ardupilot/libraries/AP_TECS/AP_TECS.h

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// -*- tab-width: 4; Mode: C++; c-basic-offset: 4; indent-tabs-mode: t -*-
/// @file AP_TECS.h
/// @brief Combined Total Energy Speed & Height Control. This is a instance of an
/// AP_SpdHgtControl class
/*
* Written by Paul Riseborough 2013 to provide:
* - Combined control of speed and height using throttle to control
* total energy and pitch angle to control exchange of energy between
* potential and kinetic.
* Selectable speed or height priority modes when calculating pitch angle
* - Fallback mode when no airspeed measurement is available that
* sets throttle based on height rate demand and switches pitch angle control to
* height priority
* - Underspeed protection that demands maximum throttle switches pitch angle control
* to speed priority mode
* - Relative ease of tuning through use of intuitive time constant, trim rate and damping parameters and the use
* of easy to measure aircraft performance data
*/
#ifndef AP_TECS_H
#define AP_TECS_H
#include <AP_Math/AP_Math.h>
#include <AP_AHRS/AP_AHRS.h>
#include <AP_Param/AP_Param.h>
#include <AP_Vehicle/AP_Vehicle.h>
#include <AP_SpdHgtControl/AP_SpdHgtControl.h>
#include <DataFlash/DataFlash.h>
class AP_TECS : public AP_SpdHgtControl {
public:
AP_TECS(AP_AHRS &ahrs, const AP_Vehicle::FixedWing &parms) :
_ahrs(ahrs),
aparm(parms)
{
AP_Param::setup_object_defaults(this, var_info);
}
// Update of the estimated height and height rate internal state
// Update of the inertial speed rate internal state
// Should be called at 50Hz or greater
// hgt_afe is the height above field elevation (takeoff height)
void update_50hz(float hgt_afe);
// Update the control loop calculations
void update_pitch_throttle(int32_t hgt_dem_cm,
int32_t EAS_dem_cm,
enum FlightStage flight_stage,
int32_t ptchMinCO_cd,
int16_t throttle_nudge,
float hgt_afe,
float load_factor);
// demanded throttle in percentage
// should return 0 to 100
int32_t get_throttle_demand(void) {return int32_t(_throttle_dem * 100.0f);}
// demanded pitch angle in centi-degrees
// should return between -9000 to +9000
int32_t get_pitch_demand(void) { return int32_t(_pitch_dem * 5729.5781f);}
// Rate of change of velocity along X body axis in m/s^2
float get_VXdot(void) { return _vel_dot; }
// log data on internal state of the controller. Called at 10Hz
void log_data(DataFlash_Class &dataflash, uint8_t msgid);
// return current target airspeed
float get_target_airspeed(void) const { return _TAS_dem / _ahrs.get_EAS2TAS(); }
// return maximum climb rate
float get_max_climbrate(void) const { return _maxClimbRate; }
// return landing sink rate
float get_land_sinkrate(void) const { return _land_sink; }
// this supports the TECS_* user settable parameters
static const struct AP_Param::GroupInfo var_info[];
struct PACKED log_TECS_Tuning {
LOG_PACKET_HEADER;
uint64_t time_us;
float hgt;
float dhgt;
float hgt_dem;
float dhgt_dem;
float spd_dem;
float spd;
float dspd;
float ithr;
float iptch;
float thr;
float ptch;
float dspd_dem;
} log_tuning;
private:
// Last time update_50Hz was called
uint32_t _update_50hz_last_usec;
// Last time update_speed was called
uint32_t _update_speed_last_usec;
// Last time update_pitch_throttle was called
uint32_t _update_pitch_throttle_last_usec;
// reference to the AHRS object
AP_AHRS &_ahrs;
const AP_Vehicle::FixedWing &aparm;
// TECS tuning parameters
AP_Float _hgtCompFiltOmega;
AP_Float _spdCompFiltOmega;
AP_Float _maxClimbRate;
AP_Float _minSinkRate;
AP_Float _maxSinkRate;
AP_Float _timeConst;
AP_Float _landTimeConst;
AP_Float _ptchDamp;
AP_Float _landDamp;
AP_Float _thrDamp;
AP_Float _integGain;
AP_Float _vertAccLim;
AP_Float _rollComp;
AP_Float _spdWeight;
AP_Float _spdWeightLand;
AP_Float _landThrottle;
AP_Float _landAirspeed;
AP_Float _land_sink;
AP_Int8 _pitch_max;
AP_Int8 _pitch_min;
AP_Int8 _land_pitch_max;
// throttle demand in the range from 0.0 to 1.0
float _throttle_dem;
// pitch angle demand in radians
float _pitch_dem;
// Integrator state 1 - height filter second derivative
float _integ1_state;
// Integrator state 2 - height rate
float _climb_rate;
// Integrator state 3 - height
float _integ3_state;
// Integrator state 4 - airspeed filter first derivative
float _integ4_state;
// Integrator state 5 - true airspeed
float _integ5_state;
// Integrator state 6 - throttle integrator
float _integ6_state;
// Integrator state 6 - pitch integrator
float _integ7_state;
// throttle demand rate limiter state
float _last_throttle_dem;
// pitch demand rate limiter state
float _last_pitch_dem;
// Rate of change of speed along X axis
float _vel_dot;
// Equivalent airspeed
float _EAS;
// True airspeed limits
float _TASmax;
float _TASmin;
// Current and last true airspeed demand
float _TAS_dem;
float _TAS_dem_last;
// Equivalent airspeed demand
float _EAS_dem;
// height demands
float _hgt_dem;
float _hgt_dem_in_old;
float _hgt_dem_adj;
float _hgt_dem_adj_last;
float _hgt_rate_dem;
float _hgt_dem_prev;
float _land_hgt_dem;
// Speed demand after application of rate limiting
// This is the demand tracked by the TECS control loops
float _TAS_dem_adj;
// Speed rate demand after application of rate limiting
// This is the demand tracked by the TECS control loops
float _TAS_rate_dem;
// Total energy rate filter state
float _STEdotErrLast;
// Underspeed condition
bool _underspeed;
// Bad descent condition caused by unachievable airspeed demand
bool _badDescent;
// climbout mode
enum FlightStage _flight_stage;
// pitch demand before limiting
float _pitch_dem_unc;
// Maximum and minimum specific total energy rate limits
float _STEdot_max;
float _STEdot_min;
// Maximum and minimum floating point throttle limits
float _THRmaxf;
float _THRminf;
// Maximum and minimum floating point pitch limits
float _PITCHmaxf;
float _PITCHminf;
// Specific energy quantities
float _SPE_dem;
float _SKE_dem;
float _SPEdot_dem;
float _SKEdot_dem;
float _SPE_est;
float _SKE_est;
float _SPEdot;
float _SKEdot;
// Specific energy error quantities
float _STE_error;
// Time since last update of main TECS loop (seconds)
float _DT;
// counter for demanded sink rate on land final
uint8_t _flare_counter;
// Update the airspeed internal state using a second order complementary filter
void _update_speed(float load_factor);
// Update the demanded airspeed
void _update_speed_demand(void);
// Update the demanded height
void _update_height_demand(void);
// Detect an underspeed condition
void _detect_underspeed(void);
// Update Specific Energy Quantities
void _update_energies(void);
// Update Demanded Throttle
void _update_throttle(void);
// Update Demanded Throttle Non-Airspeed
void _update_throttle_option(int16_t throttle_nudge);
// Detect Bad Descent
void _detect_bad_descent(void);
// Update Demanded Pitch Angle
void _update_pitch(void);
// Initialise states and variables
void _initialise_states(int32_t ptchMinCO_cd, float hgt_afe);
// Calculate specific total energy rate limits
void _update_STE_rate_lim(void);
// declares a 5point average filter using floats
AverageFilterFloat_Size5 _vdot_filter;
// current time constant
float timeConstant(void) const;
};
#define TECS_LOG_FORMAT(msg) { msg, sizeof(AP_TECS::log_TECS_Tuning), \
"TECS", "Qffffffffffff", "TimeUS,h,dh,h_dem,dh_dem,sp_dem,sp,dsp,ith,iph,th,ph,dsp_dem" }
#endif //AP_TECS_H