Difference between revisions of "Subsystem/ahrs"
(→DCM (floating point)) |
(→DCM (floating point)) |
||
Line 94: | Line 94: | ||
=== DCM (floating point) === | === DCM (floating point) === | ||
Similar in principle to the ''float_cmpl_rmat'' filter (but less cleanly written). | Similar in principle to the ''float_cmpl_rmat'' filter (but less cleanly written). | ||
− | The main advantages are: 1. using the centrifugal force in z direction for calculating the attitude (you can fly circles for long time without any problems) 2. Correcting the matrix elements of the direct cosine matrix for every calculation step (typ. every 25ms) to archive the orthogonality of the matrix (small errors of the integration and calculations are not accumulated, the algorithm gives almost exact results). The algorithms was developed by William Premerlani and Paul Bizard. The theory can be found here | + | The main advantages are: 1. using the centrifugal force in z direction for calculating the attitude (you can fly circles for long time without any problems) 2. Correcting the matrix elements of the direct cosine matrix for every calculation step (typ. every 25ms) to archive the orthogonality of the matrix (small errors of the integration and calculations are not accumulated, the algorithm gives almost exact results). The algorithms was developed by William Premerlani and Paul Bizard. The theory can be found here The algorithm is also used in the AHS system. |
Other flags of interest are: | Other flags of interest are: |
Revision as of 01:56, 6 January 2012
Contents
AHRS subsystem
The AHRS subsystem specifies which attitude estimation filter you are using.
Currently possible AHRS subsystems are
- int_cmpl_quat
- int_cmpl_euler
- float_cmpl_rmat
- float_dcm
e.g. for the latest complementary filter:
File: conf/airframes/myplane.xml |
<firmware name="fixedwing or rotorcraft"> ... <subsystem name="ahrs" type="int_cmpl_quat"/> </firmware> |
Implementations
There is a test program ( sw/airborne/test/ahrs/compare_ahrs.py ) to compare different AHRS implementations on simple test cases.
Complementary Euler (fixed point)
Not recommended for fixedwings, as this filter doesn't compensate for centrifugal force when flying turns.
File: conf/airframes/myplane.xml |
<firmware name="fixedwing or rotorcraft"> ... <subsystem name="ahrs" type="int_cmpl_euler"/> </firmware> <section name="MISC"> <define name="FACE_REINJ_1" value="1024"/> <!-- optional, defaults to 1024 --> </section> |
Complementary Quaternion (fixed point)
If you are NOT using the dev branch, this is currently not recommended for fixedwings, as this filter doesn't compensate for centrifugal force when flying turns. In the dev branch this is fixed (but untested) and the needed AHRS_GRAVITY_UPDATE_COORDINATED_TURN already set by default for a fixedwing firmware.
Other flags of interest are:
- AHRS_PROPAGATE_LOW_PASS_RATES : apply a low pass filter on rotational velocity
- AHRS_MAG_UPDATE_YAW_ONLY : use mag to update yaw only
For the latest integer complementary quaternion filter (int_cmpl_quat):
File: conf/airframes/myplane.xml |
<firmware name="rotorcraft"> ... <subsystem name="ahrs" type="int_cmpl_quat"/> </firmware> <section name="AHRS" prefix="AHRS_"> <define name="H_X" value=" 0.51562740288882"/> <define name="H_Y" value="-0.05707735220832"/> <define name="H_Z" value=" 0.85490967783446"/> </section> |
Also see the Local Magnetic Field section.
Complementary Rotation Matrix (floating point)
If you are NOT using the dev branch, this is currently not recommended for fixedwings, as this filter doesn't compensate for centrifugal force when flying turns. In the dev branch this is fixed (but untested) and the needed AHRS_GRAVITY_UPDATE_COORDINATED_TURN already set by default for a fixedwing firmware.
Other flags of interest are:
- AHRS_PROPAGATE_LOW_PASS_RATES : apply a low pass filter on rotational velocity
- AHRS_MAG_UPDATE_YAW_ONLY : use mag to update yaw only
File: conf/airframes/myplane.xml |
<firmware name="rotorcraft or fixedwing"> ... <subsystem name="ahrs" type="float_cmpl_rmat"> <define name="AHRS_PROPAGATE_RMAT"/> </subsystem> </firmware> <section name="AHRS" prefix="AHRS_"> <define name="H_X" value=" 0.51562740288882"/> <define name="H_Y" value="-0.05707735220832"/> <define name="H_Z" value=" 0.85490967783446"/> </section> |
Also see the Local Magnetic Field section.
DCM (floating point)
Similar in principle to the float_cmpl_rmat filter (but less cleanly written). The main advantages are: 1. using the centrifugal force in z direction for calculating the attitude (you can fly circles for long time without any problems) 2. Correcting the matrix elements of the direct cosine matrix for every calculation step (typ. every 25ms) to archive the orthogonality of the matrix (small errors of the integration and calculations are not accumulated, the algorithm gives almost exact results). The algorithms was developed by William Premerlani and Paul Bizard. The theory can be found here The algorithm is also used in the AHS system.
Other flags of interest are:
- USE_MAGNETOMETER : use magnetometer to update yaw (untested ?)
File: conf/airframes/myplane.xml |
<firmware name="rotorcraft or fixedwing"> ... <subsystem name="ahrs" type="float_dcm"/> </firmware> |
Infrared
Local Magnetic Field
To calculate the normalised local magnetic field insert the relevant location coordinates hereand calculate.
Copy the north(x),east(y),vertical(z) component values into scilab and execute "X/norm(X)".