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fw_pos_control_l1: pass time through from run
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@@ -325,11 +325,14 @@ private:
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*/
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bool update_desired_altitude(float dt);
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bool control_position(const Vector2f &curr_pos, const Vector2f &ground_speed, const position_setpoint_s &pos_sp_prev,
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bool control_position(const hrt_abstime &now, const Vector2f &curr_pos, const Vector2f &ground_speed,
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const position_setpoint_s &pos_sp_prev,
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const position_setpoint_s &pos_sp_curr, const position_setpoint_s &pos_sp_next);
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void control_takeoff(const Vector2f &curr_pos, const Vector2f &ground_speed, const position_setpoint_s &pos_sp_prev,
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void control_takeoff(const hrt_abstime &now, const Vector2f &curr_pos, const Vector2f &ground_speed,
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const position_setpoint_s &pos_sp_prev,
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const position_setpoint_s &pos_sp_curr);
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void control_landing(const Vector2f &curr_pos, const Vector2f &ground_speed, const position_setpoint_s &pos_sp_prev,
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void control_landing(const hrt_abstime &now, const Vector2f &curr_pos, const Vector2f &ground_speed,
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const position_setpoint_s &pos_sp_prev,
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const position_setpoint_s &pos_sp_curr);
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float get_tecs_pitch();
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@@ -349,7 +352,7 @@ private:
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/*
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* Call TECS : a wrapper function to call the TECS implementation
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*/
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void tecs_update_pitch_throttle(float alt_sp, float airspeed_sp,
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void tecs_update_pitch_throttle(const hrt_abstime &now, float alt_sp, float airspeed_sp,
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float pitch_min_rad, float pitch_max_rad,
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float throttle_min, float throttle_max, float throttle_cruise,
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bool climbout_mode, float climbout_pitch_min_rad,
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