forked from Archive/PX4-Autopilot
Add TECS logging
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@ -146,6 +146,7 @@ private:
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int _range_finder_sub; /**< range finder subscription */
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orb_advert_t _attitude_sp_pub; /**< attitude setpoint */
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orb_advert_t _tecs_status_pub; /**< TECS status publication */
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orb_advert_t _nav_capabilities_pub; /**< navigation capabilities publication */
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struct vehicle_attitude_s _att; /**< vehicle attitude */
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@ -414,6 +415,7 @@ FixedwingPositionControl::FixedwingPositionControl() :
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/* publications */
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_attitude_sp_pub(-1),
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_tecs_status_pub(-1),
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_nav_capabilities_pub(-1),
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/* states */
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@ -1384,6 +1386,51 @@ void FixedwingPositionControl::tecs_update_pitch_throttle(float alt_sp, float v_
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climbout_mode, climbout_pitch_min_rad,
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throttle_min, throttle_max, throttle_cruise,
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pitch_min_rad, pitch_max_rad);
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struct TECS::tecs_state s;
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_tecs.get_tecs_state(s);
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struct tecs_status_s t;
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t.timestamp = s.timestamp;
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switch (s.mode) {
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case TECS::ECL_TECS_MODE_NORMAL:
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t.mode = TECS_MODE_NORMAL;
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break;
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case TECS::ECL_TECS_MODE_UNDERSPEED:
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t.mode = TECS_MODE_UNDERSPEED;
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break;
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case TECS::ECL_TECS_MODE_BAD_DESCENT:
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t.mode = TECS_MODE_BAD_DESCENT;
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break;
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case TECS::ECL_TECS_MODE_CLIMBOUT:
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t.mode = TECS_MODE_CLIMBOUT;
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break;
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}
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t.altitudeSp = s.hgt_dem;
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t.altitude_filtered = s.hgt;
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t.airspeedSp = s.spd_dem;
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t.airspeed_filtered = s.spd;
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t.flightPathAngleSp = s.dhgt_dem;
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t.flightPathAngle = s.dhgt;
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t.flightPathAngleFiltered = s.dhgt;
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t.airspeedDerivativeSp = s.dspd_dem;
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t.airspeedDerivative = s.dspd;
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t.totalEnergyRateSp = s.thr;
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t.totalEnergyRate = s.ithr;
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t.energyDistributionRateSp = s.ptch;
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t.energyDistributionRate = s.iptch;
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if (_tecs_status_pub > 0) {
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orb_publish(ORB_ID(tecs_status), _tecs_status_pub, &t);
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} else {
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_tecs_status_pub = orb_advertise(ORB_ID(tecs_status), &t);
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}
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}
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}
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