forked from Archive/PX4-Autopilot
Integral fixes, last parts
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@ -62,8 +62,7 @@ float ECL_PitchController::control(float pitch_setpoint, float pitch, float pitc
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/* get the usual dt estimate */
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uint64_t dt_micros = ecl_elapsed_time(&_last_run);
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_last_run = ecl_absolute_time();
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float dt = dt_micros / 1000000;
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float dt = (float)dt_micros * 1e-6f;
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/* lock integral for long intervals */
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if (dt_micros > 500000)
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@ -115,7 +114,7 @@ float ECL_PitchController::control(float pitch_setpoint, float pitch, float pitc
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_rate_error = _rate_setpoint - pitch_rate;
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float ilimit_scaled = 0.0f;
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float ilimit_scaled = _integrator_max * scaler;
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if (!lock_integrator && k_i_rate > 0.0f && airspeed > 0.5f * airspeed_min) {
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@ -64,8 +64,11 @@ float ECL_RollController::control(float roll_setpoint, float roll, float roll_ra
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/* get the usual dt estimate */
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uint64_t dt_micros = ecl_elapsed_time(&_last_run);
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_last_run = ecl_absolute_time();
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float dt = (float)dt_micros * 1e-6f;
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float dt = (dt_micros > 500000) ? 0.0f : dt_micros / 1000000;
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/* lock integral for long intervals */
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if (dt_micros > 500000)
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lock_integrator = true;
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float k_ff = math::max((_k_p - _k_i * _tc) * _tc - _k_d, 0.0f);
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float k_i_rate = _k_i * _tc;
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@ -90,7 +93,7 @@ float ECL_RollController::control(float roll_setpoint, float roll, float roll_ra
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_rate_error = _rate_setpoint - roll_rate;
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float ilimit_scaled = 0.0f;
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float ilimit_scaled = _integrator_max * scaler;
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if (!lock_integrator && k_i_rate > 0.0f && airspeed > 0.5f * airspeed_min) {
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