Plane: scale VTOL angle P gains with airspeed

During POSITION1 back-transiton we scale the MC angle P gains with
airspeed to reduce the chance of oscillations. At higher airspeeds the
fixed wing controller dominates so we should use the fixed wing angle
P gain.
This commit is contained in:
Andrew Tridgell 2022-10-08 20:41:42 +11:00
parent 56066eb470
commit 00b4b5b7ed
2 changed files with 50 additions and 0 deletions

View File

@ -2615,6 +2615,10 @@ void QuadPlane::vtol_position_controller(void)
// call attitude controller
disable_yaw_rate_time_constant();
// setup scaling of roll and pitch angle P gains to match fixed wing gains
setup_rp_fw_angle_gains();
if (have_target_yaw) {
attitude_control->input_euler_angle_roll_pitch_yaw(plane.nav_roll_cd,
plane.nav_pitch_cd,
@ -4330,4 +4334,45 @@ bool QuadPlane::landing_with_fixed_wing_spiral_approach(void) const
cmd.p1 == NAV_VTOL_LAND_OPTIONS_FW_SPIRAL_APPROACH));
}
/*
setup scaling of roll and pitch angle P gains to match fixed wing gains
we setup the angle P gain to match fixed wing at high speed (above
ARSPD_FBW_MIN) where fixed wing surfaces are presumed to
dominate. At lower speeds we use the multicopter angle P gains.
*/
void QuadPlane::setup_rp_fw_angle_gains(void)
{
const float mc_angR = attitude_control->get_angle_roll_p().kP();
const float mc_angP = attitude_control->get_angle_pitch_p().kP();
const float fw_angR = 1.0/plane.rollController.tau();
const float fw_angP = 1.0/plane.pitchController.tau();
if (!is_positive(mc_angR) || !is_positive(mc_angP)) {
// bad configuration, don't scale
return;
}
float aspeed;
if (!ahrs.airspeed_estimate(aspeed)) {
// can't get airspeed, no scaling of VTOL angle gains
return;
}
const float low_airspeed = 3.0;
if (aspeed <= low_airspeed || plane.aparm.airspeed_min <= low_airspeed) {
// no scaling
return;
}
const float angR_scale = linear_interpolate(mc_angR, fw_angR,
aspeed,
low_airspeed, plane.aparm.airspeed_min) / mc_angR;
const float angP_scale = linear_interpolate(mc_angP, fw_angP,
aspeed,
low_airspeed, plane.aparm.airspeed_min) / mc_angP;
const Vector3f gain_scale{angR_scale, angP_scale, 1.0};
attitude_control->set_angle_P_scale(gain_scale);
}
#endif // HAL_QUADPLANE_ENABLED

View File

@ -665,6 +665,11 @@ private:
*/
float get_scaled_wp_speed(float target_bearing_deg) const;
/*
setup scaling of roll and pitch angle P gains to match fixed wing gains
*/
void setup_rp_fw_angle_gains(void);
public:
void motor_test_output();
MAV_RESULT mavlink_motor_test_start(mavlink_channel_t chan, uint8_t motor_seq, uint8_t throttle_type,