mirror of https://github.com/ArduPilot/ardupilot
AC_AttitudeControl: add SITL panic to remind us to implent the quarternion
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@ -212,6 +212,11 @@ void AC_AttitudeControl::reset_rate_controller_I_terms_smoothly()
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// Command a Quaternion attitude with feedforward and smoothing
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void AC_AttitudeControl::input_quaternion(Quaternion attitude_desired_quat)
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{
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#if CONFIG_HAL_BOARD == HAL_BOARD_SITL
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// this function is not currently used, this is a reminder that we need to add a 6DoF implementation
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AP_HAL::panic("input_quaternion not implemented AC_AttitudeControl_Multi_6DoF");
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#endif
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// calculate the attitude target euler angles
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_attitude_target_quat.to_euler(_attitude_target_euler_angle.x, _attitude_target_euler_angle.y, _attitude_target_euler_angle.z);
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@ -124,6 +124,20 @@ void AC_AttitudeControl_Multi_6DoF::input_angle_step_bf_roll_pitch_yaw(float rol
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AC_AttitudeControl_Multi::input_angle_step_bf_roll_pitch_yaw(roll_angle_step_bf_cd, pitch_angle_step_bf_cd, yaw_angle_step_bf_cd);
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}
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// Command a Quaternion attitude with feedforward and smoothing
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// not used anywhere in current code, panic in SITL so this implementaiton is not overlooked
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void AC_AttitudeControl_Multi_6DoF::input_quaternion(Quaternion attitude_desired_quat) {
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#if CONFIG_HAL_BOARD == HAL_BOARD_SITL
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AP_HAL::panic("input_quaternion not implemented AC_AttitudeControl_Multi_6DoF");
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#endif
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_motors.set_lateral(0.0f);
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_motors.set_forward(0.0f);
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AC_AttitudeControl_Multi::input_quaternion(attitude_desired_quat);
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}
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AC_AttitudeControl_Multi_6DoF *AC_AttitudeControl_Multi_6DoF::_singleton = nullptr;
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#endif // ENABLE_SCRIPTING
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@ -20,10 +20,7 @@ public:
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// Command a Quaternion attitude with feedforward and smoothing
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// not used anywhere in current code, panic so this implementaiton is not overlooked
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void input_quaternion(Quaternion attitude_desired_quat) override {
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AP_HAL::panic("input_quaternion not implemented AC_AttitudeControl_Multi_6DoF");
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}
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void input_quaternion(Quaternion attitude_desired_quat) override;
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/*
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override input functions to attitude controller and convert desired angles into thrust angles and substitute for osset angles
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*/
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