stabilization_heli_indi module

INDI stabilization controller for helicopters

No detailed description...

Example for airframe file

Add to your firmware section:

<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

Module functions

Init Functions

These initialization functions are called once on startup.

• stabilization_attitude_heli_indi_init()

Files

Header Files

The following headers are automatically included in modules.h

• stabilization_attitude_heli_indi.h

Source Files

• /stabilization/stabilization_attitude_heli_indi.c

Raw stabilization_heli_indi.xml file:

<!DOCTYPE module SYSTEM "module.dtd">
 
<module name="stabilization_heli_indi" dir="stabilization" task="control">
  <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>
  <dep>
    <depends>stabilization_rotorcraft,@attitude_command</depends>
    <provides>commands</provides>
  </dep>
  <header>
    <file name="stabilization_attitude_heli_indi.h"/>
  </header>
  <init fun="stabilization_attitude_heli_indi_init()"/>
  <makefile target="ap|nps" firmware="rotorcraft">
    <file name="stabilization_attitude_heli_indi.c" dir="$(SRC_FIRMWARE)/stabilization"/>
  </makefile>
</module>