2
// @RebootRequired: True
// @User: Advanced
AP_GROUPINFO("_BUS", 9, AP_Airspeed, param[0].bus, HAL_AIRSPEED_BUS_DEFAULT),
#endif // HAL_BUILD_AP_PERIPH
#if AIRSPEED_MAX_SENSORS > 1
// @Param: _PRIMARY
// @DisplayName: Primary airspeed sensor
// @Description: This selects which airspeed sensor will be the primary if multiple sensors are found
// @Values: 0:FirstSensor,1:2ndSensor
// @User: Advanced
AP_GROUPINFO("_PRIMARY", 10, AP_Airspeed, primary_sensor, 0),
#endif
#ifndef HAL_BUILD_AP_PERIPH
// @Param: _OPTIONS
// @DisplayName: Airspeed options bitmask
// @Description: Bitmask of options to use with airspeed. 0:Disable use based on airspeed/groundspeed mismatch (see ARSPD_WIND_MAX), 1:Automatically reenable use based on airspeed/groundspeed mismatch recovery (see ARSPD_WIND_MAX) 2:Disable voltage correction, 3:Check that the airspeed is statistically consistent with the navigation EKF vehicle and wind velocity estimates using EKF3 (requires AHRS_EKF_TYPE = 3)
// @Description{Copter, Blimp, Rover, Sub}: This parameter and function is not used by this vehicle. Always set to 0.
// @Bitmask: 0:SpeedMismatchDisable, 1:AllowSpeedMismatchRecovery, 2:DisableVoltageCorrection, 3:UseEkf3Consistency
// @User: Advanced
AP_GROUPINFO("_OPTIONS", 21, AP_Airspeed, _options, OPTIONS_DEFAULT),
// @Param: _WIND_MAX
// @DisplayName: Maximum airspeed and ground speed difference
// @Description: If the difference between airspeed and ground speed is greater than this value the sensor will be marked unhealthy. Using ARSPD_OPTION this health value can be used to disable the sensor.
// @Description{Copter, Blimp, Rover, Sub}: This parameter and function is not used by this vehicle. Always set to 0.
// @Units: m/s
// @User: Advanced
AP_GROUPINFO("_WIND_MAX", 22, AP_Airspeed, _wind_max, 0),
// @Param: _WIND_WARN
// @DisplayName: Airspeed and ground speed difference that gives a warning
// @Description: If the difference between airspeed and ground speed is greater than this value the sensor will issue a warning. If 0 ARSPD_WIND_MAX is used.
// @Description{Copter, Blimp, Rover, Sub}: This parameter and function is not used by this vehicle. Always set to 0.
// @Units: m/s
// @User: Advanced
AP_GROUPINFO("_WIND_WARN", 23, AP_Airspeed, _wind_warn, 0),
// @Param: _WIND_GATE
// @DisplayName: Re-enable Consistency Check Gate Size
// @Description: Number of standard deviations applied to the re-enable EKF consistency check that is used when ARSPD_OPTIONS bit position 3 is set. Larger values will make the re-enabling of the airspeed sensor faster, but increase the likelihood of re-enabling a degraded sensor. The value can be tuned by using the ARSP.TR log message by setting ARSP_WIND_GATE to a value that is higher than the value for ARSP.TR observed with a healthy airspeed sensor. Occasional transients in ARSP.TR above the value set by ARSP_WIND_GATE can be tolerated provided they are less than 5 seconds in duration and less than 10% duty cycle.
// @Description{Copter, Blimp, Rover, Sub}: This parameter and function is not used by this vehicle.
// @Range: 0.0 10.0
// @User: Advanced
AP_GROUPINFO("_WIND_GATE", 26, AP_Airspeed, _wind_gate, 5.0f),
// @Param: _OFF_PCNT
// @DisplayName: Maximum offset cal speed error
// @Description: The maximum percentage speed change in airspeed reports that is allowed due to offset changes between calibraions before a warning is issued. This potential speed error is in percent of ASPD_FBW_MIN. 0 disables. Helps warn of calibrations without pitot being covered.
// @Range: 0.0 10.0
// @Units: %
// @User: Advanced
AP_GROUPINFO_FRAME("_OFF_PCNT", 27, AP_Airspeed, max_speed_pcnt, 0, AP_PARAM_FRAME_PLANE),
#endif
#if AIRSPEED_MAX_SENSORS > 1
// @Param: 2_TYPE
// @DisplayName: Second Airspeed type
// @Description: Type of 2nd airspeed sensor
// @Values: 0:None,1:I2C-MS4525D0,2:Analog,3:I2C-MS5525,4:I2C-MS5525 (0x76),5:I2C-MS5525 (0x77),6:I2C-SDP3X,7:I2C-DLVR-5in,8:DroneCAN,9:I2C-DLVR-10in,10:I2C-DLVR-20in,11:I2C-DLVR-30in,12:I2C-DLVR-60in,13:NMEA water speed,14:MSP,15:ASP5033
// @User: Standard
AP_GROUPINFO_FLAGS("2_TYPE", 11, AP_Airspeed, param[1].type, 0, AP_PARAM_FLAG_ENABLE),
#ifndef HAL_BUILD_AP_PERIPH
// @Param: 2_USE
// @DisplayName: Enable use of 2nd airspeed sensor
// @Description: use airspeed for flight control. When set to 0 airspeed sensor can be logged and displayed on a GCS but won't be used for flight. When set to 1 it will be logged and used. When set to 2 it will be only used when the throttle is zero, which can be useful in gliders with airspeed sensors behind a propeller
// @Description{Copter, Blimp, Rover, Sub}: This parameter and function is not used by this vehicle. Always set to 0.
// @Values: 0:Don't Use,1:use,2:UseWhenZeroThrottle
// @User: Standard
AP_GROUPINFO("2_USE", 12, AP_Airspeed, param[1].use, 0),
// @Param: 2_OFFSET
// @DisplayName: Airspeed offset for 2nd airspeed sensor
// @Description: Airspeed calibration offset
// @Increment: 0.1
// @User: Advanced
AP_GROUPINFO("2_OFFSET", 13, AP_Airspeed, param[1].offset, 0),
// @Param: 2_RATIO
// @DisplayName: Airspeed ratio for 2nd airspeed sensor
// @Description: Airspeed calibration ratio
// @Increment: 0.1
// @User: Advanced
AP_GROUPINFO("2_RATIO", 14, AP_Airspeed, param[1].ratio, 2),
// @Param: 2_PIN
// @DisplayName: Airspeed pin for 2nd airspeed sensor
// @Description: Pin number indicating location of analog airspeed sensors. Pixhawk/Cube if set to 15.
// @User: Advanced
AP_GROUPINFO("2_PIN", 15, AP_Airspeed, param[1].pin, 0),
#endif
#if AP_AIRSPEED_AUTOCAL_ENABLE
// @Param: 2_AUTOCAL
// @DisplayName: Automatic airspeed ratio calibration for 2nd airspeed sensor
// @Description: If this is enabled then the autopilot will automatically adjust the ARSPD_RATIO during flight, based upon an estimation filter using ground speed and true airspeed. The automatic calibration will save the new ratio to EEPROM every 2 minutes if it changes by more than 5%. This option should be enabled for a calibration flight then disabled again when calibration is complete. Leaving it enabled all the time is not recommended.
// @Description{Copter, Blimp, Rover, Sub}: This parameter and function is not used by this vehicle. Always set to 0.
// @User: Advanced
AP_GROUPINFO("2_AUTOCAL", 16, AP_Airspeed, param[1].autocal, 0),
#endif
#ifndef HAL_BUILD_AP_PERIPH
// @Param: 2_TUBE_ORDR
// @DisplayName: Control pitot tube order of 2nd airspeed sensor
// @Description: This parameter allows you to control whether the order in which the tubes are attached to your pitot tube matters. If you set this to 0 then the first (often the top) connector on the sensor needs to be the stagnation pressure (the pressure at the tip of the pitot tube). If set to 1 then the second (often the bottom) connector needs to be the stagnation pressure. If set to 2 (the default) then the airspeed driver will accept either order. The reason you may wish to specify the order is it will allow your airspeed sensor to detect if the aircraft is receiving excessive pressure on the static port compared to the stagnation port such as during a stall, which would otherwise be seen as a positive airspeed.
// @User: Advanced
// @Values: 0:Normal,1:Swapped,2:Auto Detect
AP_GROUPINFO("2_TUBE_ORDR", 17, AP_Airspeed, param[1].tube_order, 2),
// @Param: 2_SKIP_CAL
// @DisplayName: Skip airspeed offset calibration on startup for 2nd sensor
// @Description: This parameter allows you to skip airspeed offset calibration on startup, instead using the offset from the last calibration. This may be desirable if the offset variance between flights for your sensor is low and you want to avoid having to cover the pitot tube on each boot.
// @Values: 0:Disable,1:Enable
// @User: Advanced
AP_GROUPINFO("2_SKIP_CAL", 18, AP_Airspeed, param[1].skip_cal, 0),
#endif
// @Param: 2_PSI_RANGE
// @DisplayName: The PSI range of the device for 2nd sensor
// @Description: This parameter allows you to set the PSI (pounds per square inch) range for your sensor. You should not change this unless you examine the datasheet for your device
// @User: Advanced
AP_GROUPINFO("2_PSI_RANGE", 19, AP_Airspeed, param[1].psi_range, PSI_RANGE_DEFAULT),
#ifndef HAL_BUILD_AP_PERIPH
// @Param: 2_BUS
// @DisplayName: Airspeed I2C bus for 2nd sensor
// @Description: Bus number of the I2C bus where the airspeed sensor is connected. May not correspond to board's I2C bus number labels. Retry another bus and reboot if airspeed sensor fails to initialize.
// @Values: 0:Bus0,1:Bus1,2:Bus2
// @RebootRequired: True
// @User: Advanced
AP_GROUPINFO("2_BUS", 20, AP_Airspeed, param[1].bus, 1),
#endif
#if AIRSPEED_MAX_SENSORS > 1
// @Param: 2_DEVID
// @DisplayName: Airspeed2 ID
// @Description: Airspeed2 sensor ID, taking into account its type, bus and instance
// @ReadOnly: True
// @User: Advanced
AP_GROUPINFO_FLAGS("2_DEVID", 25, AP_Airspeed, param[1].bus_id, 0, AP_PARAM_FLAG_INTERNAL_USE_ONLY),
#endif
#endif // AIRSPEED_MAX_SENSORS
// Note that 21, 22, 23, 24, 25 and 26 are used above by the _OPTIONS, _DEVID, __WIND_MAX, _WIND_WARN and _WIND_GATE parameters. Do not use them!!
// NOTE: Index 63 is used by AIRSPEED_TYPE, Do not use it!: AP_Param converts an index of 0 to 63 so that the index may be bit shifted
AP_GROUPEND
};
/*
this scaling factor converts from the old system where we used a
0 to 4095 raw ADC value for 0-5V to the new system which gets the
voltage in volts directly from the ADC driver
*/
#define SCALING_OLD_CALIBRATION 819 // 4095/5
AP_Airspeed::AP_Airspeed()
{
AP_Param::setup_object_defaults(this, var_info);
if (_singleton != nullptr) {
AP_HAL::panic("AP_Airspeed must be singleton");
}
_singleton = this;
}
void AP_Airspeed::set_fixedwing_parameters(const AP_FixedWing *_fixed_wing_parameters)
{
fixed_wing_parameters = _fixed_wing_parameters;
}
// macro for use by HAL_INS_PROBE_LIST
#define GET_I2C_DEVICE(bus, address) hal.i2c_mgr->get_device(bus, address)
bool AP_Airspeed::add_backend(AP_Airspeed_Backend *backend)
{
if (!backend) {
return false;
}
if (num_sensors >= AIRSPEED_MAX_SENSORS) {
AP_HAL::panic("Too many airspeed drivers");
}
const uint8_t i = num_sensors;
sensor[num_sensors++] = backend;
if (!sensor[i]->init()) {
GCS_SEND_TEXT(MAV_SEVERITY_ERROR, "Airspeed %u init failed", i+1);
delete sensor[i];
sensor[i] = nullptr;
}
return true;
}
/*
macro to add a backend with check for too many sensors
We don't try to start more than the maximum allowed
*/
#define ADD_BACKEND(backend) \
do { add_backend(backend); \
if (num_sensors == AIRSPEED_MAX_SENSORS) { return; } \
} while (0)
void AP_Airspeed::init()
{
if (sensor[0] != nullptr) {
// already initialised
return;
}
#ifndef HAL_BUILD_AP_PERIPH
// cope with upgrade from old system
if (param[0].pin.load() && param[0].pin.get() != 65) {
param[0].type.set_default(TYPE_ANALOG);
}
// Switch to dedicated WIND_MAX param
// PARAMETER_CONVERSION - Added: Oct-2020
const float ahrs_max_wind = AP::ahrs().get_max_wind();
if (!_wind_max.configured() && is_positive(ahrs_max_wind)) {
_wind_max.set_and_save(ahrs_max_wind);
// Turn off _options to override the new default
if (!_options.configured()) {
_options.set_and_save(0);
}
}
#endif
#ifdef HAL_AIRSPEED_PROBE_LIST
// load sensors via a list from hwdef.dat
HAL_AIRSPEED_PROBE_LIST;
#else
// look for sensors based on type parameters
for (uint8_t i=0; i<AIRSPEED_MAX_SENSORS; i++) {
#if AP_AIRSPEED_AUTOCAL_ENABLE
state[i].calibration.init(param[i].ratio);
state[i].last_saved_ratio = param[i].ratio;
#endif
// Set the enable automatically to false and set the probability that the airspeed is healhy to start with
state[i].failures.health_probability = 1.0f;
switch ((enum airspeed_type)param[i].type.get()) {
case TYPE_NONE:
// nothing to do
break;
case TYPE_I2C_MS4525:
#if AP_AIRSPEED_MS4525_ENABLED
sensor[i] = new AP_Airspeed_MS4525(*this, i);
#endif
break;
case TYPE_SITL:
#if AP_AIRSPEED_SITL_ENABLED
sensor[i] = new AP_Airspeed_SITL(*this, i);
#endif
break;
case TYPE_ANALOG:
#if AP_AIRSPEED_ANALOG_ENABLED
sensor[i] = new AP_Airspeed_Analog(*this, i);
#endif
break;
case TYPE_I2C_MS5525:
#if AP_AIRSPEED_MS5525_ENABLED
sensor[i] = new AP_Airspeed_MS5525(*this, i, AP_Airspeed_MS5525::MS5525_ADDR_AUTO);
#endif
break;
case TYPE_I2C_MS5525_ADDRESS_1:
#if AP_AIRSPEED_MS5525_ENABLED
sensor[i] = new AP_Airspeed_MS5525(*this, i, AP_Airspeed_MS5525::MS5525_ADDR_1);
#endif
break;
case TYPE_I2C_MS5525_ADDRESS_2:
#if AP_AIRSPEED_MS5525_ENABLED
sensor[i] = new AP_Airspeed_MS5525(*this, i, AP_Airspeed_MS5525::MS5525_ADDR_2);
#endif
break;
case TYPE_I2C_SDP3X:
#if AP_AIRSPEED_SDP3X_ENABLED
sensor[i] = new AP_Airspeed_SDP3X(*this, i);
#endif
break;
case TYPE_I2C_DLVR_5IN:
#if AP_AIRSPEED_DLVR_ENABLED
sensor[i] = new AP_Airspeed_DLVR(*this, i, 5);
#endif
break;
case TYPE_I2C_DLVR_10IN:
#if AP_AIRSPEED_DLVR_ENABLED
sensor[i] = new AP_Airspeed_DLVR(*this, i, 10);
#endif
break;
case TYPE_I2C_DLVR_20IN:
#if AP_AIRSPEED_DLVR_ENABLED
sensor[i] = new AP_Airspeed_DLVR(*this, i, 20);
#endif
break;
case TYPE_I2C_DLVR_30IN:
#if AP_AIRSPEED_DLVR_ENABLED
sensor[i] = new AP_Airspeed_DLVR(*this, i, 30);
#endif
break;
case TYPE_I2C_DLVR_60IN:
#if AP_AIRSPEED_DLVR_ENABLED
sensor[i] = new AP_Airspeed_DLVR(*this, i, 60);
#endif // AP_AIRSPEED_DLVR_ENABLED
break;
case TYPE_I2C_ASP5033:
#if AP_AIRSPEED_ASP5033_ENABLED
sensor[i] = new AP_Airspeed_ASP5033(*this, i);
#endif
break;
case TYPE_UAVCAN:
#if AP_AIRSPEED_UAVCAN_ENABLED
sensor[i] = AP_Airspeed_UAVCAN::probe(*this, i, uint32_t(param[i].bus_id.get()));
#endif
break;
case TYPE_NMEA_WATER:
#if AP_AIRSPEED_NMEA_ENABLED
#if APM_BUILD_TYPE(APM_BUILD_Rover) || APM_BUILD_TYPE(APM_BUILD_ArduSub)
sensor[i] = new AP_Airspeed_NMEA(*this, i);
#endif
#endif
break;
case TYPE_MSP:
#if AP_AIRSPEED_MSP_ENABLED
sensor[i] = new AP_Airspeed_MSP(*this, i, 0);
#endif
break;
}
if (sensor[i] && !sensor[i]->init()) {
GCS_SEND_TEXT(MAV_SEVERITY_ERROR, "Airspeed %u init failed", i + 1);
delete sensor[i];
sensor[i] = nullptr;
}
if (sensor[i] != nullptr) {
num_sensors = i+1;
}
}
#if AP_AIRSPEED_UAVCAN_ENABLED
// we need a 2nd pass for DroneCAN sensors so we can match order by DEVID
// the 2nd pass accepts any devid
for (uint8_t i=0; i<AIRSPEED_MAX_SENSORS; i++) {
if (sensor[i] == nullptr && (enum airspeed_type)param[i].type.get() == TYPE_UAVCAN) {
sensor[i] = AP_Airspeed_UAVCAN::probe(*this, i, 0);
if (sensor[i] != nullptr) {
num_sensors = i+1;
}
}
}
#endif // AP_AIRSPEED_UAVCAN_ENABLED
#endif // HAL_AIRSPEED_PROBE_LIST
// set DEVID to zero for any sensors not found. This allows backends to order
// based on previous value of DEVID. This allows for swapping out sensors
for (uint8_t i=0; i<AIRSPEED_MAX_SENSORS; i++) {
if (sensor[i] == nullptr) {
// note we use set() not set_and_save() to allow a sensor to be temporarily
// removed for one boot without losing its slot
param[i].bus_id.set(0);
}
}
}
// read the airspeed sensor
float AP_Airspeed::get_pressure(uint8_t i)
{
if (!enabled(i)) {
return 0;
}
float pressure = 0;
if (sensor[i]) {
state[i].healthy = sensor[i]->get_differential_pressure(pressure);
}
return pressure;
}
// get a temperature reading if possible
bool AP_Airspeed::get_temperature(uint8_t i, float &temperature)
{
if (!enabled(i)) {
return false;
}
if (sensor[i]) {
return sensor[i]->get_temperature(temperature);
}
return false;
}
// calibrate the zero offset for the airspeed. This must be called at
// least once before the get_airspeed() interface can be used
void AP_Airspeed::calibrate(bool in_startup)
{
#ifndef HAL_BUILD_AP_PERIPH
if (hal.util->was_watchdog_reset()) {
GCS_SEND_TEXT(MAV_SEVERITY_INFO,"Airspeed: skipping cal");
return;
}
for (uint8_t i=0; i<AIRSPEED_MAX_SENSORS; i++) {
if (!enabled(i)) {
continue;
}
if (state[i].use_zero_offset) {
param[i].offset.set(0);
continue;
}
if (in_startup && param[i].skip_cal) {
continue;
}
if (sensor[i] == nullptr) {
GCS_SEND_TEXT(MAV_SEVERITY_ERROR, "Airspeed %u not initalized, cannot cal", i+1);
continue;
}
state[i].cal.start_ms = AP_HAL::millis();
state[i].cal.count = 0;
state[i].cal.sum = 0;
state[i].cal.read_count = 0;
GCS_SEND_TEXT(MAV_SEVERITY_INFO,"Airspeed %u calibration started", i+1);
}
#endif // HAL_BUILD_AP_PERIPH
}
/*
update async airspeed zero offset calibration
*/
void AP_Airspeed::update_calibration(uint8_t i, float raw_pressure)
{
#ifndef HAL_BUILD_AP_PERIPH
if (!enabled(i) || state[i].cal.start_ms == 0) {
return;
}
// consider calibration complete when we have at least 15 samples
// over at least 1 second
if (AP_HAL::millis() - state[i].cal.start_ms >= 1000 &&
state[i].cal.read_count > 15) {
if (state[i].cal.count == 0) {
GCS_SEND_TEXT(MAV_SEVERITY_WARNING, "Airspeed %u unhealthy", i + 1);
} else {
GCS_SEND_TEXT(MAV_SEVERITY_INFO, "Airspeed %u calibrated", i + 1);
float calibrated_offset = state[i].cal.sum / state[i].cal.count;
// check if new offset differs too greatly from last calibration, indicating pitot uncovered in wind
if (fixed_wing_parameters != nullptr) {
float airspeed_min = fixed_wing_parameters->airspeed_min.get();
// use percentage of ARSPD_FBW_MIN as criteria for max allowed change in offset
float max_change = 0.5*(sq((1 + (max_speed_pcnt * 0.01))*airspeed_min) - sq(airspeed_min));
if (max_speed_pcnt > 0 && (abs(calibrated_offset-param[i].offset) > max_change) && (abs(param[i].offset) > 0)) {
GCS_SEND_TEXT(MAV_SEVERITY_WARNING, "Arspd %d offset change large;cover and recal", i +1);
}
}
param[i].offset.set_and_save(calibrated_offset);
}
state[i].cal.start_ms = 0;
return;
}
// we discard the first 5 samples
if (state[i].healthy && state[i].cal.read_count > 5) {
state[i].cal.sum += raw_pressure;
state[i].cal.count++;
}
state[i].cal.read_count++;
#endif // HAL_BUILD_AP_PERIPH
}
// read one airspeed sensor
void AP_Airspeed::read(uint8_t i)
{
if (!enabled(i) || !sensor[i]) {
return;
}
state[i].last_update_ms = AP_HAL::millis();
// try and get a direct reading of airspeed
if (sensor[i]->has_airspeed()) {
state[i].healthy = sensor[i]->get_airspeed(state[i].airspeed);
state[i].raw_airspeed = state[i].airspeed; // for logging
return;
}
float raw_pressure = get_pressure(i);
float airspeed_pressure = raw_pressure - get_offset(i);
// remember raw pressure for logging
state[i].corrected_pressure = airspeed_pressure;
#ifndef HAL_BUILD_AP_PERIPH
bool prev_healthy = state[i].healthy;
if (state[i].cal.start_ms != 0) {
update_calibration(i, raw_pressure);
}
// filter before clamping positive
if (!prev_healthy) {
// if the previous state was not healthy then we should not
// use an IIR filter, otherwise a bad reading will last for
// some time after the sensor becomees healthy again
state[i].filtered_pressure = airspeed_pressure;
} else {
state[i].filtered_pressure = 0.7f * state[i].filtered_pressure + 0.3f * airspeed_pressure;
}
/*
we support different pitot tube setups so user can choose if
they want to be able to detect pressure on the static port
*/
switch ((enum pitot_tube_order)param[i].tube_order.get()) {
case PITOT_TUBE_ORDER_NEGATIVE:
state[i].last_pressure = -airspeed_pressure;
state[i].raw_airspeed = sqrtf(MAX(-airspeed_pressure, 0) * param[i].ratio);
state[i].airspeed = sqrtf(MAX(-state[i].filtered_pressure, 0) * param[i].ratio);
break;
case PITOT_TUBE_ORDER_POSITIVE:
state[i].last_pressure = airspeed_pressure;
state[i].raw_airspeed = sqrtf(MAX(airspeed_pressure, 0) * param[i].ratio);
state[i].airspeed = sqrtf(MAX(state[i].filtered_pressure, 0) * param[i].ratio);
break;
case PITOT_TUBE_ORDER_AUTO:
default:
state[i].last_pressure = fabsf(airspeed_pressure);
state[i].raw_airspeed = sqrtf(fabsf(airspeed_pressure) * param[i].ratio);
state[i].airspeed = sqrtf(fabsf(state[i].filtered_pressure) * param[i].ratio);
break;
}
#endif // HAL_BUILD_AP_PERIPH
}
// read all airspeed sensors
void AP_Airspeed::update()
{
for (uint8_t i=0; i<AIRSPEED_MAX_SENSORS; i++) {
read(i);
}
#if HAL_GCS_ENABLED
// debugging until we get MAVLink support for 2nd airspeed sensor
if (enabled(1)) {
gcs().send_named_float("AS2", get_airspeed(1));
}
#endif
#if HAL_LOGGING_ENABLED
const uint8_t old_primary = primary;
#endif
// setup primary
if (healthy(primary_sensor.get())) {
primary = primary_sensor.get();
} else {
for (uint8_t i=0; i<AIRSPEED_MAX_SENSORS; i++) {
if (healthy(i)) {
primary = i;
break;
}
}
}
check_sensor_failures();
#if HAL_LOGGING_ENABLED
if (primary != old_primary) {
AP::logger().Write_Event(LogEvent::AIRSPEED_PRIMARY_CHANGED);
}
if (_log_bit != (uint32_t)-1 && AP::logger().should_log(_log_bit)) {
Log_Airspeed();
}
#endif
}
#if AP_AIRSPEED_MSP_ENABLED
/*
handle MSP airspeed data
*/
void AP_Airspeed::handle_msp(const MSP::msp_airspeed_data_message_t &pkt)
{
if (pkt.instance > 1) {
return; //supporting 2 airspeed sensors at most
}
for (uint8_t i=0; i<AIRSPEED_MAX_SENSORS; i++) {
if (sensor[i]) {
sensor[i]->handle_msp(pkt);
}
}
}
#endif
// @LoggerMessage: HYGR
// @Description: Hygrometer data
// @Field: TimeUS: Time since system startup
// @Field: Id: sensor ID
// @Field: Humidity: percentage humidity
// @Field: Temp: temperature in degrees C
void AP_Airspeed::Log_Airspeed()
{
const uint64_t now = AP_HAL::micros64();
for (uint8_t i=0; i<AIRSPEED_MAX_SENSORS; i++) {
if (!enabled(i) || sensor[i] == nullptr) {
continue;
}
float temperature;
if (!get_temperature(i, temperature)) {
temperature = 0;
}
const struct log_ARSP pkt{
LOG_PACKET_HEADER_INIT(LOG_ARSP_MSG),
time_us : now,
instance : i,
airspeed : get_raw_airspeed(i),
diffpressure : get_differential_pressure(i),
temperature : (int16_t)(temperature * 100.0f),
rawpressure : get_corrected_pressure(i),
offset : get_offset(i),
use : use(i),
healthy : healthy(i),
health_prob : get_health_probability(i),
test_ratio : get_test_ratio(i),
primary : get_primary()
};
AP::logger().WriteBlock(&pkt, sizeof(pkt));
#if AP_AIRSPEED_HYGROMETER_ENABLE
struct {
uint32_t sample_ms;
float temperature;
float humidity;
} hygrometer;
if (sensor[i]->get_hygrometer(hygrometer.sample_ms, hygrometer.temperature, hygrometer.humidity) &&
hygrometer.sample_ms != state[i].last_hygrometer_log_ms) {
AP::logger().WriteStreaming("HYGR",
"TimeUS,Id,Humidity,Temp",
"s#%O",
"F---",
"QBff",
AP_HAL::micros64(),
i,
hygrometer.humidity,
hygrometer.temperature);
state[i].last_hygrometer_log_ms = hygrometer.sample_ms;
}
#endif
}
}
bool AP_Airspeed::use(uint8_t i) const
{
#ifndef HAL_BUILD_AP_PERIPH
if (_force_disable_use) {
return false;
}
if (!enabled(i) || !param[i].use) {
return false;
}
if (param[i].use == 2 && !is_zero(SRV_Channels::get_output_scaled(SRV_Channel::k_throttle))) {
// special case for gliders with airspeed sensors behind the
// propeller. Allow airspeed to be disabled when throttle is
// running
return false;
}
return true;
#else
return false;
#endif // HAL_BUILD_AP_PERIPH
}
/*
return true if all enabled sensors are healthy
*/
bool AP_Airspeed::all_healthy(void) const
{
for (uint8_t i=0; i<AIRSPEED_MAX_SENSORS; i++) {
if (enabled(i) && !healthy(i)) {
return false;
}
}
return true;
}
// return true if airspeed is enabled
bool AP_Airspeed::enabled(uint8_t i) const {
if (i < AIRSPEED_MAX_SENSORS) {
return param[i].type.get() != TYPE_NONE;
}
return false;
}
// return health status of sensor
bool AP_Airspeed::healthy(uint8_t i) const {
bool ok = state[i].healthy && enabled(i) && sensor[i] != nullptr;
#ifndef HAL_BUILD_AP_PERIPH
// sanity check the offset parameter. Zero is permitted if we are skipping calibration.
ok &= (fabsf(param[i].offset) > 0 || state[i].use_zero_offset || param[i].skip_cal);
#endif
return ok;
}
// return the current airspeed in m/s
float AP_Airspeed::get_airspeed(uint8_t i) const {
if (!enabled(i)) {
// we can't have negative airspeed so sending an obviously invalid value
return -1.0;
}
return state[i].airspeed;
}
// return the unfiltered airspeed in m/s
float AP_Airspeed::get_raw_airspeed(uint8_t i) const {
if (!enabled(i)) {
// we can't have negative airspeed so sending an obviously invalid value
return -1.0;
}
return state[i].raw_airspeed;
}
// return the differential pressure in Pascal for the last airspeed reading
float AP_Airspeed::get_differential_pressure(uint8_t i) const {
if (!enabled(i)) {
return 0.0;
}
return state[i].last_pressure;
}
// return the current corrected pressure
float AP_Airspeed::get_corrected_pressure(uint8_t i) const {
if (!enabled(i)) {
return 0.0;
}
return state[i].corrected_pressure;
}
#if AP_AIRSPEED_HYGROMETER_ENABLE
bool AP_Airspeed::get_hygrometer(uint8_t i, uint32_t &last_sample_ms, float &temperature, float &humidity) const
{
if (!enabled(i) || sensor[i] == nullptr) {
return false;
}
return sensor[i]->get_hygrometer(last_sample_ms, temperature, humidity);
}
#endif // AP_AIRSPEED_HYGROMETER_ENABLE
#else // build type is not appropriate; provide a dummy implementation:
const AP_Param::GroupInfo AP_Airspeed::var_info[] = { AP_GROUPEND };
void AP_Airspeed::update() {};
bool AP_Airspeed::get_temperature(uint8_t i, float &temperature) { return false; }
void AP_Airspeed::calibrate(bool in_startup) {}
bool AP_Airspeed::use(uint8_t i) const { return false; }
bool AP_Airspeed::enabled(uint8_t i) const { return false; }
bool AP_Airspeed::healthy(uint8_t i) const { return false; }
float AP_Airspeed::get_airspeed(uint8_t i) const { return 0.0; }
float AP_Airspeed::get_differential_pressure(uint8_t i) const { return 0.0; }
#if AP_AIRSPEED_MSP_ENABLED
void AP_Airspeed::handle_msp(const MSP::msp_airspeed_data_message_t &pkt) {}
#endif
bool AP_Airspeed::all_healthy(void) const { return false; }
void AP_Airspeed::init(void) {};
AP_Airspeed::AP_Airspeed() {}
#endif // #if AP_AIRSPEED_DUMMY_METHODS_ENABLED
// singleton instance
AP_Airspeed *AP_Airspeed::_singleton;
namespace AP {
AP_Airspeed *airspeed()
{
return AP_Airspeed::get_singleton();
}
};
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