2015-05-13 03:09:36 -03:00
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#include "Plane.h"
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2011-09-08 22:29:39 -03:00
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2012-09-11 00:01:36 -03:00
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/*
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get a speed scaling number for control surfaces. This is applied to
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PIDs to change the scaling of the PID with speed. At high speed we
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move the surfaces less, and at low speeds we move them more.
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*/
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2015-05-13 03:09:36 -03:00
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float Plane::get_speed_scaler(void)
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2012-09-11 00:01:36 -03:00
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{
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float aspeed, speed_scaler;
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2012-08-24 09:03:03 -03:00
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if (ahrs.airspeed_estimate(&aspeed)) {
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2014-05-21 07:21:19 -03:00
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if (aspeed > auto_state.highest_airspeed) {
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auto_state.highest_airspeed = aspeed;
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}
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2016-06-04 06:20:18 -03:00
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if (aspeed > 0.0001f) {
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2012-08-21 23:19:50 -03:00
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speed_scaler = g.scaling_speed / aspeed;
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2012-07-15 22:21:50 -03:00
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} else {
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2012-08-21 23:19:50 -03:00
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speed_scaler = 2.0;
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2012-07-15 22:21:50 -03:00
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}
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2018-11-02 00:56:06 -03:00
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// ensure we have scaling over the full configured airspeed
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float scale_min = MIN(0.5, (0.5 * aparm.airspeed_min) / g.scaling_speed);
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float scale_max = MAX(2.0, (1.5 * aparm.airspeed_max) / g.scaling_speed);
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speed_scaler = constrain_float(speed_scaler, scale_min, scale_max);
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2018-09-13 00:49:58 -03:00
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if (quadplane.in_vtol_mode() && hal.util->get_soft_armed()) {
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// when in VTOL modes limit surface movement at low speed to prevent instability
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float threshold = aparm.airspeed_min * 0.5;
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if (aspeed < threshold) {
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float new_scaler = linear_interpolate(0, g.scaling_speed / threshold, aspeed, 0, threshold);
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speed_scaler = MIN(speed_scaler, new_scaler);
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}
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}
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2018-12-06 00:29:08 -04:00
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} else if (hal.util->get_soft_armed()) {
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// scale assumed surface movement using throttle output
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float throttle_out = MAX(SRV_Channels::get_output_scaled(SRV_Channel::k_throttle), 1);
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speed_scaler = sqrtf(THROTTLE_CRUISE / throttle_out);
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2012-08-24 09:03:03 -03:00
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// This case is constrained tighter as we don't have real speed info
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2015-04-11 06:43:13 -03:00
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speed_scaler = constrain_float(speed_scaler, 0.6f, 1.67f);
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2018-12-06 00:29:08 -04:00
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} else {
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// no speed estimate and not armed, use a unit scaling
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speed_scaler = 1;
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2012-08-21 23:19:50 -03:00
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}
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2012-09-11 00:01:36 -03:00
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return speed_scaler;
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}
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2012-09-22 20:33:17 -03:00
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/*
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return true if the current settings and mode should allow for stick mixing
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*/
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2015-05-13 03:09:36 -03:00
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bool Plane::stick_mixing_enabled(void)
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2012-09-22 20:33:17 -03:00
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{
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2016-07-04 23:52:13 -03:00
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if (auto_throttle_mode && auto_navigation_mode) {
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2012-09-23 18:13:57 -03:00
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// we're in an auto mode. Check the stick mixing flag
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2013-04-01 18:52:56 -03:00
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if (g.stick_mixing != STICK_MIXING_DISABLED &&
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2012-09-23 18:13:57 -03:00
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geofence_stickmixing() &&
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2013-07-19 01:11:16 -03:00
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failsafe.state == FAILSAFE_NONE &&
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2014-03-08 01:20:09 -04:00
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!rc_failsafe_active()) {
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2012-09-23 18:13:57 -03:00
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// we're in an auto mode, and haven't triggered failsafe
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return true;
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} else {
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return false;
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}
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2012-09-22 20:33:17 -03:00
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}
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2013-09-13 21:30:13 -03:00
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2017-12-06 19:02:11 -04:00
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if (failsafe.rc_failsafe && g.fs_action_short == FS_ACTION_SHORT_FBWA) {
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2013-09-13 21:30:13 -03:00
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// don't do stick mixing in FBWA glide mode
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return false;
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}
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2012-09-23 18:13:57 -03:00
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// non-auto mode. Always do stick mixing
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return true;
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2012-09-22 20:33:17 -03:00
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}
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2012-09-11 00:01:36 -03:00
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2012-12-04 02:32:37 -04:00
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/*
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this is the main roll stabilization function. It takes the
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previously set nav_roll calculates roll servo_out to try to
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stabilize the plane at the given roll
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*/
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2015-05-13 03:09:36 -03:00
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void Plane::stabilize_roll(float speed_scaler)
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2012-09-11 00:01:36 -03:00
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{
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2014-06-05 03:12:10 -03:00
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if (fly_inverted()) {
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2011-09-09 11:18:38 -03:00
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// we want to fly upside down. We need to cope with wrap of
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// the roll_sensor interfering with wrap of nav_roll, which
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// would really confuse the PID code. The easiest way to
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// handle this is to ensure both go in the same direction from
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// zero
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2012-08-07 03:05:51 -03:00
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nav_roll_cd += 18000;
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if (ahrs.roll_sensor < 0) nav_roll_cd -= 36000;
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2011-09-09 11:18:38 -03:00
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}
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2013-08-02 08:55:34 -03:00
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bool disable_integrator = false;
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ArduPlane: Fix up after refactoring RC_Channel class
Further to refactor of RC_Channel class which included
adding get_xx set_xx methods, change reads and writes to the public members
to calls to get and set functionsss
old public member(int16_t) get function -> int16_t set function (int16_t)
(expression where c is an object of type RC_Channel)
c.radio_in c.get_radio_in() c.set_radio_in(v)
c.control_in c.get_control_in() c.set_control_in(v)
c.servo_out c.get_servo_out() c.set_servo_out(v)
c.pwm_out c.get_pwm_out() // use existing
c.radio_out c.get_radio_out() c.set_radio_out(v)
c.radio_max c.get_radio_max() c.set_radio_max(v)
c.radio_min c.get_radio_min() c.set_radio_min(v)
c.radio_trim c.get_radio_trim() c.set_radio_trim(v);
c.min_max_configured() // return true if min and max are configured
Because data members of RC_Channels are now private and so cannot be written directly
some overloads are provided in the Plane classes to provide the old functionality
new overload Plane::stick_mix_channel(RC_Channel *channel)
which forwards to the previously existing
void stick_mix_channel(RC_Channel *channel, int16_t &servo_out);
new overload Plane::channel_output_mixer(Rc_Channel* , RC_Channel*)const
which forwards to
(uint8_t mixing_type, int16_t & chan1, int16_t & chan2)const;
Rename functions
RC_Channel_aux::set_radio_trim(Aux_servo_function_t function)
to RC_Channel_aux::set_trim_to_radio_in_for(Aux_servo_function_t function)
RC_Channel_aux::set_servo_out(Aux_servo_function_t function, int16_t value)
to RC_Channel_aux::set_servo_out_for(Aux_servo_function_t function, int16_t value)
Rationale:
RC_Channel is a complicated class, which combines
several functionalities dealing with stick inputs
in pwm and logical units, logical and actual actuator
outputs, unit conversion etc, etc
The intent of this PR is to clarify existing use of
the class. At the basic level it should now be possible
to grep all places where private variable is set by
searching for the set_xx function.
(The wider purpose is to provide a more generic and
logically simpler method of output mixing. This is a small step)
2016-05-08 05:33:02 -03:00
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if (control_mode == STABILIZE && channel_roll->get_control_in() != 0) {
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2013-08-02 08:55:34 -03:00
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disable_integrator = true;
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}
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2016-10-22 07:27:57 -03:00
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SRV_Channels::set_output_scaled(SRV_Channel::k_aileron, rollController.get_servo_out(nav_roll_cd - ahrs.roll_sensor,
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speed_scaler,
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disable_integrator));
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2012-12-04 02:32:37 -04:00
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}
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/*
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this is the main pitch stabilization function. It takes the
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previously set nav_pitch and calculates servo_out values to try to
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stabilize the plane at the given attitude.
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*/
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2015-05-13 03:09:36 -03:00
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void Plane::stabilize_pitch(float speed_scaler)
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2012-12-04 02:32:37 -04:00
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{
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2014-05-21 07:21:19 -03:00
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int8_t force_elevator = takeoff_tail_hold();
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if (force_elevator != 0) {
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2016-01-30 03:22:21 -04:00
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// we are holding the tail down during takeoff. Just convert
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2014-05-21 07:21:19 -03:00
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// from a percentage to a -4500..4500 centidegree angle
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2016-10-22 07:27:57 -03:00
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SRV_Channels::set_output_scaled(SRV_Channel::k_elevator, 45*force_elevator);
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2014-05-21 07:21:19 -03:00
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return;
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}
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2016-10-22 07:27:57 -03:00
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int32_t demanded_pitch = nav_pitch_cd + g.pitch_trim_cd + SRV_Channels::get_output_scaled(SRV_Channel::k_throttle) * g.kff_throttle_to_pitch;
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2013-08-02 08:55:34 -03:00
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bool disable_integrator = false;
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ArduPlane: Fix up after refactoring RC_Channel class
Further to refactor of RC_Channel class which included
adding get_xx set_xx methods, change reads and writes to the public members
to calls to get and set functionsss
old public member(int16_t) get function -> int16_t set function (int16_t)
(expression where c is an object of type RC_Channel)
c.radio_in c.get_radio_in() c.set_radio_in(v)
c.control_in c.get_control_in() c.set_control_in(v)
c.servo_out c.get_servo_out() c.set_servo_out(v)
c.pwm_out c.get_pwm_out() // use existing
c.radio_out c.get_radio_out() c.set_radio_out(v)
c.radio_max c.get_radio_max() c.set_radio_max(v)
c.radio_min c.get_radio_min() c.set_radio_min(v)
c.radio_trim c.get_radio_trim() c.set_radio_trim(v);
c.min_max_configured() // return true if min and max are configured
Because data members of RC_Channels are now private and so cannot be written directly
some overloads are provided in the Plane classes to provide the old functionality
new overload Plane::stick_mix_channel(RC_Channel *channel)
which forwards to the previously existing
void stick_mix_channel(RC_Channel *channel, int16_t &servo_out);
new overload Plane::channel_output_mixer(Rc_Channel* , RC_Channel*)const
which forwards to
(uint8_t mixing_type, int16_t & chan1, int16_t & chan2)const;
Rename functions
RC_Channel_aux::set_radio_trim(Aux_servo_function_t function)
to RC_Channel_aux::set_trim_to_radio_in_for(Aux_servo_function_t function)
RC_Channel_aux::set_servo_out(Aux_servo_function_t function, int16_t value)
to RC_Channel_aux::set_servo_out_for(Aux_servo_function_t function, int16_t value)
Rationale:
RC_Channel is a complicated class, which combines
several functionalities dealing with stick inputs
in pwm and logical units, logical and actual actuator
outputs, unit conversion etc, etc
The intent of this PR is to clarify existing use of
the class. At the basic level it should now be possible
to grep all places where private variable is set by
searching for the set_xx function.
(The wider purpose is to provide a more generic and
logically simpler method of output mixing. This is a small step)
2016-05-08 05:33:02 -03:00
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if (control_mode == STABILIZE && channel_pitch->get_control_in() != 0) {
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2013-08-02 08:55:34 -03:00
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disable_integrator = true;
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}
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2016-10-22 07:27:57 -03:00
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SRV_Channels::set_output_scaled(SRV_Channel::k_elevator, pitchController.get_servo_out(demanded_pitch - ahrs.pitch_sensor,
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speed_scaler,
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disable_integrator));
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2012-12-04 02:32:37 -04:00
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}
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2011-09-08 22:29:39 -03:00
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2013-10-03 09:51:43 -03:00
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/*
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perform stick mixing on one channel
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This type of stick mixing reduces the influence of the auto
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controller as it increases the influence of the users stick input,
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allowing the user full deflection if needed
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*/
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2015-05-13 03:09:36 -03:00
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void Plane::stick_mix_channel(RC_Channel *channel, int16_t &servo_out)
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2013-10-03 09:51:43 -03:00
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{
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float ch_inf;
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ArduPlane: Fix up after refactoring RC_Channel class
Further to refactor of RC_Channel class which included
adding get_xx set_xx methods, change reads and writes to the public members
to calls to get and set functionsss
old public member(int16_t) get function -> int16_t set function (int16_t)
(expression where c is an object of type RC_Channel)
c.radio_in c.get_radio_in() c.set_radio_in(v)
c.control_in c.get_control_in() c.set_control_in(v)
c.servo_out c.get_servo_out() c.set_servo_out(v)
c.pwm_out c.get_pwm_out() // use existing
c.radio_out c.get_radio_out() c.set_radio_out(v)
c.radio_max c.get_radio_max() c.set_radio_max(v)
c.radio_min c.get_radio_min() c.set_radio_min(v)
c.radio_trim c.get_radio_trim() c.set_radio_trim(v);
c.min_max_configured() // return true if min and max are configured
Because data members of RC_Channels are now private and so cannot be written directly
some overloads are provided in the Plane classes to provide the old functionality
new overload Plane::stick_mix_channel(RC_Channel *channel)
which forwards to the previously existing
void stick_mix_channel(RC_Channel *channel, int16_t &servo_out);
new overload Plane::channel_output_mixer(Rc_Channel* , RC_Channel*)const
which forwards to
(uint8_t mixing_type, int16_t & chan1, int16_t & chan2)const;
Rename functions
RC_Channel_aux::set_radio_trim(Aux_servo_function_t function)
to RC_Channel_aux::set_trim_to_radio_in_for(Aux_servo_function_t function)
RC_Channel_aux::set_servo_out(Aux_servo_function_t function, int16_t value)
to RC_Channel_aux::set_servo_out_for(Aux_servo_function_t function, int16_t value)
Rationale:
RC_Channel is a complicated class, which combines
several functionalities dealing with stick inputs
in pwm and logical units, logical and actual actuator
outputs, unit conversion etc, etc
The intent of this PR is to clarify existing use of
the class. At the basic level it should now be possible
to grep all places where private variable is set by
searching for the set_xx function.
(The wider purpose is to provide a more generic and
logically simpler method of output mixing. This is a small step)
2016-05-08 05:33:02 -03:00
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ch_inf = (float)channel->get_radio_in() - (float)channel->get_radio_trim();
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2013-10-03 09:51:43 -03:00
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ch_inf = fabsf(ch_inf);
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2015-11-27 13:11:58 -04:00
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ch_inf = MIN(ch_inf, 400.0f);
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2014-07-08 07:26:07 -03:00
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ch_inf = ((400.0f - ch_inf) / 400.0f);
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2014-03-04 21:13:19 -04:00
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servo_out *= ch_inf;
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2017-01-07 01:36:30 -04:00
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servo_out += channel->get_control_in();
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2013-10-03 09:51:43 -03:00
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}
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2012-12-04 02:32:37 -04:00
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/*
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this gives the user control of the aircraft in stabilization modes
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*/
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2015-05-13 03:09:36 -03:00
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void Plane::stabilize_stick_mixing_direct()
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2012-12-04 02:32:37 -04:00
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{
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if (!stick_mixing_enabled() ||
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2013-07-10 10:25:38 -03:00
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control_mode == ACRO ||
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2012-12-04 02:32:37 -04:00
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control_mode == FLY_BY_WIRE_A ||
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2014-04-12 01:12:14 -03:00
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control_mode == AUTOTUNE ||
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2012-12-04 02:32:37 -04:00
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control_mode == FLY_BY_WIRE_B ||
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2013-07-13 07:05:53 -03:00
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control_mode == CRUISE ||
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2015-12-26 03:45:42 -04:00
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control_mode == QSTABILIZE ||
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control_mode == QHOVER ||
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2015-12-26 04:51:05 -04:00
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control_mode == QLOITER ||
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2016-03-09 03:20:41 -04:00
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control_mode == QLAND ||
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2016-04-29 02:31:08 -03:00
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control_mode == QRTL ||
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2019-02-17 14:42:05 -04:00
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control_mode == QACRO ||
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2018-12-07 03:52:05 -04:00
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control_mode == TRAINING ||
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control_mode == QAUTOTUNE) {
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2012-12-04 02:32:37 -04:00
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return;
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}
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2016-10-22 07:27:57 -03:00
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int16_t aileron = SRV_Channels::get_output_scaled(SRV_Channel::k_aileron);
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stick_mix_channel(channel_roll, aileron);
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SRV_Channels::set_output_scaled(SRV_Channel::k_aileron, aileron);
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int16_t elevator = SRV_Channels::get_output_scaled(SRV_Channel::k_elevator);
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stick_mix_channel(channel_pitch, elevator);
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SRV_Channels::set_output_scaled(SRV_Channel::k_elevator, elevator);
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2012-12-04 02:32:37 -04:00
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}
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2013-04-01 18:52:56 -03:00
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/*
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this gives the user control of the aircraft in stabilization modes
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using FBW style controls
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*/
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2015-05-13 03:09:36 -03:00
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void Plane::stabilize_stick_mixing_fbw()
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2013-04-01 18:52:56 -03:00
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{
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if (!stick_mixing_enabled() ||
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2013-07-10 10:25:38 -03:00
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control_mode == ACRO ||
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2013-04-01 18:52:56 -03:00
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control_mode == FLY_BY_WIRE_A ||
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2014-04-12 01:12:14 -03:00
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control_mode == AUTOTUNE ||
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2013-04-01 18:52:56 -03:00
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control_mode == FLY_BY_WIRE_B ||
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2013-07-13 07:05:53 -03:00
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control_mode == CRUISE ||
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2015-12-26 03:45:42 -04:00
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control_mode == QSTABILIZE ||
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control_mode == QHOVER ||
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2015-12-26 04:51:05 -04:00
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|
control_mode == QLOITER ||
|
2016-03-09 03:20:41 -04:00
|
|
|
control_mode == QLAND ||
|
2016-04-29 02:31:08 -03:00
|
|
|
control_mode == QRTL ||
|
2019-02-17 14:42:05 -04:00
|
|
|
control_mode == QACRO ||
|
2013-09-19 23:31:35 -03:00
|
|
|
control_mode == TRAINING ||
|
2018-12-07 03:52:05 -04:00
|
|
|
control_mode == QAUTOTUNE ||
|
2016-04-05 18:58:23 -03:00
|
|
|
(control_mode == AUTO && g.auto_fbw_steer == 42)) {
|
2013-04-01 18:52:56 -03:00
|
|
|
return;
|
|
|
|
}
|
|
|
|
// do FBW style stick mixing. We don't treat it linearly
|
|
|
|
// however. For inputs up to half the maximum, we use linear
|
|
|
|
// addition to the nav_roll and nav_pitch. Above that it goes
|
|
|
|
// non-linear and ends up as 2x the maximum, to ensure that
|
|
|
|
// the user can direct the plane in any direction with stick
|
|
|
|
// mixing.
|
2013-06-03 02:32:08 -03:00
|
|
|
float roll_input = channel_roll->norm_input();
|
2013-05-26 19:24:35 -03:00
|
|
|
if (roll_input > 0.5f) {
|
2013-04-01 18:52:56 -03:00
|
|
|
roll_input = (3*roll_input - 1);
|
2013-05-26 19:24:35 -03:00
|
|
|
} else if (roll_input < -0.5f) {
|
|
|
|
roll_input = (3*roll_input + 1);
|
2013-04-01 18:52:56 -03:00
|
|
|
}
|
2013-11-04 04:48:22 -04:00
|
|
|
nav_roll_cd += roll_input * roll_limit_cd;
|
|
|
|
nav_roll_cd = constrain_int32(nav_roll_cd, -roll_limit_cd, roll_limit_cd);
|
2013-04-01 18:52:56 -03:00
|
|
|
|
2013-06-03 02:32:08 -03:00
|
|
|
float pitch_input = channel_pitch->norm_input();
|
2016-06-01 19:07:55 -03:00
|
|
|
if (pitch_input > 0.5f) {
|
2013-04-01 18:52:56 -03:00
|
|
|
pitch_input = (3*pitch_input - 1);
|
2016-06-01 19:07:55 -03:00
|
|
|
} else if (pitch_input < -0.5f) {
|
|
|
|
pitch_input = (3*pitch_input + 1);
|
2013-04-01 18:52:56 -03:00
|
|
|
}
|
2014-06-05 03:12:10 -03:00
|
|
|
if (fly_inverted()) {
|
2013-04-01 18:52:56 -03:00
|
|
|
pitch_input = -pitch_input;
|
|
|
|
}
|
|
|
|
if (pitch_input > 0) {
|
2013-06-26 07:48:45 -03:00
|
|
|
nav_pitch_cd += pitch_input * aparm.pitch_limit_max_cd;
|
2013-04-01 18:52:56 -03:00
|
|
|
} else {
|
2013-11-04 04:48:22 -04:00
|
|
|
nav_pitch_cd += -(pitch_input * pitch_limit_min_cd);
|
2013-04-01 18:52:56 -03:00
|
|
|
}
|
2013-11-04 04:48:22 -04:00
|
|
|
nav_pitch_cd = constrain_int32(nav_pitch_cd, pitch_limit_min_cd, aparm.pitch_limit_max_cd.get());
|
2013-04-01 18:52:56 -03:00
|
|
|
}
|
|
|
|
|
2012-08-21 23:19:50 -03:00
|
|
|
|
2012-12-04 02:32:37 -04:00
|
|
|
/*
|
2013-10-03 09:01:43 -03:00
|
|
|
stabilize the yaw axis. There are 3 modes of operation:
|
|
|
|
|
|
|
|
- hold a specific heading with ground steering
|
|
|
|
- rate controlled with ground steering
|
|
|
|
- yaw control for coordinated flight
|
2012-12-04 02:32:37 -04:00
|
|
|
*/
|
2015-05-13 03:09:36 -03:00
|
|
|
void Plane::stabilize_yaw(float speed_scaler)
|
2012-12-04 02:32:37 -04:00
|
|
|
{
|
2017-01-10 03:42:57 -04:00
|
|
|
if (landing.is_flaring()) {
|
|
|
|
// in flaring then enable ground steering
|
2014-08-26 06:37:36 -03:00
|
|
|
steering_control.ground_steering = true;
|
|
|
|
} else {
|
|
|
|
// otherwise use ground steering when no input control and we
|
|
|
|
// are below the GROUND_STEER_ALT
|
ArduPlane: Fix up after refactoring RC_Channel class
Further to refactor of RC_Channel class which included
adding get_xx set_xx methods, change reads and writes to the public members
to calls to get and set functionsss
old public member(int16_t) get function -> int16_t set function (int16_t)
(expression where c is an object of type RC_Channel)
c.radio_in c.get_radio_in() c.set_radio_in(v)
c.control_in c.get_control_in() c.set_control_in(v)
c.servo_out c.get_servo_out() c.set_servo_out(v)
c.pwm_out c.get_pwm_out() // use existing
c.radio_out c.get_radio_out() c.set_radio_out(v)
c.radio_max c.get_radio_max() c.set_radio_max(v)
c.radio_min c.get_radio_min() c.set_radio_min(v)
c.radio_trim c.get_radio_trim() c.set_radio_trim(v);
c.min_max_configured() // return true if min and max are configured
Because data members of RC_Channels are now private and so cannot be written directly
some overloads are provided in the Plane classes to provide the old functionality
new overload Plane::stick_mix_channel(RC_Channel *channel)
which forwards to the previously existing
void stick_mix_channel(RC_Channel *channel, int16_t &servo_out);
new overload Plane::channel_output_mixer(Rc_Channel* , RC_Channel*)const
which forwards to
(uint8_t mixing_type, int16_t & chan1, int16_t & chan2)const;
Rename functions
RC_Channel_aux::set_radio_trim(Aux_servo_function_t function)
to RC_Channel_aux::set_trim_to_radio_in_for(Aux_servo_function_t function)
RC_Channel_aux::set_servo_out(Aux_servo_function_t function, int16_t value)
to RC_Channel_aux::set_servo_out_for(Aux_servo_function_t function, int16_t value)
Rationale:
RC_Channel is a complicated class, which combines
several functionalities dealing with stick inputs
in pwm and logical units, logical and actual actuator
outputs, unit conversion etc, etc
The intent of this PR is to clarify existing use of
the class. At the basic level it should now be possible
to grep all places where private variable is set by
searching for the set_xx function.
(The wider purpose is to provide a more generic and
logically simpler method of output mixing. This is a small step)
2016-05-08 05:33:02 -03:00
|
|
|
steering_control.ground_steering = (channel_roll->get_control_in() == 0 &&
|
2017-01-30 15:48:22 -04:00
|
|
|
fabsf(relative_altitude) < g.ground_steer_alt);
|
2017-02-14 15:13:11 -04:00
|
|
|
if (!landing.is_ground_steering_allowed()) {
|
2014-08-28 22:36:09 -03:00
|
|
|
// don't use ground steering on landing approach
|
|
|
|
steering_control.ground_steering = false;
|
|
|
|
}
|
2014-08-26 06:37:36 -03:00
|
|
|
}
|
|
|
|
|
2012-12-04 02:32:37 -04:00
|
|
|
|
2014-03-04 21:13:19 -04:00
|
|
|
/*
|
2014-08-26 06:37:36 -03:00
|
|
|
first calculate steering_control.steering for a nose or tail
|
2017-01-10 03:42:57 -04:00
|
|
|
wheel. We use "course hold" mode for the rudder when either performing
|
|
|
|
a flare (when the wings are held level) or when in course hold in
|
|
|
|
FBWA mode (when we are below GROUND_STEER_ALT)
|
2014-03-04 21:13:19 -04:00
|
|
|
*/
|
2017-01-10 03:42:57 -04:00
|
|
|
if (landing.is_flaring() ||
|
2014-08-26 06:37:36 -03:00
|
|
|
(steer_state.hold_course_cd != -1 && steering_control.ground_steering)) {
|
2013-10-03 09:01:43 -03:00
|
|
|
calc_nav_yaw_course();
|
2014-03-04 21:13:19 -04:00
|
|
|
} else if (steering_control.ground_steering) {
|
2013-10-03 09:01:43 -03:00
|
|
|
calc_nav_yaw_ground();
|
|
|
|
}
|
2014-03-04 21:13:19 -04:00
|
|
|
|
|
|
|
/*
|
|
|
|
now calculate steering_control.rudder for the rudder
|
|
|
|
*/
|
|
|
|
calc_nav_yaw_coordinated(speed_scaler);
|
2011-09-08 22:29:39 -03:00
|
|
|
}
|
|
|
|
|
2012-12-04 02:32:37 -04:00
|
|
|
|
|
|
|
/*
|
|
|
|
a special stabilization function for training mode
|
|
|
|
*/
|
2015-05-13 03:09:36 -03:00
|
|
|
void Plane::stabilize_training(float speed_scaler)
|
2012-12-04 02:32:37 -04:00
|
|
|
{
|
|
|
|
if (training_manual_roll) {
|
2016-10-22 07:27:57 -03:00
|
|
|
SRV_Channels::set_output_scaled(SRV_Channel::k_aileron, channel_roll->get_control_in());
|
2012-12-04 02:32:37 -04:00
|
|
|
} else {
|
|
|
|
// calculate what is needed to hold
|
|
|
|
stabilize_roll(speed_scaler);
|
2016-10-22 07:27:57 -03:00
|
|
|
if ((nav_roll_cd > 0 && channel_roll->get_control_in() < SRV_Channels::get_output_scaled(SRV_Channel::k_aileron)) ||
|
|
|
|
(nav_roll_cd < 0 && channel_roll->get_control_in() > SRV_Channels::get_output_scaled(SRV_Channel::k_aileron))) {
|
2012-12-04 02:32:37 -04:00
|
|
|
// allow user to get out of the roll
|
2016-10-22 07:27:57 -03:00
|
|
|
SRV_Channels::set_output_scaled(SRV_Channel::k_aileron, channel_roll->get_control_in());
|
2012-12-04 02:32:37 -04:00
|
|
|
}
|
|
|
|
}
|
|
|
|
|
|
|
|
if (training_manual_pitch) {
|
2016-10-22 07:27:57 -03:00
|
|
|
SRV_Channels::set_output_scaled(SRV_Channel::k_elevator, channel_pitch->get_control_in());
|
2012-12-04 02:32:37 -04:00
|
|
|
} else {
|
|
|
|
stabilize_pitch(speed_scaler);
|
2016-10-22 07:27:57 -03:00
|
|
|
if ((nav_pitch_cd > 0 && channel_pitch->get_control_in() < SRV_Channels::get_output_scaled(SRV_Channel::k_elevator)) ||
|
|
|
|
(nav_pitch_cd < 0 && channel_pitch->get_control_in() > SRV_Channels::get_output_scaled(SRV_Channel::k_elevator))) {
|
2012-12-04 02:32:37 -04:00
|
|
|
// allow user to get back to level
|
2016-10-22 07:27:57 -03:00
|
|
|
SRV_Channels::set_output_scaled(SRV_Channel::k_elevator, channel_pitch->get_control_in());
|
2012-12-04 02:32:37 -04:00
|
|
|
}
|
|
|
|
}
|
|
|
|
|
|
|
|
stabilize_yaw(speed_scaler);
|
|
|
|
}
|
|
|
|
|
|
|
|
|
2013-07-10 10:25:38 -03:00
|
|
|
/*
|
|
|
|
this is the ACRO mode stabilization function. It does rate
|
|
|
|
stabilization on roll and pitch axes
|
|
|
|
*/
|
2015-05-13 03:09:36 -03:00
|
|
|
void Plane::stabilize_acro(float speed_scaler)
|
2013-07-10 10:25:38 -03:00
|
|
|
{
|
ArduPlane: Fix up after refactoring RC_Channel class
Further to refactor of RC_Channel class which included
adding get_xx set_xx methods, change reads and writes to the public members
to calls to get and set functionsss
old public member(int16_t) get function -> int16_t set function (int16_t)
(expression where c is an object of type RC_Channel)
c.radio_in c.get_radio_in() c.set_radio_in(v)
c.control_in c.get_control_in() c.set_control_in(v)
c.servo_out c.get_servo_out() c.set_servo_out(v)
c.pwm_out c.get_pwm_out() // use existing
c.radio_out c.get_radio_out() c.set_radio_out(v)
c.radio_max c.get_radio_max() c.set_radio_max(v)
c.radio_min c.get_radio_min() c.set_radio_min(v)
c.radio_trim c.get_radio_trim() c.set_radio_trim(v);
c.min_max_configured() // return true if min and max are configured
Because data members of RC_Channels are now private and so cannot be written directly
some overloads are provided in the Plane classes to provide the old functionality
new overload Plane::stick_mix_channel(RC_Channel *channel)
which forwards to the previously existing
void stick_mix_channel(RC_Channel *channel, int16_t &servo_out);
new overload Plane::channel_output_mixer(Rc_Channel* , RC_Channel*)const
which forwards to
(uint8_t mixing_type, int16_t & chan1, int16_t & chan2)const;
Rename functions
RC_Channel_aux::set_radio_trim(Aux_servo_function_t function)
to RC_Channel_aux::set_trim_to_radio_in_for(Aux_servo_function_t function)
RC_Channel_aux::set_servo_out(Aux_servo_function_t function, int16_t value)
to RC_Channel_aux::set_servo_out_for(Aux_servo_function_t function, int16_t value)
Rationale:
RC_Channel is a complicated class, which combines
several functionalities dealing with stick inputs
in pwm and logical units, logical and actual actuator
outputs, unit conversion etc, etc
The intent of this PR is to clarify existing use of
the class. At the basic level it should now be possible
to grep all places where private variable is set by
searching for the set_xx function.
(The wider purpose is to provide a more generic and
logically simpler method of output mixing. This is a small step)
2016-05-08 05:33:02 -03:00
|
|
|
float roll_rate = (channel_roll->get_control_in()/4500.0f) * g.acro_roll_rate;
|
|
|
|
float pitch_rate = (channel_pitch->get_control_in()/4500.0f) * g.acro_pitch_rate;
|
2013-07-10 10:25:38 -03:00
|
|
|
|
2013-07-10 19:05:25 -03:00
|
|
|
/*
|
|
|
|
check for special roll handling near the pitch poles
|
|
|
|
*/
|
2015-05-04 23:34:27 -03:00
|
|
|
if (g.acro_locking && is_zero(roll_rate)) {
|
2013-07-10 19:05:25 -03:00
|
|
|
/*
|
|
|
|
we have no roll stick input, so we will enter "roll locked"
|
|
|
|
mode, and hold the roll we had when the stick was released
|
|
|
|
*/
|
2013-07-10 10:25:38 -03:00
|
|
|
if (!acro_state.locked_roll) {
|
|
|
|
acro_state.locked_roll = true;
|
2013-07-13 08:06:45 -03:00
|
|
|
acro_state.locked_roll_err = 0;
|
|
|
|
} else {
|
2013-10-11 23:30:27 -03:00
|
|
|
acro_state.locked_roll_err += ahrs.get_gyro().x * G_Dt;
|
2013-07-10 10:25:38 -03:00
|
|
|
}
|
2013-07-13 08:06:45 -03:00
|
|
|
int32_t roll_error_cd = -ToDeg(acro_state.locked_roll_err)*100;
|
|
|
|
nav_roll_cd = ahrs.roll_sensor + roll_error_cd;
|
|
|
|
// try to reduce the integrated angular error to zero. We set
|
|
|
|
// 'stabilze' to true, which disables the roll integrator
|
2016-10-22 07:27:57 -03:00
|
|
|
SRV_Channels::set_output_scaled(SRV_Channel::k_aileron, rollController.get_servo_out(roll_error_cd,
|
|
|
|
speed_scaler,
|
|
|
|
true));
|
2013-07-10 10:25:38 -03:00
|
|
|
} else {
|
2013-07-10 19:05:25 -03:00
|
|
|
/*
|
|
|
|
aileron stick is non-zero, use pure rate control until the
|
|
|
|
user releases the stick
|
|
|
|
*/
|
2013-07-10 10:25:38 -03:00
|
|
|
acro_state.locked_roll = false;
|
2016-10-22 07:27:57 -03:00
|
|
|
SRV_Channels::set_output_scaled(SRV_Channel::k_aileron, rollController.get_rate_out(roll_rate, speed_scaler));
|
2013-07-10 10:25:38 -03:00
|
|
|
}
|
|
|
|
|
2015-05-04 23:34:27 -03:00
|
|
|
if (g.acro_locking && is_zero(pitch_rate)) {
|
2013-07-10 19:05:25 -03:00
|
|
|
/*
|
|
|
|
user has zero pitch stick input, so we lock pitch at the
|
|
|
|
point they release the stick
|
|
|
|
*/
|
2013-07-10 10:25:38 -03:00
|
|
|
if (!acro_state.locked_pitch) {
|
|
|
|
acro_state.locked_pitch = true;
|
|
|
|
acro_state.locked_pitch_cd = ahrs.pitch_sensor;
|
|
|
|
}
|
2013-07-13 08:06:45 -03:00
|
|
|
// try to hold the locked pitch. Note that we have the pitch
|
|
|
|
// integrator enabled, which helps with inverted flight
|
2013-07-10 10:25:38 -03:00
|
|
|
nav_pitch_cd = acro_state.locked_pitch_cd;
|
2016-10-22 07:27:57 -03:00
|
|
|
SRV_Channels::set_output_scaled(SRV_Channel::k_elevator, pitchController.get_servo_out(nav_pitch_cd - ahrs.pitch_sensor,
|
|
|
|
speed_scaler,
|
|
|
|
false));
|
2013-07-10 10:25:38 -03:00
|
|
|
} else {
|
2013-07-10 19:05:25 -03:00
|
|
|
/*
|
|
|
|
user has non-zero pitch input, use a pure rate controller
|
|
|
|
*/
|
2013-07-10 10:25:38 -03:00
|
|
|
acro_state.locked_pitch = false;
|
2016-10-22 07:27:57 -03:00
|
|
|
SRV_Channels::set_output_scaled(SRV_Channel::k_elevator, pitchController.get_rate_out(pitch_rate, speed_scaler));
|
2013-07-10 10:25:38 -03:00
|
|
|
}
|
|
|
|
|
2013-07-10 19:05:25 -03:00
|
|
|
/*
|
2013-10-04 09:15:53 -03:00
|
|
|
manual rudder for now
|
2013-07-10 19:05:25 -03:00
|
|
|
*/
|
2018-08-20 21:38:41 -03:00
|
|
|
steering_control.steering = steering_control.rudder = rudder_input();
|
2013-07-10 10:25:38 -03:00
|
|
|
}
|
|
|
|
|
2012-12-04 02:32:37 -04:00
|
|
|
/*
|
|
|
|
main stabilization function for all 3 axes
|
|
|
|
*/
|
2015-05-13 03:09:36 -03:00
|
|
|
void Plane::stabilize()
|
2012-12-04 02:32:37 -04:00
|
|
|
{
|
2013-07-05 05:05:27 -03:00
|
|
|
if (control_mode == MANUAL) {
|
|
|
|
// nothing to do
|
|
|
|
return;
|
|
|
|
}
|
2012-12-04 02:32:37 -04:00
|
|
|
float speed_scaler = get_speed_scaler();
|
|
|
|
|
2017-10-30 01:19:38 -03:00
|
|
|
if (quadplane.in_tailsitter_vtol_transition()) {
|
|
|
|
/*
|
|
|
|
during transition to vtol in a tailsitter try to raise the
|
|
|
|
nose rapidly while keeping the wings level
|
|
|
|
*/
|
|
|
|
nav_pitch_cd = constrain_float((quadplane.tailsitter.transition_angle+5)*100, 5500, 8500),
|
|
|
|
nav_roll_cd = 0;
|
|
|
|
}
|
|
|
|
|
2012-12-04 02:32:37 -04:00
|
|
|
if (control_mode == TRAINING) {
|
|
|
|
stabilize_training(speed_scaler);
|
2013-07-10 10:25:38 -03:00
|
|
|
} else if (control_mode == ACRO) {
|
|
|
|
stabilize_acro(speed_scaler);
|
2017-10-30 01:19:38 -03:00
|
|
|
} else if ((control_mode == QSTABILIZE ||
|
|
|
|
control_mode == QHOVER ||
|
|
|
|
control_mode == QLOITER ||
|
|
|
|
control_mode == QLAND ||
|
2018-12-07 03:52:05 -04:00
|
|
|
control_mode == QRTL ||
|
2019-02-17 14:42:05 -04:00
|
|
|
control_mode == QACRO ||
|
2018-12-07 03:52:05 -04:00
|
|
|
control_mode == QAUTOTUNE) &&
|
2017-10-30 01:19:38 -03:00
|
|
|
!quadplane.in_tailsitter_vtol_transition()) {
|
2015-12-26 06:40:40 -04:00
|
|
|
quadplane.control_run();
|
2012-12-04 02:32:37 -04:00
|
|
|
} else {
|
2013-04-01 18:52:56 -03:00
|
|
|
if (g.stick_mixing == STICK_MIXING_FBW && control_mode != STABILIZE) {
|
|
|
|
stabilize_stick_mixing_fbw();
|
|
|
|
}
|
2012-12-04 02:32:37 -04:00
|
|
|
stabilize_roll(speed_scaler);
|
|
|
|
stabilize_pitch(speed_scaler);
|
2013-04-01 18:52:56 -03:00
|
|
|
if (g.stick_mixing == STICK_MIXING_DIRECT || control_mode == STABILIZE) {
|
|
|
|
stabilize_stick_mixing_direct();
|
|
|
|
}
|
2012-12-04 02:32:37 -04:00
|
|
|
stabilize_yaw(speed_scaler);
|
|
|
|
}
|
2013-06-01 04:34:40 -03:00
|
|
|
|
|
|
|
/*
|
|
|
|
see if we should zero the attitude controller integrators.
|
|
|
|
*/
|
2018-11-09 18:38:43 -04:00
|
|
|
if (get_throttle_input() == 0 &&
|
2017-01-30 15:48:22 -04:00
|
|
|
fabsf(relative_altitude) < 5.0f &&
|
2014-07-08 07:26:07 -03:00
|
|
|
fabsf(barometer.get_climb_rate()) < 0.5f &&
|
2014-03-28 16:52:48 -03:00
|
|
|
gps.ground_speed() < 3) {
|
2013-06-01 04:34:40 -03:00
|
|
|
// we are low, with no climb rate, and zero throttle, and very
|
|
|
|
// low ground speed. Zero the attitude controller
|
|
|
|
// integrators. This prevents integrator buildup pre-takeoff.
|
2013-08-14 01:57:41 -03:00
|
|
|
rollController.reset_I();
|
|
|
|
pitchController.reset_I();
|
|
|
|
yawController.reset_I();
|
2014-08-24 19:20:37 -03:00
|
|
|
|
|
|
|
// if moving very slowly also zero the steering integrator
|
|
|
|
if (gps.ground_speed() < 1) {
|
|
|
|
steerController.reset_I();
|
|
|
|
}
|
2013-06-01 04:34:40 -03:00
|
|
|
}
|
2012-12-04 02:32:37 -04:00
|
|
|
}
|
|
|
|
|
|
|
|
|
2015-05-13 03:09:36 -03:00
|
|
|
void Plane::calc_throttle()
|
2011-09-08 22:29:39 -03:00
|
|
|
{
|
2013-06-26 07:48:45 -03:00
|
|
|
if (aparm.throttle_cruise <= 1) {
|
2013-03-07 23:59:19 -04:00
|
|
|
// user has asked for zero throttle - this may be done by a
|
|
|
|
// mission which wants to turn off the engine for a parachute
|
|
|
|
// landing
|
2016-10-22 07:27:57 -03:00
|
|
|
SRV_Channels::set_output_scaled(SRV_Channel::k_throttle, 0);
|
2013-03-07 23:59:19 -04:00
|
|
|
return;
|
|
|
|
}
|
|
|
|
|
2016-06-30 12:50:17 -03:00
|
|
|
int32_t commanded_throttle = SpdHgt_Controller->get_throttle_demand();
|
|
|
|
|
|
|
|
// Received an external msg that guides throttle in the last 3 seconds?
|
2016-08-12 17:27:48 -03:00
|
|
|
if ((control_mode == GUIDED || control_mode == AVOID_ADSB) &&
|
2016-06-30 12:50:17 -03:00
|
|
|
plane.guided_state.last_forced_throttle_ms > 0 &&
|
|
|
|
millis() - plane.guided_state.last_forced_throttle_ms < 3000) {
|
|
|
|
commanded_throttle = plane.guided_state.forced_throttle;
|
|
|
|
}
|
|
|
|
|
2016-10-22 07:27:57 -03:00
|
|
|
SRV_Channels::set_output_scaled(SRV_Channel::k_throttle, commanded_throttle);
|
2011-09-08 22:29:39 -03:00
|
|
|
}
|
|
|
|
|
|
|
|
/*****************************************
|
2012-08-21 23:19:50 -03:00
|
|
|
* Calculate desired roll/pitch/yaw angles (in medium freq loop)
|
|
|
|
*****************************************/
|
2011-09-08 22:29:39 -03:00
|
|
|
|
2013-10-03 09:01:43 -03:00
|
|
|
/*
|
|
|
|
calculate yaw control for coordinated flight
|
|
|
|
*/
|
2015-05-13 03:09:36 -03:00
|
|
|
void Plane::calc_nav_yaw_coordinated(float speed_scaler)
|
2011-09-08 22:29:39 -03:00
|
|
|
{
|
2013-08-02 08:55:34 -03:00
|
|
|
bool disable_integrator = false;
|
2018-08-20 21:38:41 -03:00
|
|
|
int16_t rudder_in = rudder_input();
|
2012-08-14 22:19:12 -03:00
|
|
|
|
2016-06-30 12:50:17 -03:00
|
|
|
int16_t commanded_rudder;
|
|
|
|
|
|
|
|
// Received an external msg that guides yaw in the last 3 seconds?
|
2016-08-12 17:27:48 -03:00
|
|
|
if ((control_mode == GUIDED || control_mode == AVOID_ADSB) &&
|
2016-06-30 12:50:17 -03:00
|
|
|
plane.guided_state.last_forced_rpy_ms.z > 0 &&
|
|
|
|
millis() - plane.guided_state.last_forced_rpy_ms.z < 3000) {
|
|
|
|
commanded_rudder = plane.guided_state.forced_rpy_cd.z;
|
|
|
|
} else {
|
2018-08-20 21:38:41 -03:00
|
|
|
if (control_mode == STABILIZE && rudder_in != 0) {
|
|
|
|
disable_integrator = true;
|
|
|
|
}
|
|
|
|
|
2016-06-30 12:50:17 -03:00
|
|
|
commanded_rudder = yawController.get_servo_out(speed_scaler, disable_integrator);
|
|
|
|
|
|
|
|
// add in rudder mixing from roll
|
2016-10-22 07:27:57 -03:00
|
|
|
commanded_rudder += SRV_Channels::get_output_scaled(SRV_Channel::k_aileron) * g.kff_rudder_mix;
|
2018-08-20 21:38:41 -03:00
|
|
|
commanded_rudder += rudder_in;
|
2016-06-30 12:50:17 -03:00
|
|
|
}
|
|
|
|
|
|
|
|
steering_control.rudder = constrain_int16(commanded_rudder, -4500, 4500);
|
2011-09-08 22:29:39 -03:00
|
|
|
}
|
|
|
|
|
2013-10-03 09:01:43 -03:00
|
|
|
/*
|
|
|
|
calculate yaw control for ground steering with specific course
|
|
|
|
*/
|
2015-05-13 03:09:36 -03:00
|
|
|
void Plane::calc_nav_yaw_course(void)
|
2013-10-03 09:01:43 -03:00
|
|
|
{
|
|
|
|
// holding a specific navigation course on the ground. Used in
|
|
|
|
// auto-takeoff and landing
|
|
|
|
int32_t bearing_error_cd = nav_controller->bearing_error_cd();
|
2014-03-04 21:13:19 -04:00
|
|
|
steering_control.steering = steerController.get_steering_out_angle_error(bearing_error_cd);
|
2013-10-03 09:01:43 -03:00
|
|
|
if (stick_mixing_enabled()) {
|
2014-03-04 21:13:19 -04:00
|
|
|
stick_mix_channel(channel_rudder, steering_control.steering);
|
2013-10-03 09:01:43 -03:00
|
|
|
}
|
2014-03-04 21:13:19 -04:00
|
|
|
steering_control.steering = constrain_int16(steering_control.steering, -4500, 4500);
|
2013-10-03 09:01:43 -03:00
|
|
|
}
|
|
|
|
|
|
|
|
/*
|
|
|
|
calculate yaw control for ground steering
|
|
|
|
*/
|
2015-05-13 03:09:36 -03:00
|
|
|
void Plane::calc_nav_yaw_ground(void)
|
2013-10-03 09:01:43 -03:00
|
|
|
{
|
2014-03-28 16:52:48 -03:00
|
|
|
if (gps.ground_speed() < 1 &&
|
2018-11-09 18:38:43 -04:00
|
|
|
get_throttle_input() == 0 &&
|
2016-12-13 22:20:57 -04:00
|
|
|
flight_stage != AP_Vehicle::FixedWing::FLIGHT_TAKEOFF &&
|
2016-12-13 23:18:48 -04:00
|
|
|
flight_stage != AP_Vehicle::FixedWing::FLIGHT_ABORT_LAND) {
|
2013-10-03 09:16:09 -03:00
|
|
|
// manual rudder control while still
|
|
|
|
steer_state.locked_course = false;
|
|
|
|
steer_state.locked_course_err = 0;
|
2018-08-20 21:38:41 -03:00
|
|
|
steering_control.steering = rudder_input();
|
2013-10-03 09:16:09 -03:00
|
|
|
return;
|
|
|
|
}
|
|
|
|
|
2018-08-20 21:38:41 -03:00
|
|
|
float steer_rate = (rudder_input()/4500.0f) * g.ground_steer_dps;
|
2016-12-13 22:20:57 -04:00
|
|
|
if (flight_stage == AP_Vehicle::FixedWing::FLIGHT_TAKEOFF ||
|
2016-12-13 23:18:48 -04:00
|
|
|
flight_stage == AP_Vehicle::FixedWing::FLIGHT_ABORT_LAND) {
|
2014-10-06 17:17:33 -03:00
|
|
|
steer_rate = 0;
|
|
|
|
}
|
2015-05-04 23:34:27 -03:00
|
|
|
if (!is_zero(steer_rate)) {
|
2013-10-03 09:01:43 -03:00
|
|
|
// pilot is giving rudder input
|
|
|
|
steer_state.locked_course = false;
|
2013-10-03 09:16:09 -03:00
|
|
|
} else if (!steer_state.locked_course) {
|
2013-10-03 09:01:43 -03:00
|
|
|
// pilot has released the rudder stick or we are still - lock the course
|
|
|
|
steer_state.locked_course = true;
|
2016-12-13 22:20:57 -04:00
|
|
|
if (flight_stage != AP_Vehicle::FixedWing::FLIGHT_TAKEOFF &&
|
2016-12-13 23:18:48 -04:00
|
|
|
flight_stage != AP_Vehicle::FixedWing::FLIGHT_ABORT_LAND) {
|
2014-10-06 17:17:33 -03:00
|
|
|
steer_state.locked_course_err = 0;
|
|
|
|
}
|
2013-10-03 09:01:43 -03:00
|
|
|
}
|
|
|
|
if (!steer_state.locked_course) {
|
2013-10-03 09:51:43 -03:00
|
|
|
// use a rate controller at the pilot specified rate
|
2014-03-04 21:13:19 -04:00
|
|
|
steering_control.steering = steerController.get_steering_out_rate(steer_rate);
|
2013-10-03 09:01:43 -03:00
|
|
|
} else {
|
2013-10-03 09:51:43 -03:00
|
|
|
// use a error controller on the summed error
|
2013-10-03 09:01:43 -03:00
|
|
|
int32_t yaw_error_cd = -ToDeg(steer_state.locked_course_err)*100;
|
2014-03-04 21:13:19 -04:00
|
|
|
steering_control.steering = steerController.get_steering_out_angle_error(yaw_error_cd);
|
2013-10-03 09:01:43 -03:00
|
|
|
}
|
2014-03-04 21:13:19 -04:00
|
|
|
steering_control.steering = constrain_int16(steering_control.steering, -4500, 4500);
|
2013-10-03 09:01:43 -03:00
|
|
|
}
|
|
|
|
|
2011-09-08 22:29:39 -03:00
|
|
|
|
2014-11-11 22:35:34 -04:00
|
|
|
/*
|
|
|
|
calculate a new nav_pitch_cd from the speed height controller
|
|
|
|
*/
|
2015-05-13 03:09:36 -03:00
|
|
|
void Plane::calc_nav_pitch()
|
2011-09-08 22:29:39 -03:00
|
|
|
{
|
2012-08-21 23:19:50 -03:00
|
|
|
// Calculate the Pitch of the plane
|
|
|
|
// --------------------------------
|
2016-06-30 12:50:17 -03:00
|
|
|
int32_t commanded_pitch = SpdHgt_Controller->get_pitch_demand();
|
|
|
|
|
|
|
|
// Received an external msg that guides roll in the last 3 seconds?
|
2016-08-12 17:27:48 -03:00
|
|
|
if ((control_mode == GUIDED || control_mode == AVOID_ADSB) &&
|
2016-06-30 12:50:17 -03:00
|
|
|
plane.guided_state.last_forced_rpy_ms.y > 0 &&
|
|
|
|
millis() - plane.guided_state.last_forced_rpy_ms.y < 3000) {
|
|
|
|
commanded_pitch = plane.guided_state.forced_rpy_cd.y;
|
|
|
|
}
|
|
|
|
|
|
|
|
nav_pitch_cd = constrain_int32(commanded_pitch, pitch_limit_min_cd, aparm.pitch_limit_max_cd.get());
|
2011-09-08 22:29:39 -03:00
|
|
|
}
|
|
|
|
|
|
|
|
|
2014-11-11 22:35:34 -04:00
|
|
|
/*
|
|
|
|
calculate a new nav_roll_cd from the navigation controller
|
|
|
|
*/
|
2015-05-13 03:09:36 -03:00
|
|
|
void Plane::calc_nav_roll()
|
2011-09-08 22:29:39 -03:00
|
|
|
{
|
2016-05-09 11:34:11 -03:00
|
|
|
int32_t commanded_roll = nav_controller->nav_roll_cd();
|
|
|
|
|
2016-06-30 11:48:37 -03:00
|
|
|
// Received an external msg that guides roll in the last 3 seconds?
|
2016-08-12 17:27:48 -03:00
|
|
|
if ((control_mode == GUIDED || control_mode == AVOID_ADSB) &&
|
2016-06-30 12:50:17 -03:00
|
|
|
plane.guided_state.last_forced_rpy_ms.x > 0 &&
|
|
|
|
millis() - plane.guided_state.last_forced_rpy_ms.x < 3000) {
|
|
|
|
commanded_roll = plane.guided_state.forced_rpy_cd.x;
|
2016-05-09 11:34:11 -03:00
|
|
|
}
|
|
|
|
|
|
|
|
nav_roll_cd = constrain_int32(commanded_roll, -roll_limit_cd, roll_limit_cd);
|
2014-11-11 22:35:34 -04:00
|
|
|
update_load_factor();
|
2011-09-08 22:29:39 -03:00
|
|
|
}
|
|
|
|
|
2014-08-03 04:16:51 -03:00
|
|
|
/*
|
|
|
|
adjust nav_pitch_cd for STAB_PITCH_DOWN_CD. This is used to make
|
|
|
|
keeping up good airspeed in FBWA mode easier, as the plane will
|
|
|
|
automatically pitch down a little when at low throttle. It makes
|
|
|
|
FBWA landings without stalling much easier.
|
|
|
|
*/
|
2015-05-13 03:09:36 -03:00
|
|
|
void Plane::adjust_nav_pitch_throttle(void)
|
2014-08-03 04:16:51 -03:00
|
|
|
{
|
2016-01-30 02:38:31 -04:00
|
|
|
int8_t throttle = throttle_percentage();
|
2016-12-13 22:20:57 -04:00
|
|
|
if (throttle >= 0 && throttle < aparm.throttle_cruise && flight_stage != AP_Vehicle::FixedWing::FLIGHT_VTOL) {
|
2014-08-03 04:16:51 -03:00
|
|
|
float p = (aparm.throttle_cruise - throttle) / (float)aparm.throttle_cruise;
|
2014-08-05 22:46:40 -03:00
|
|
|
nav_pitch_cd -= g.stab_pitch_down * 100.0f * p;
|
2014-08-03 04:16:51 -03:00
|
|
|
}
|
|
|
|
}
|
2014-11-11 22:35:34 -04:00
|
|
|
|
|
|
|
|
|
|
|
/*
|
|
|
|
calculate a new aerodynamic_load_factor and limit nav_roll_cd to
|
|
|
|
ensure that the load factor does not take us below the sustainable
|
|
|
|
airspeed
|
|
|
|
*/
|
2015-05-13 03:09:36 -03:00
|
|
|
void Plane::update_load_factor(void)
|
2014-11-11 22:35:34 -04:00
|
|
|
{
|
|
|
|
float demanded_roll = fabsf(nav_roll_cd*0.01f);
|
|
|
|
if (demanded_roll > 85) {
|
|
|
|
// limit to 85 degrees to prevent numerical errors
|
|
|
|
demanded_roll = 85;
|
|
|
|
}
|
2015-05-15 12:54:46 -03:00
|
|
|
aerodynamic_load_factor = 1.0f / safe_sqrt(cosf(radians(demanded_roll)));
|
2014-11-11 22:35:34 -04:00
|
|
|
|
2017-10-29 03:31:09 -03:00
|
|
|
if (quadplane.in_transition() &&
|
|
|
|
(quadplane.options & QuadPlane::OPTION_LEVEL_TRANSITION)) {
|
2018-12-30 18:46:14 -04:00
|
|
|
// the user wants transitions to be kept level to within LEVEL_ROLL_LIMIT
|
2017-10-29 03:31:09 -03:00
|
|
|
roll_limit_cd = MIN(roll_limit_cd, g.level_roll_limit*100);
|
2018-12-30 18:46:14 -04:00
|
|
|
nav_roll_cd = constrain_int32(nav_roll_cd, -roll_limit_cd, roll_limit_cd);
|
|
|
|
return;
|
2017-10-29 03:31:09 -03:00
|
|
|
}
|
|
|
|
|
2014-11-12 23:06:00 -04:00
|
|
|
if (!aparm.stall_prevention) {
|
|
|
|
// stall prevention is disabled
|
|
|
|
return;
|
|
|
|
}
|
|
|
|
if (fly_inverted()) {
|
|
|
|
// no roll limits when inverted
|
|
|
|
return;
|
|
|
|
}
|
2017-02-11 04:12:56 -04:00
|
|
|
if (quadplane.tailsitter_active()) {
|
|
|
|
// no limits while hovering
|
|
|
|
return;
|
|
|
|
}
|
|
|
|
|
2014-11-12 23:06:00 -04:00
|
|
|
|
2017-11-19 01:04:40 -04:00
|
|
|
float max_load_factor = smoothed_airspeed / MAX(aparm.airspeed_min, 1);
|
2014-11-11 22:35:34 -04:00
|
|
|
if (max_load_factor <= 1) {
|
|
|
|
// our airspeed is below the minimum airspeed. Limit roll to
|
|
|
|
// 25 degrees
|
|
|
|
nav_roll_cd = constrain_int32(nav_roll_cd, -2500, 2500);
|
2018-12-26 18:36:12 -04:00
|
|
|
roll_limit_cd = MIN(roll_limit_cd, 2500);
|
2014-11-11 22:35:34 -04:00
|
|
|
} else if (max_load_factor < aerodynamic_load_factor) {
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// the demanded nav_roll would take us past the aerodymamic
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// load limit. Limit our roll to a bank angle that will keep
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// the load within what the airframe can handle. We always
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// allow at least 25 degrees of roll however, to ensure the
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// aircraft can be maneuvered with a bad airspeed estimate. At
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// 25 degrees the load factor is 1.1 (10%)
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int32_t roll_limit = degrees(acosf(sq(1.0f / max_load_factor)))*100;
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if (roll_limit < 2500) {
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roll_limit = 2500;
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}
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nav_roll_cd = constrain_int32(nav_roll_cd, -roll_limit, roll_limit);
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2018-12-26 18:36:12 -04:00
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roll_limit_cd = MIN(roll_limit_cd, roll_limit);
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2014-11-11 22:35:34 -04:00
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}
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}
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