Paparazzi UAS  v5.15_devel-46-gd23ed71
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stabilization_heli_indi module

INDI stabilization controller for helicopters

No detailed description...

Example for airframe file

Add to your firmware section:

1 <module name="stabilization_heli_indi"/>

Module configuration options

Airframe file section

  • section name: RC_SETPOINT prefix: STABILIZATION_ATTITUDE_
    • name SP_MAX_PHI value: 45.
      Description: max setpoint for roll angle
    • name SP_MAX_THETA value: 45.
      Description: max setpoint for pitch angle
    • name SP_MAX_R value: 90.
      Description: max setpoint for yaw rate
    • name DEADBAND_R value: 250
      Description: deadband on yaw rate input
  • section name: ATTITUDE_REFERENCE prefix: STABILIZATION_ATTITUDE_
    • name REF_OMEGA_P value: 400
      Description: reference generator omega param on roll rate
    • name REF_ZETA_P value: 0.9
      Description: reference generator zeta param on roll rate
    • name REF_MAX_P value: 300.
      Description: reference generator max roll rate
    • name REF_MAX_PDOT value: RadOfDeg(7000.)
      Description: reference generator max roll acceleration
    • name REF_OMEGA_Q value: 400
      Description: reference generator omega param on pitch rate
    • name REF_ZETA_Q value: 0.9
      Description: reference generator zeta param on pitch rate
    • name REF_MAX_Q value: 300.
      Description: reference generator max pitch rate
    • name REF_MAX_QDOT value: RadOfDeg(7000.)
      Description: reference generator max pitch acceleration
    • name REF_OMEGA_R value: 250
      Description: reference generator omega param on yaw rate
    • name REF_ZETA_R value: 0.9
      Description: reference generator zeta param on yaw rate
    • name REF_MAX_R value: 180.
      Description: reference generator max yaw rate
    • name REF_MAX_RDOT value: RadOfDeg(1800.)
      Description: reference generator max yaw acceleration
  • section name: STABILIZATION_ATTITUDE_INDI prefix: STABILIZATION_INDI_
    • name G1_P value: 0.0639
      Description: control effectiveness G1 gain on roll rate
    • name G1_Q value: 0.0361
      Description: control effectiveness G1 gain on pitch rate
    • name G1_R value: 0.0022
      Description: control effectiveness G1 gain on yaw rate
    • name G2_R value: 0.1450
      Description: control effectiveness G2 gain on yaw rate
    • name REF_ERR_P value: 600.0
      Description: reference acceleration
    • name REF_ERR_Q value: 600.0
      Description: reference acceleration
    • name REF_ERR_R value: 600.0
      Description: reference acceleration
    • name REF_RATE_P value: 28.0
      Description: reference acceleration
    • name REF_RATE_Q value: 28.0
      Description: reference acceleration
    • name REF_RATE_R value: 28.0
      Description: reference acceleration
    • name MAX_R value: 120.0
      Description: max yaw rate
    • name FILT_CUTOFF value: 8.0
      Description: second order cutoff parameter
    • name ESTIMATION_FILT_CUTOFF value: 8.0
      Description: second order cutoff parameter
    • name ACT_DYN_P value: 0.1
      Description: first order actuator dynamics on roll rate
    • name ACT_DYN_Q value: 0.1
      Description: first order actuator dynamics on pitch rate
    • name ACT_DYN_R value: 0.1
      Description: first order actuator dynamics on yaw rate
    • name USE_ADAPTIVE value: FALSE|TRUE
      Description: enable adaptive gains
    • name ADAPTIVE_MU value: 0.0001
      Description: adaptation parameter

Auto-loaded modules

The following modules are automatically loaded (just as if you had added them in the airframe file)

  • module__stabilizationrotorcraft

Module functions

Init Functions

These initialization functions are called once on startup.

Files

Header Files

The following headers are automatically included in modules.h

Source Files

  • /stabilization/stabilization_attitude_heli_indi.c
  • /stabilization/stabilization_attitude_quat_transformations.c
  • /stabilization/stabilization_attitude_rc_setpoint.c

Raw stabilization_heli_indi.xml file:

<!DOCTYPE module SYSTEM "module.dtd">
<module name="stabilization_heli_indi" dir="stabilization">
<doc>
<description>
INDI stabilization controller for helicopters
</description>
<section name="RC_SETPOINT" prefix="STABILIZATION_ATTITUDE_">
<define name="SP_MAX_PHI" value="45." description="max setpoint for roll angle" unit="deg"/>
<define name="SP_MAX_THETA" value="45." description="max setpoint for pitch angle" unit="deg"/>
<define name="SP_MAX_R" value="90." description="max setpoint for yaw rate" unit="deg/s"/>
<define name="DEADBAND_R" value="250" description="deadband on yaw rate input"/>
</section>
<section name="ATTITUDE_REFERENCE" prefix="STABILIZATION_ATTITUDE_">
<define name="REF_OMEGA_P" value="400" description="reference generator omega param on roll rate" unit="deg/s"/>
<define name="REF_ZETA_P" value="0.9" description="reference generator zeta param on roll rate"/>
<define name="REF_MAX_P" value="300." description="reference generator max roll rate" unit="deg/s"/>
<define name="REF_MAX_PDOT" value="RadOfDeg(7000.)" description="reference generator max roll acceleration"/>
<define name="REF_OMEGA_Q" value="400" description="reference generator omega param on pitch rate" unit="deg/s"/>
<define name="REF_ZETA_Q" value="0.9" description="reference generator zeta param on pitch rate"/>
<define name="REF_MAX_Q" value="300." description="reference generator max pitch rate" unit="deg/s"/>
<define name="REF_MAX_QDOT" value="RadOfDeg(7000.)" description="reference generator max pitch acceleration"/>
<define name="REF_OMEGA_R" value="250" description="reference generator omega param on yaw rate" unit="deg/s"/>
<define name="REF_ZETA_R" value="0.9" description="reference generator zeta param on yaw rate"/>
<define name="REF_MAX_R" value="180." description="reference generator max yaw rate" unit="deg/s"/>
<define name="REF_MAX_RDOT" value="RadOfDeg(1800.)" description="reference generator max yaw acceleration"/>
</section>
<section name="STABILIZATION_ATTITUDE_INDI" prefix="STABILIZATION_INDI_">
<define name="G1_P" value="0.0639" description="control effectiveness G1 gain on roll rate"/>
<define name="G1_Q" value="0.0361" description="control effectiveness G1 gain on pitch rate"/>
<define name="G1_R" value="0.0022" description="control effectiveness G1 gain on yaw rate"/>
<define name="G2_R" value="0.1450" description="control effectiveness G2 gain on yaw rate"/>
<define name="REF_ERR_P" value="600.0" description="reference acceleration"/>
<define name="REF_ERR_Q" value="600.0" description="reference acceleration"/>
<define name="REF_ERR_R" value="600.0" description="reference acceleration"/>
<define name="REF_RATE_P" value="28.0" description="reference acceleration"/>
<define name="REF_RATE_Q" value="28.0" description="reference acceleration"/>
<define name="REF_RATE_R" value="28.0" description="reference acceleration"/>
<define name="MAX_R" value="120.0" description="max yaw rate" unit="deg/s"/>
<define name="FILT_CUTOFF" value="8.0" description="second order cutoff parameter"/>
<define name="ESTIMATION_FILT_CUTOFF" value="8.0" description="second order cutoff parameter"/>
<define name="ACT_DYN_P" value="0.1" description="first order actuator dynamics on roll rate"/>
<define name="ACT_DYN_Q" value="0.1" description="first order actuator dynamics on pitch rate"/>
<define name="ACT_DYN_R" value="0.1" description="first order actuator dynamics on yaw rate"/>
<define name="USE_ADAPTIVE" value="FALSE|TRUE" description="enable adaptive gains"/>
<define name="ADAPTIVE_MU" value="0.0001" description="adaptation parameter"/>
</section>
</doc>
<autoload name="stabilization" type="rotorcraft"/>
<header>
<file name="stabilization_attitude.h"/>
</header>
<init fun="stabilization_attitude_init()"/>
<makefile target="ap|nps" firmware="rotorcraft">
<file name="stabilization_attitude_heli_indi.c" dir="$(SRC_FIRMWARE)/stabilization"/>
<file name="stabilization_attitude_quat_transformations.c" dir="$(SRC_FIRMWARE)/stabilization"/>
<file name="stabilization_attitude_rc_setpoint.c" dir="$(SRC_FIRMWARE)/stabilization"/>
<define name="STABILIZATION_ATTITUDE_TYPE_INT"/>
<define name="STABILIZATION_ATTITUDE_TYPE_H" value="stabilization/stabilization_attitude_heli_indi.h" type="string"/>
</makefile>
</module>