mirror of https://github.com/ArduPilot/ardupilot
504 lines
21 KiB
C++
504 lines
21 KiB
C++
#include "AC_AttitudeControl_Multi.h"
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#include <AP_HAL/AP_HAL.h>
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#include <AP_Math/AP_Math.h>
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#include <AC_PID/AC_PID.h>
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#include <AP_Scheduler/AP_Scheduler.h>
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// table of user settable parameters
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const AP_Param::GroupInfo AC_AttitudeControl_Multi::var_info[] = {
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// parameters from parent vehicle
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AP_NESTEDGROUPINFO(AC_AttitudeControl, 0),
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// @Param: RAT_RLL_P
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// @DisplayName: Roll axis rate controller P gain
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// @Description: Roll axis rate controller P gain. Corrects in proportion to the difference between the desired roll rate vs actual roll rate
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// @Range: 0.01 0.5
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// @Increment: 0.005
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// @User: Standard
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// @Param: RAT_RLL_I
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// @DisplayName: Roll axis rate controller I gain
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// @Description: Roll axis rate controller I gain. Corrects long-term difference in desired roll rate vs actual roll rate
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// @Range: 0.01 2.0
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// @Increment: 0.01
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// @User: Standard
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// @Param: RAT_RLL_IMAX
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// @DisplayName: Roll axis rate controller I gain maximum
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// @Description: Roll axis rate controller I gain maximum. Constrains the maximum that the I term will output
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// @Range: 0 1
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// @Increment: 0.01
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// @User: Standard
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// @Param: RAT_RLL_D
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// @DisplayName: Roll axis rate controller D gain
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// @Description: Roll axis rate controller D gain. Compensates for short-term change in desired roll rate vs actual roll rate
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// @Range: 0.0 0.05
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// @Increment: 0.001
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// @User: Standard
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// @Param: RAT_RLL_FF
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// @DisplayName: Roll axis rate controller feed forward
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// @Description: Roll axis rate controller feed forward
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// @Range: 0 0.5
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// @Increment: 0.001
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// @User: Standard
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// @Param: RAT_RLL_FLTT
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// @DisplayName: Roll axis rate controller target frequency in Hz
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// @Description: Roll axis rate controller target frequency in Hz
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// @Range: 5 100
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// @Increment: 1
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// @Units: Hz
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// @User: Standard
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// @Param: RAT_RLL_FLTE
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// @DisplayName: Roll axis rate controller error frequency in Hz
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// @Description: Roll axis rate controller error frequency in Hz
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// @Range: 0 100
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// @Increment: 1
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// @Units: Hz
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// @User: Standard
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// @Param: RAT_RLL_FLTD
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// @DisplayName: Roll axis rate controller derivative frequency in Hz
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// @Description: Roll axis rate controller derivative frequency in Hz
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// @Range: 5 100
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// @Increment: 1
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// @Units: Hz
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// @User: Standard
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// @Param: RAT_RLL_SMAX
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// @DisplayName: Roll slew rate limit
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// @Description: Sets an upper limit on the slew rate produced by the combined P and D gains. If the amplitude of the control action produced by the rate feedback exceeds this value, then the D+P gain is reduced to respect the limit. This limits the amplitude of high frequency oscillations caused by an excessive gain. The limit should be set to no more than 25% of the actuators maximum slew rate to allow for load effects. Note: The gain will not be reduced to less than 10% of the nominal value. A value of zero will disable this feature.
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// @Range: 0 200
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// @Increment: 0.5
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// @User: Advanced
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// @Param: RAT_RLL_PDMX
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// @DisplayName: Roll axis rate controller PD sum maximum
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// @Description: Roll axis rate controller PD sum maximum. The maximum/minimum value that the sum of the P and D term can output
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// @Range: 0 1
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// @Increment: 0.01
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// @Param: RAT_RLL_D_FF
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// @DisplayName: Roll Derivative FeedForward Gain
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// @Description: FF D Gain which produces an output that is proportional to the rate of change of the target
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// @Range: 0 0.02
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// @Increment: 0.0001
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// @User: Advanced
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// @Param: RAT_RLL_NTF
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// @DisplayName: Roll Target notch filter index
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// @Description: Roll Target notch filter index
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// @Range: 1 8
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// @User: Advanced
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// @Param: RAT_RLL_NEF
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// @DisplayName: Roll Error notch filter index
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// @Description: Roll Error notch filter index
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// @Range: 1 8
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// @User: Advanced
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AP_SUBGROUPINFO(_pid_rate_roll, "RAT_RLL_", 1, AC_AttitudeControl_Multi, AC_PID),
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// @Param: RAT_PIT_P
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// @DisplayName: Pitch axis rate controller P gain
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// @Description: Pitch axis rate controller P gain. Corrects in proportion to the difference between the desired pitch rate vs actual pitch rate output
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// @Range: 0.01 0.50
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// @Increment: 0.005
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// @User: Standard
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// @Param: RAT_PIT_I
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// @DisplayName: Pitch axis rate controller I gain
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// @Description: Pitch axis rate controller I gain. Corrects long-term difference in desired pitch rate vs actual pitch rate
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// @Range: 0.01 2.0
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// @Increment: 0.01
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// @User: Standard
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// @Param: RAT_PIT_IMAX
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// @DisplayName: Pitch axis rate controller I gain maximum
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// @Description: Pitch axis rate controller I gain maximum. Constrains the maximum that the I term will output
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// @Range: 0 1
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// @Increment: 0.01
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// @User: Standard
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// @Param: RAT_PIT_D
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// @DisplayName: Pitch axis rate controller D gain
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// @Description: Pitch axis rate controller D gain. Compensates for short-term change in desired pitch rate vs actual pitch rate
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// @Range: 0.0 0.05
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// @Increment: 0.001
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// @User: Standard
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// @Param: RAT_PIT_FF
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// @DisplayName: Pitch axis rate controller feed forward
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// @Description: Pitch axis rate controller feed forward
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// @Range: 0 0.5
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// @Increment: 0.001
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// @User: Standard
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// @Param: RAT_PIT_FLTT
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// @DisplayName: Pitch axis rate controller target frequency in Hz
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// @Description: Pitch axis rate controller target frequency in Hz
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// @Range: 5 100
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// @Increment: 1
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// @Units: Hz
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// @User: Standard
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// @Param: RAT_PIT_FLTE
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// @DisplayName: Pitch axis rate controller error frequency in Hz
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// @Description: Pitch axis rate controller error frequency in Hz
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// @Range: 0 100
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// @Increment: 1
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// @Units: Hz
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// @User: Standard
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// @Param: RAT_PIT_FLTD
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// @DisplayName: Pitch axis rate controller derivative frequency in Hz
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// @Description: Pitch axis rate controller derivative frequency in Hz
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// @Range: 5 100
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// @Increment: 1
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// @Units: Hz
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// @User: Standard
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// @Param: RAT_PIT_SMAX
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// @DisplayName: Pitch slew rate limit
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// @Description: Sets an upper limit on the slew rate produced by the combined P and D gains. If the amplitude of the control action produced by the rate feedback exceeds this value, then the D+P gain is reduced to respect the limit. This limits the amplitude of high frequency oscillations caused by an excessive gain. The limit should be set to no more than 25% of the actuators maximum slew rate to allow for load effects. Note: The gain will not be reduced to less than 10% of the nominal value. A value of zero will disable this feature.
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// @Range: 0 200
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// @Increment: 0.5
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// @User: Advanced
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// @Param: RAT_PIT_PDMX
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// @DisplayName: Pitch axis rate controller PD sum maximum
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// @Description: Pitch axis rate controller PD sum maximum. The maximum/minimum value that the sum of the P and D term can output
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// @Range: 0 1
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// @Increment: 0.01
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// @Param: RAT_PIT_D_FF
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// @DisplayName: Pitch Derivative FeedForward Gain
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// @Description: FF D Gain which produces an output that is proportional to the rate of change of the target
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// @Range: 0 0.02
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// @Increment: 0.0001
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// @User: Advanced
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// @Param: RAT_PIT_NTF
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// @DisplayName: Pitch Target notch filter index
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// @Description: Pitch Target notch filter index
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// @Range: 1 8
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// @User: Advanced
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// @Param: RAT_PIT_NEF
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// @DisplayName: Pitch Error notch filter index
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// @Description: Pitch Error notch filter index
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// @Range: 1 8
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// @User: Advanced
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AP_SUBGROUPINFO(_pid_rate_pitch, "RAT_PIT_", 2, AC_AttitudeControl_Multi, AC_PID),
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// @Param: RAT_YAW_P
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// @DisplayName: Yaw axis rate controller P gain
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// @Description: Yaw axis rate controller P gain. Corrects in proportion to the difference between the desired yaw rate vs actual yaw rate
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// @Range: 0.10 2.50
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// @Increment: 0.005
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// @User: Standard
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// @Param: RAT_YAW_I
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// @DisplayName: Yaw axis rate controller I gain
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// @Description: Yaw axis rate controller I gain. Corrects long-term difference in desired yaw rate vs actual yaw rate
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// @Range: 0.010 1.0
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// @Increment: 0.01
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// @User: Standard
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// @Param: RAT_YAW_IMAX
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// @DisplayName: Yaw axis rate controller I gain maximum
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// @Description: Yaw axis rate controller I gain maximum. Constrains the maximum that the I term will output
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// @Range: 0 1
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// @Increment: 0.01
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// @User: Standard
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// @Param: RAT_YAW_D
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// @DisplayName: Yaw axis rate controller D gain
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// @Description: Yaw axis rate controller D gain. Compensates for short-term change in desired yaw rate vs actual yaw rate
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// @Range: 0.000 0.02
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// @Increment: 0.001
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// @User: Standard
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// @Param: RAT_YAW_FF
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// @DisplayName: Yaw axis rate controller feed forward
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// @Description: Yaw axis rate controller feed forward
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// @Range: 0 0.5
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// @Increment: 0.001
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// @User: Standard
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// @Param: RAT_YAW_FLTT
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// @DisplayName: Yaw axis rate controller target frequency in Hz
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// @Description: Yaw axis rate controller target frequency in Hz
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// @Range: 1 50
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// @Increment: 1
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// @Units: Hz
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// @User: Standard
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// @Param: RAT_YAW_FLTE
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// @DisplayName: Yaw axis rate controller error frequency in Hz
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// @Description: Yaw axis rate controller error frequency in Hz
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// @Range: 0 20
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// @Increment: 1
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// @Units: Hz
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// @User: Standard
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// @Param: RAT_YAW_FLTD
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// @DisplayName: Yaw axis rate controller derivative frequency in Hz
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// @Description: Yaw axis rate controller derivative frequency in Hz
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// @Range: 5 50
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// @Increment: 1
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// @Units: Hz
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// @User: Standard
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// @Param: RAT_YAW_SMAX
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// @DisplayName: Yaw slew rate limit
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// @Description: Sets an upper limit on the slew rate produced by the combined P and D gains. If the amplitude of the control action produced by the rate feedback exceeds this value, then the D+P gain is reduced to respect the limit. This limits the amplitude of high frequency oscillations caused by an excessive gain. The limit should be set to no more than 25% of the actuators maximum slew rate to allow for load effects. Note: The gain will not be reduced to less than 10% of the nominal value. A value of zero will disable this feature.
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// @Range: 0 200
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// @Increment: 0.5
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// @User: Advanced
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// @Param: RAT_YAW_PDMX
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// @DisplayName: Yaw axis rate controller PD sum maximum
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// @Description: Yaw axis rate controller PD sum maximum. The maximum/minimum value that the sum of the P and D term can output
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// @Range: 0 1
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// @Increment: 0.01
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// @Param: RAT_YAW_D_FF
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// @DisplayName: Yaw Derivative FeedForward Gain
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// @Description: FF D Gain which produces an output that is proportional to the rate of change of the target
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// @Range: 0 0.02
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// @Increment: 0.0001
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// @User: Advanced
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// @Param: RAT_YAW_NTF
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// @DisplayName: Yaw Target notch filter index
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// @Description: Yaw Target notch filter index
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// @Range: 1 8
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// @Units: Hz
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// @User: Advanced
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// @Param: RAT_YAW_NEF
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// @DisplayName: Yaw Error notch filter index
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// @Description: Yaw Error notch filter index
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// @Range: 1 8
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// @User: Advanced
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AP_SUBGROUPINFO(_pid_rate_yaw, "RAT_YAW_", 3, AC_AttitudeControl_Multi, AC_PID),
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// @Param: THR_MIX_MIN
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// @DisplayName: Throttle Mix Minimum
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// @Description: Throttle vs attitude control prioritisation used when landing (higher values mean we prioritise attitude control over throttle)
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// @Range: 0.1 0.25
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// @User: Advanced
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AP_GROUPINFO("THR_MIX_MIN", 4, AC_AttitudeControl_Multi, _thr_mix_min, AC_ATTITUDE_CONTROL_MIN_DEFAULT),
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// @Param: THR_MIX_MAX
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// @DisplayName: Throttle Mix Maximum
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// @Description: Throttle vs attitude control prioritisation used during active flight (higher values mean we prioritise attitude control over throttle)
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// @Range: 0.5 0.9
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// @User: Advanced
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AP_GROUPINFO("THR_MIX_MAX", 5, AC_AttitudeControl_Multi, _thr_mix_max, AC_ATTITUDE_CONTROL_MAX_DEFAULT),
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// @Param: THR_MIX_MAN
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// @DisplayName: Throttle Mix Manual
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// @Description: Throttle vs attitude control prioritisation used during manual flight (higher values mean we prioritise attitude control over throttle)
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// @Range: 0.1 0.9
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// @User: Advanced
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AP_GROUPINFO("THR_MIX_MAN", 6, AC_AttitudeControl_Multi, _thr_mix_man, AC_ATTITUDE_CONTROL_MAN_DEFAULT),
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// @Param: THR_G_BOOST
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// @DisplayName: Throttle-gain boost
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// @Description: Throttle-gain boost ratio. A value of 0 means no boosting is applied, a value of 1 means full boosting is applied. Describes the ratio increase that is applied to angle P and PD on pitch and roll.
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// @Range: 0 1
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// @User: Advanced
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AP_GROUPINFO("THR_G_BOOST", 7, AC_AttitudeControl_Multi, _throttle_gain_boost, 0.0f),
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AP_GROUPEND
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};
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AC_AttitudeControl_Multi::AC_AttitudeControl_Multi(AP_AHRS_View &ahrs, const AP_MultiCopter &aparm, AP_MotorsMulticopter& motors) :
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AC_AttitudeControl(ahrs, aparm, motors),
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_motors_multi(motors)
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{
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AP_Param::setup_object_defaults(this, var_info);
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#if AP_FILTER_ENABLED
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set_notch_sample_rate(AP::scheduler().get_loop_rate_hz());
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#endif
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}
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// Update Alt_Hold angle maximum
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void AC_AttitudeControl_Multi::update_althold_lean_angle_max(float throttle_in)
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{
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// calc maximum tilt angle based on throttle
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float thr_max = _motors_multi.get_throttle_thrust_max();
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// divide by zero check
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if (is_zero(thr_max)) {
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_althold_lean_angle_max = 0.0f;
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return;
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}
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float althold_lean_angle_max = acosf(constrain_float(throttle_in / (AC_ATTITUDE_CONTROL_ANGLE_LIMIT_THROTTLE_MAX * thr_max), 0.0f, 1.0f));
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_althold_lean_angle_max = _althold_lean_angle_max + (_dt / (_dt + _angle_limit_tc)) * (althold_lean_angle_max - _althold_lean_angle_max);
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}
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void AC_AttitudeControl_Multi::set_throttle_out(float throttle_in, bool apply_angle_boost, float filter_cutoff)
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{
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_throttle_in = throttle_in;
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update_althold_lean_angle_max(throttle_in);
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_motors.set_throttle_filter_cutoff(filter_cutoff);
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if (apply_angle_boost) {
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// Apply angle boost
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throttle_in = get_throttle_boosted(throttle_in);
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} else {
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// Clear angle_boost for logging purposes
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_angle_boost = 0.0f;
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}
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_motors.set_throttle(throttle_in);
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_motors.set_throttle_avg_max(get_throttle_avg_max(MAX(throttle_in, _throttle_in)));
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}
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void AC_AttitudeControl_Multi::set_throttle_mix_max(float ratio)
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{
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ratio = constrain_float(ratio, 0.0f, 1.0f);
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_throttle_rpy_mix_desired = (1.0f - ratio) * _thr_mix_min + ratio * _thr_mix_max;
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}
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// returns a throttle including compensation for roll/pitch angle
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// throttle value should be 0 ~ 1
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float AC_AttitudeControl_Multi::get_throttle_boosted(float throttle_in)
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{
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if (!_angle_boost_enabled) {
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_angle_boost = 0;
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return throttle_in;
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}
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// inverted_factor is 1 for tilt angles below 60 degrees
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// inverted_factor reduces from 1 to 0 for tilt angles between 60 and 90 degrees
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float cos_tilt = _ahrs.cos_pitch() * _ahrs.cos_roll();
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float inverted_factor = constrain_float(10.0f * cos_tilt, 0.0f, 1.0f);
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float cos_tilt_target = cosf(_thrust_angle);
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float boost_factor = 1.0f / constrain_float(cos_tilt_target, 0.1f, 1.0f);
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float throttle_out = throttle_in * inverted_factor * boost_factor;
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_angle_boost = constrain_float(throttle_out - throttle_in, -1.0f, 1.0f);
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return throttle_out;
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}
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// returns a throttle including compensation for roll/pitch angle
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// throttle value should be 0 ~ 1
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float AC_AttitudeControl_Multi::get_throttle_avg_max(float throttle_in)
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{
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throttle_in = constrain_float(throttle_in, 0.0f, 1.0f);
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return MAX(throttle_in, throttle_in * MAX(0.0f, 1.0f - _throttle_rpy_mix) + _motors.get_throttle_hover() * _throttle_rpy_mix);
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}
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// update_throttle_gain_boost - boost angle_p/pd each cycle on high throttle slew
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void AC_AttitudeControl_Multi::update_throttle_gain_boost()
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{
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// Boost PD and Angle P on very rapid throttle changes
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if (_motors.get_throttle_slew_rate() > AC_ATTITUDE_CONTROL_THR_G_BOOST_THRESH) {
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const float pd_boost = constrain_float(_throttle_gain_boost + 1.0f, 1.0, 2.0);
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set_PD_scale_mult(Vector3f(pd_boost, pd_boost, 1.0f));
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const float angle_p_boost = constrain_float((_throttle_gain_boost + 1.0f) * (_throttle_gain_boost + 1.0f), 1.0, 4.0);
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set_angle_P_scale_mult(Vector3f(angle_p_boost, angle_p_boost, 1.0f));
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}
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}
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// update_throttle_rpy_mix - slew set_throttle_rpy_mix to requested value
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void AC_AttitudeControl_Multi::update_throttle_rpy_mix()
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{
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// slew _throttle_rpy_mix to _throttle_rpy_mix_desired
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if (_throttle_rpy_mix < _throttle_rpy_mix_desired) {
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// increase quickly (i.e. from 0.1 to 0.9 in 0.4 seconds)
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_throttle_rpy_mix += MIN(2.0f * _dt, _throttle_rpy_mix_desired - _throttle_rpy_mix);
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} else if (_throttle_rpy_mix > _throttle_rpy_mix_desired) {
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// reduce more slowly (from 0.9 to 0.1 in 1.6 seconds)
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_throttle_rpy_mix -= MIN(0.5f * _dt, _throttle_rpy_mix - _throttle_rpy_mix_desired);
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// if the mix is still higher than that being used, reset immediately
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const float throttle_hover = _motors.get_throttle_hover();
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const float throttle_in = _motors.get_throttle();
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const float throttle_out = MAX(_motors.get_throttle_out(), throttle_in);
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float mix_used;
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// since throttle_out >= throttle_in at this point we don't need to check throttle_in < throttle_hover
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if (throttle_out < throttle_hover) {
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mix_used = (throttle_out - throttle_in) / (throttle_hover - throttle_in);
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} else {
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mix_used = throttle_out / throttle_hover;
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}
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_throttle_rpy_mix = MIN(_throttle_rpy_mix, MAX(mix_used, _throttle_rpy_mix_desired));
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}
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_throttle_rpy_mix = constrain_float(_throttle_rpy_mix, 0.1f, AC_ATTITUDE_CONTROL_MAX);
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}
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void AC_AttitudeControl_Multi::rate_controller_run()
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{
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// boost angle_p/pd each cycle on high throttle slew
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update_throttle_gain_boost();
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|
|
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// move throttle vs attitude mixing towards desired (called from here because this is conveniently called on every iteration)
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update_throttle_rpy_mix();
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|
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_ang_vel_body += _sysid_ang_vel_body;
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|
|
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_rate_gyro = _ahrs.get_gyro_latest();
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_rate_gyro_time_us = AP_HAL::micros64();
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|
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_motors.set_roll(get_rate_roll_pid().update_all(_ang_vel_body.x, _rate_gyro.x, _dt, _motors.limit.roll, _pd_scale.x) + _actuator_sysid.x);
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_motors.set_roll_ff(get_rate_roll_pid().get_ff());
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|
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_motors.set_pitch(get_rate_pitch_pid().update_all(_ang_vel_body.y, _rate_gyro.y, _dt, _motors.limit.pitch, _pd_scale.y) + _actuator_sysid.y);
|
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_motors.set_pitch_ff(get_rate_pitch_pid().get_ff());
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|
|
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_motors.set_yaw(get_rate_yaw_pid().update_all(_ang_vel_body.z, _rate_gyro.z, _dt, _motors.limit.yaw, _pd_scale.z) + _actuator_sysid.z);
|
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_motors.set_yaw_ff(get_rate_yaw_pid().get_ff()*_feedforward_scalar);
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|
|
|
_sysid_ang_vel_body.zero();
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|
_actuator_sysid.zero();
|
|
|
|
_pd_scale_used = _pd_scale;
|
|
_pd_scale = VECTORF_111;
|
|
|
|
control_monitor_update();
|
|
}
|
|
|
|
// sanity check parameters. should be called once before takeoff
|
|
void AC_AttitudeControl_Multi::parameter_sanity_check()
|
|
{
|
|
// sanity check throttle mix parameters
|
|
if (_thr_mix_man < 0.1f || _thr_mix_man > AC_ATTITUDE_CONTROL_MAN_LIMIT) {
|
|
// parameter description recommends thr-mix-man be no higher than 0.9 but we allow up to 4.0
|
|
// which can be useful for very high powered copters with very low hover throttle
|
|
_thr_mix_man.set_and_save(constrain_float(_thr_mix_man, 0.1, AC_ATTITUDE_CONTROL_MAN_LIMIT));
|
|
}
|
|
if (_thr_mix_min < 0.1f || _thr_mix_min > AC_ATTITUDE_CONTROL_MIN_LIMIT) {
|
|
_thr_mix_min.set_and_save(constrain_float(_thr_mix_min, 0.1, AC_ATTITUDE_CONTROL_MIN_LIMIT));
|
|
}
|
|
if (_thr_mix_max < 0.5f || _thr_mix_max > AC_ATTITUDE_CONTROL_MAX) {
|
|
// parameter description recommends thr-mix-max be no higher than 0.9 but we allow up to 5.0
|
|
// which can be useful for very high powered copters with very low hover throttle
|
|
_thr_mix_max.set_and_save(constrain_float(_thr_mix_max, 0.5, AC_ATTITUDE_CONTROL_MAX));
|
|
}
|
|
if (_thr_mix_min > _thr_mix_max) {
|
|
_thr_mix_min.set_and_save(AC_ATTITUDE_CONTROL_MIN_DEFAULT);
|
|
_thr_mix_max.set_and_save(AC_ATTITUDE_CONTROL_MAX_DEFAULT);
|
|
}
|
|
}
|
|
|
|
void AC_AttitudeControl_Multi::set_notch_sample_rate(float sample_rate)
|
|
{
|
|
#if AP_FILTER_ENABLED
|
|
_pid_rate_roll.set_notch_sample_rate(sample_rate);
|
|
_pid_rate_pitch.set_notch_sample_rate(sample_rate);
|
|
_pid_rate_yaw.set_notch_sample_rate(sample_rate);
|
|
#endif
|
|
}
|