diff options
| author | Anton Babushkin <anton.babushkin@me.com> | 2014-01-19 13:11:15 +0100 |
|---|---|---|
| committer | Anton Babushkin <anton.babushkin@me.com> | 2014-01-19 13:11:15 +0100 |
| commit | 18b28f0efd0fa308644eb69bc9c90f7378435542 (patch) | |
| tree | b6a9594ff10057daf43914a49438c4bd056e2281 /src/modules/mc_att_control/mc_att_control_main.cpp | |
| parent | 302632e7c45d455072dd89c6ecdf1637d1cf1977 (diff) | |
| download | px4-firmware-18b28f0efd0fa308644eb69bc9c90f7378435542.tar.gz px4-firmware-18b28f0efd0fa308644eb69bc9c90f7378435542.tar.bz2 px4-firmware-18b28f0efd0fa308644eb69bc9c90f7378435542.zip | |
Copyright and comments fixes
Diffstat (limited to 'src/modules/mc_att_control/mc_att_control_main.cpp')
| -rw-r--r-- | src/modules/mc_att_control/mc_att_control_main.cpp | 17 |
1 files changed, 13 insertions, 4 deletions
diff --git a/src/modules/mc_att_control/mc_att_control_main.cpp b/src/modules/mc_att_control/mc_att_control_main.cpp index 93974c742..646dc84e6 100644 --- a/src/modules/mc_att_control/mc_att_control_main.cpp +++ b/src/modules/mc_att_control/mc_att_control_main.cpp @@ -1,9 +1,9 @@ /**************************************************************************** * * Copyright (c) 2013, 2014 PX4 Development Team. All rights reserved. - * Author: Tobias Naegeli <naegelit@student.ethz.ch> - * Lorenz Meier <lm@inf.ethz.ch> - * Anton Babushkin <anton.babushkin@me.com> + * Author: @author Tobias Naegeli <naegelit@student.ethz.ch> + * @author Lorenz Meier <lm@inf.ethz.ch> + * @author Anton Babushkin <anton.babushkin@me.com> * * Redistribution and use in source and binary forms, with or without * modification, are permitted provided that the following conditions @@ -36,7 +36,16 @@ /** * @file mc_att_control_main.c - * Implementation of a multicopter attitude controller based on desired rotation matrix. + * Multicopter attitude controller. + * + * The controller has two loops: P loop for angular error and PD loop for angular rate error. + * Desired rotation calculated keeping in mind that yaw response is normally slower than roll/pitch. + * For small deviations controller rotates copter to have shortest path of thrust vector and independently rotates around yaw, + * so actual rotation axis is not constant. For large deviations controller rotates copter around fixed axis. + * These two approaches fused seamlessly with weight depending on angular error. + * When thrust vector directed near-horizontally (e.g. roll ~= PI/2) yaw setpoint ignored because of singularity. + * Controller doesn't use Euler angles for work, they generated only for more human-friendly control and logging. + * If rotation matrix setpoint is invalid it will be generated from Euler angles for compatibility with old position controllers. */ #include <nuttx/config.h> |