Mirrors_Framework/PX4-Autopilot
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This commit is contained in:
Lorenz Meier
2014-05-07 14:14:31 +02:00
parent 319ce3de10 9f2d65eff5
commit 6a6feaf96c
104 changed files with 610 additions and 6673 deletions
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.gitignore
+2
View File
@@ -37,3 +37,5 @@ mavlink/include/mavlink/v0.9/
tags
.tags_sorted_by_file
.pydevproject
.ropeproject
*.orig
ROMFS/px4fmu_common/init.d/2100_mpx_easystar
+1 -1
View File
@@ -5,4 +5,4 @@
sh /etc/init.d/rc.fw_defaults
set MIXER FMU_RET
set MIXER easystar.mix
ROMFS/px4fmu_common/init.d/rc.io
+1 -1
View File
@@ -11,7 +11,7 @@ px4io recovery
# Adjust PX4IO update rate limit
#
set PX4IO_LIMIT 400
if hw_ver compare PX4FMU_V1
if ver hwcmp PX4FMU_V1
then
set PX4IO_LIMIT 200
fi
ROMFS/px4fmu_common/init.d/rc.logging
+1 -1
View File
@@ -5,7 +5,7 @@
if [ -d /fs/microsd ]
then
if hw_ver compare PX4FMU_V1
if ver hwcmp PX4FMU_V1
then
echo "Start sdlog2 at 50Hz"
sdlog2 start -r 50 -a -b 8 -t
ROMFS/px4fmu_common/init.d/rc.mc_defaults
+2 -2
View File
@@ -32,9 +32,9 @@ then
param set MPC_Z_VEL_D 0.0
param set MPC_Z_VEL_MAX 3
param set MPC_Z_FF 0.5
param set MPC_TILT_MAX 1.0
param set MPC_TILTMAX_AIR 45.0
param set MPC_TILTMAX_LND 15.0
param set MPC_LAND_SPEED 1.0
param set MPC_LAND_TILT 0.3
param set PE_VELNE_NOISE 0.5
param set PE_VELNE_NOISE 0.7
ROMFS/px4fmu_common/init.d/rc.sensors
+1 -1
View File
@@ -22,7 +22,7 @@ then
echo "[init] Using L3GD20(H)"
fi
if hw_ver compare PX4FMU_V2
if ver hwcmp PX4FMU_V2
then
if lsm303d start
then
ROMFS/px4fmu_common/init.d/rcS
+4 -4
View File
@@ -248,7 +248,7 @@ then
echo "[init] ERROR: PX4IO not found, disabling output"
# Avoid using ttyS0 for MAVLink on FMUv1
if hw_ver compare PX4FMU_V1
if ver hwcmp PX4FMU_V1
then
set FMU_MODE serial
fi
@@ -262,7 +262,7 @@ then
if [ $HIL == yes ]
then
set OUTPUT_MODE hil
if hw_ver compare PX4FMU_V1
if ver hwcmp PX4FMU_V1
then
set FMU_MODE serial
fi
@@ -308,7 +308,7 @@ then
tone_alarm $TUNE_OUT_ERROR
fi
if hw_ver compare PX4FMU_V1
if ver hwcmp PX4FMU_V1
then
if [ $FMU_MODE == pwm -o $FMU_MODE == gpio ]
then
@@ -383,7 +383,7 @@ then
tone_alarm $TUNE_OUT_ERROR
fi
if hw_ver compare PX4FMU_V1
if ver hwcmp PX4FMU_V1
then
if [ $FMU_MODE == pwm -o $FMU_MODE == gpio ]
then
ROMFS/px4fmu_common/mixers/easystar.mix
+31
View File
@@ -0,0 +1,31 @@
EASYSTAR / EASYSTAR II MIXER
============================
Aileron mixer
-------------
One output - would be easy to add support for 2 servos
M: 1
O: 10000 10000 0 -10000 10000
S: 0 0 10000 10000 0 -10000 10000
Elevator mixer
------------
M: 1
O: 10000 10000 0 -10000 10000
S: 0 1 -10000 -10000 0 -10000 10000
Rudder mixer
------------
M: 1
O: 10000 10000 0 -10000 10000
S: 0 2 -10000 -10000 0 -10000 10000
Motor speed mixer
-----------------
M: 1
O: 10000 10000 0 -10000 10000
S: 0 3 0 20000 -10000 -10000 10000
Tools/px_romfs_pruner.py
+15 -14
View File
@@ -43,29 +43,30 @@ from __future__ import print_function
import argparse
import os
def main():
# Parse commandline arguments
parser = argparse.ArgumentParser(description="ROMFS pruner.")
parser.add_argument('--folder', action="store", help="ROMFS scratch folder.")
args = parser.parse_args()
print("Pruning ROMFS files.")
# go through
# go through
for (root, dirs, files) in os.walk(args.folder):
for file in files:
# only prune text files
if ".zip" in file or ".bin" in file:
if ".zip" in file or ".bin" in file or ".swp" in file:
continue
file_path = os.path.join(root, file)
file_path = os.path.join(root, file)
# read file line by line
pruned_content = ""
with open(file_path, "r") as f:
for line in f:
for line in f:
# handle mixer files differently than startup files
if file_path.endswith(".mix"):
if line.startswith(("Z:", "M:", "R: ", "O:", "S:")):
@@ -73,11 +74,11 @@ def main():
else:
if not line.isspace() and not line.strip().startswith("#"):
pruned_content += line
# overwrite old scratch file
with open(file_path, "w") as f:
f.write(pruned_content)
if __name__ == '__main__':
main()
main()
Tools/tests-host/autodeclination_test.cpp
+1 -1
View File
@@ -25,4 +25,4 @@ int main(int argc, char *argv[]) {
printf("lat: %f lon: %f, dec: %f\n", lat, lon, declination);
}
}
Tools/tests-host/mixer_test.cpp
+1 -1
View File
@@ -11,4 +11,4 @@ int main(int argc, char *argv[]) {
test_mixer(3, args);
test_conv(1, args);
}
}
Tools/tests-host/sbus2_test.cpp
+1 -1
View File
@@ -72,4 +72,4 @@ int main(int argc, char *argv[]) {
warnx("Test aborted, errno: %d", ret);
}
}
}
makefiles/config_px4fmu-v1_default.mk
+1 -1
View File
@@ -55,8 +55,8 @@ MODULES += systemcmds/top
MODULES += systemcmds/tests
MODULES += systemcmds/config
MODULES += systemcmds/nshterm
MODULES += systemcmds/hw_ver
MODULES += systemcmds/dumpfile
MODULES += systemcmds/ver
#
# General system control
makefiles/config_px4fmu-v2_default.mk
+1 -1
View File
@@ -63,8 +63,8 @@ MODULES += systemcmds/tests
MODULES += systemcmds/config
MODULES += systemcmds/nshterm
MODULES += systemcmds/mtd
MODULES += systemcmds/hw_ver
MODULES += systemcmds/dumpfile
MODULES += systemcmds/ver
#
# General system control
makefiles/config_px4fmu-v2_test.mk
+1 -1
View File
@@ -29,7 +29,7 @@ MODULES += systemcmds/reboot
MODULES += systemcmds/tests
MODULES += systemcmds/nshterm
MODULES += systemcmds/mtd
MODULES += systemcmds/hw_ver
MODULES += systemcmds/ver
#
# Library modules
makefiles/firmware.mk
+4 -2
View File
@@ -113,7 +113,7 @@ endif
$(info % GIT_DESC = $(GIT_DESC))
#
# Set a default target so that included makefiles or errors here don't
# Set a default target so that included makefiles or errors here don't
# cause confusion.
#
# XXX We could do something cute here with $(DEFAULT_GOAL) if it's not one
@@ -177,7 +177,7 @@ GLOBAL_DEPS += $(MAKEFILE_LIST)
#
# Extra things we should clean
#
EXTRA_CLEANS =
EXTRA_CLEANS =
#
@@ -371,6 +371,8 @@ $(ROMFS_IMG): $(ROMFS_SCRATCH) $(ROMFS_DEPS) $(GLOBAL_DEPS)
$(ROMFS_SCRATCH): $(ROMFS_DEPS) $(GLOBAL_DEPS)
$(Q) $(MKDIR) -p $(ROMFS_SCRATCH)
$(Q) $(COPYDIR) $(ROMFS_ROOT)/* $(ROMFS_SCRATCH)
# delete all files in ROMFS_SCRATCH which start with a . or end with a ~
$(Q) $(RM) $(ROMFS_SCRATCH)/*/.[!.]* $(ROMFS_SCRATCH)/*/*~
ifneq ($(ROMFS_EXTRA_FILES),)
$(Q) $(MKDIR) -p $(ROMFS_SCRATCH)/extras
$(Q) $(COPY) $(ROMFS_EXTRA_FILES) $(ROMFS_SCRATCH)/extras
nuttx-configs/px4io-v2/include/board.h
-2
View File
@@ -103,8 +103,6 @@
#define GPIO_USART2_RTS 0xffffffff
#undef GPIO_USART2_CK
#define GPIO_USART2_CK 0xffffffff
#undef GPIO_USART3_TX
#define GPIO_USART3_TX 0xffffffff
#undef GPIO_USART3_CK
#define GPIO_USART3_CK 0xffffffff
#undef GPIO_USART3_CTS
nuttx-configs/px4io-v2/nsh/defconfig
+2 -2
View File
@@ -104,9 +104,9 @@ CONFIG_ARMV7M_CMNVECTOR=y
# CONFIG_STM32_JTAG_SW_ENABLE - Set JTAG-DP disabled and SW-DP enabled
#
CONFIG_STM32_DFU=n
CONFIG_STM32_JTAG_FULL_ENABLE=y
CONFIG_STM32_JTAG_FULL_ENABLE=n
CONFIG_STM32_JTAG_NOJNTRST_ENABLE=n
CONFIG_STM32_JTAG_SW_ENABLE=n
CONFIG_STM32_JTAG_SW_ENABLE=y
#
# Individual subsystems can be enabled:
src/drivers/ms5611/ms5611.cpp
+5
View File
@@ -526,6 +526,7 @@ void
MS5611::cycle()
{
int ret;
unsigned dummy;
/* collection phase? */
if (_collect_phase) {
@@ -542,6 +543,8 @@ MS5611::cycle()
} else {
//log("collection error %d", ret);
}
/* issue a reset command to the sensor */
_interface->ioctl(IOCTL_RESET, dummy);
/* reset the collection state machine and try again */
start_cycle();
return;
@@ -573,6 +576,8 @@ MS5611::cycle()
ret = measure();
if (ret != OK) {
//log("measure error %d", ret);
/* issue a reset command to the sensor */
_interface->ioctl(IOCTL_RESET, dummy);
/* reset the collection state machine and try again */
start_cycle();
return;
src/drivers/px4fmu/fmu.cpp
+167 -108
View File
@@ -120,19 +120,25 @@ private:
uint32_t _pwm_alt_rate_channels;
unsigned _current_update_rate;
int _task;
int _t_actuators;
int _t_actuator_armed;
orb_advert_t _t_outputs;
int _armed_sub;
orb_advert_t _outputs_pub;
actuator_armed_s _armed;
unsigned _num_outputs;
bool _primary_pwm_device;
volatile bool _task_should_exit;
bool _armed;
bool _servo_armed;
bool _pwm_on;
MixerGroup *_mixers;
actuator_controls_s _controls;
uint32_t _groups_required;
uint32_t _groups_subscribed;
int _control_subs[NUM_ACTUATOR_CONTROL_GROUPS];
actuator_controls_s _controls[NUM_ACTUATOR_CONTROL_GROUPS];
orb_id_t _control_topics[NUM_ACTUATOR_CONTROL_GROUPS];
pollfd _poll_fds[NUM_ACTUATOR_CONTROL_GROUPS];
unsigned _poll_fds_num;
pwm_limit_t _pwm_limit;
uint16_t _failsafe_pwm[_max_actuators];
@@ -149,7 +155,7 @@ private:
uint8_t control_group,
uint8_t control_index,
float &input);
void subscribe();
int set_pwm_rate(unsigned rate_map, unsigned default_rate, unsigned alt_rate);
int pwm_ioctl(file *filp, int cmd, unsigned long arg);
@@ -216,15 +222,18 @@ PX4FMU::PX4FMU() :
_pwm_alt_rate_channels(0),
_current_update_rate(0),
_task(-1),
_t_actuators(-1),
_t_actuator_armed(-1),
_t_outputs(0),
_control_subs({-1}),
_poll_fds_num(0),
_armed_sub(-1),
_outputs_pub(-1),
_num_outputs(0),
_primary_pwm_device(false),
_task_should_exit(false),
_armed(false),
_servo_armed(false),
_pwm_on(false),
_mixers(nullptr),
_groups_required(0),
_groups_subscribed(0),
_failsafe_pwm({0}),
_disarmed_pwm({0}),
_num_failsafe_set(0),
@@ -235,6 +244,14 @@ PX4FMU::PX4FMU() :
_max_pwm[i] = PWM_DEFAULT_MAX;
}
_control_topics[0] = ORB_ID(actuator_controls_0);
_control_topics[1] = ORB_ID(actuator_controls_1);
_control_topics[2] = ORB_ID(actuator_controls_2);
_control_topics[3] = ORB_ID(actuator_controls_3);
memset(_controls, 0, sizeof(_controls));
memset(_poll_fds, 0, sizeof(_poll_fds));
_debug_enabled = true;
}
@@ -447,33 +464,43 @@ PX4FMU::set_pwm_alt_channels(uint32_t channels)
return set_pwm_rate(channels, _pwm_default_rate, _pwm_alt_rate);
}
void
PX4FMU::subscribe()
{
/* subscribe/unsubscribe to required actuator control groups */
uint32_t sub_groups = _groups_required & ~_groups_subscribed;
uint32_t unsub_groups = _groups_subscribed & ~_groups_required;
_poll_fds_num = 0;
for (unsigned i = 0; i < NUM_ACTUATOR_CONTROL_GROUPS; i++) {
if (sub_groups & (1 << i)) {
warnx("subscribe to actuator_controls_%d", i);
_control_subs[i] = orb_subscribe(_control_topics[i]);
}
if (unsub_groups & (1 << i)) {
warnx("unsubscribe from actuator_controls_%d", i);
::close(_control_subs[i]);
_control_subs[i] = -1;
}
if (_control_subs[i] > 0) {
_poll_fds[_poll_fds_num].fd = _control_subs[i];
_poll_fds[_poll_fds_num].events = POLLIN;
_poll_fds_num++;
}
}
}
void
PX4FMU::task_main()
{
/*
* Subscribe to the appropriate PWM output topic based on whether we are the
* primary PWM output or not.
*/
_t_actuators = orb_subscribe(_primary_pwm_device ? ORB_ID_VEHICLE_ATTITUDE_CONTROLS :
ORB_ID(actuator_controls_1));
/* force a reset of the update rate */
_current_update_rate = 0;
_t_actuator_armed = orb_subscribe(ORB_ID(actuator_armed));
orb_set_interval(_t_actuator_armed, 200); /* 5Hz update rate */
_armed_sub = orb_subscribe(ORB_ID(actuator_armed));
/* advertise the mixed control outputs */
actuator_outputs_s outputs;
memset(&outputs, 0, sizeof(outputs));
/* advertise the mixed control outputs */
_t_outputs = orb_advertise(_primary_pwm_device ? ORB_ID_VEHICLE_CONTROLS : ORB_ID(actuator_outputs_1),
&outputs);
pollfd fds[2];
fds[0].fd = _t_actuators;
fds[0].events = POLLIN;
fds[1].fd = _t_actuator_armed;
fds[1].events = POLLIN;
#ifdef HRT_PPM_CHANNEL
// rc input, published to ORB
@@ -491,6 +518,12 @@ PX4FMU::task_main()
/* loop until killed */
while (!_task_should_exit) {
if (_groups_subscribed != _groups_required) {
subscribe();
_groups_subscribed = _groups_required;
/* force setting update rate */
_current_update_rate = 0;
}
/*
* Adjust actuator topic update rate to keep up with
@@ -515,7 +548,11 @@ PX4FMU::task_main()
}
debug("adjusted actuator update interval to %ums", update_rate_in_ms);
orb_set_interval(_t_actuators, update_rate_in_ms);
for (unsigned i = 0; i < NUM_ACTUATOR_CONTROL_GROUPS; i++) {
if (_control_subs[i] > 0) {
orb_set_interval(_control_subs[i], update_rate_in_ms);
}
}
// set to current max rate, even if we are actually checking slower/faster
_current_update_rate = max_rate;
@@ -523,7 +560,7 @@ PX4FMU::task_main()
/* sleep waiting for data, stopping to check for PPM
* input at 100Hz */
int ret = ::poll(&fds[0], 2, CONTROL_INPUT_DROP_LIMIT_MS);
int ret = ::poll(_poll_fds, _poll_fds_num, CONTROL_INPUT_DROP_LIMIT_MS);
/* this would be bad... */
if (ret < 0) {
@@ -537,89 +574,98 @@ PX4FMU::task_main()
} else {
/* do we have a control update? */
if (fds[0].revents & POLLIN) {
/* get controls - must always do this to avoid spinning */
orb_copy(_primary_pwm_device ? ORB_ID_VEHICLE_ATTITUDE_CONTROLS : ORB_ID(actuator_controls_1), _t_actuators, &_controls);
/* can we mix? */
if (_mixers != nullptr) {
unsigned num_outputs;
switch (_mode) {
case MODE_2PWM:
num_outputs = 2;
break;
case MODE_4PWM:
num_outputs = 4;
break;
case MODE_6PWM:
num_outputs = 6;
break;
default:
num_outputs = 0;
break;
/* get controls for required topics */
unsigned poll_id = 0;
for (unsigned i = 0; i < NUM_ACTUATOR_CONTROL_GROUPS; i++) {
if (_control_subs[i] > 0) {
if (_poll_fds[poll_id].revents & POLLIN) {
orb_copy(_control_topics[i], _control_subs[i], &_controls[i]);
}
/* do mixing */
outputs.noutputs = _mixers->mix(&outputs.output[0], num_outputs);
outputs.timestamp = hrt_absolute_time();
/* iterate actuators */
for (unsigned i = 0; i < num_outputs; i++) {
/* last resort: catch NaN, INF and out-of-band errors */
if (i >= outputs.noutputs ||
!isfinite(outputs.output[i]) ||
outputs.output[i] < -1.0f ||
outputs.output[i] > 1.0f) {
/*
* Value is NaN, INF or out of band - set to the minimum value.
* This will be clearly visible on the servo status and will limit the risk of accidentally
* spinning motors. It would be deadly in flight.
*/
outputs.output[i] = -1.0f;
}
}
uint16_t pwm_limited[num_outputs];
pwm_limit_calc(_armed, num_outputs, _disarmed_pwm, _min_pwm, _max_pwm, outputs.output, pwm_limited, &_pwm_limit);
/* output to the servos */
for (unsigned i = 0; i < num_outputs; i++) {
up_pwm_servo_set(i, pwm_limited[i]);
}
/* and publish for anyone that cares to see */
orb_publish(_primary_pwm_device ? ORB_ID_VEHICLE_CONTROLS : ORB_ID(actuator_outputs_1), _t_outputs, &outputs);
poll_id++;
}
}
/* how about an arming update? */
if (fds[1].revents & POLLIN) {
actuator_armed_s aa;
/* can we mix? */
if (_mixers != nullptr) {
/* get new value */
orb_copy(ORB_ID(actuator_armed), _t_actuator_armed, &aa);
unsigned num_outputs;
/* update the armed status and check that we're not locked down */
bool set_armed = aa.armed && !aa.lockdown;
switch (_mode) {
case MODE_2PWM:
num_outputs = 2;
break;
if (_armed != set_armed)
_armed = set_armed;
case MODE_4PWM:
num_outputs = 4;
break;
/* update PWM status if armed or if disarmed PWM values are set */
bool pwm_on = (aa.armed || _num_disarmed_set > 0);
case MODE_6PWM:
num_outputs = 6;
break;
if (_pwm_on != pwm_on) {
_pwm_on = pwm_on;
up_pwm_servo_arm(pwm_on);
default:
num_outputs = 0;
break;
}
/* do mixing */
outputs.noutputs = _mixers->mix(&outputs.output[0], num_outputs);
outputs.timestamp = hrt_absolute_time();
/* iterate actuators */
for (unsigned i = 0; i < num_outputs; i++) {
/* last resort: catch NaN, INF and out-of-band errors */
if (i >= outputs.noutputs ||
!isfinite(outputs.output[i]) ||
outputs.output[i] < -1.0f ||
outputs.output[i] > 1.0f) {
/*
* Value is NaN, INF or out of band - set to the minimum value.
* This will be clearly visible on the servo status and will limit the risk of accidentally
* spinning motors. It would be deadly in flight.
*/
outputs.output[i] = -1.0f;
}
}
uint16_t pwm_limited[num_outputs];
pwm_limit_calc(_servo_armed, num_outputs, _disarmed_pwm, _min_pwm, _max_pwm, outputs.output, pwm_limited, &_pwm_limit);
/* output to the servos */
for (unsigned i = 0; i < num_outputs; i++) {
up_pwm_servo_set(i, pwm_limited[i]);
}
/* publish mixed control outputs */
if (_outputs_pub < 0) {
_outputs_pub = orb_advertise(_primary_pwm_device ? ORB_ID_VEHICLE_CONTROLS : ORB_ID(actuator_outputs_1), &outputs);
} else {
orb_publish(_primary_pwm_device ? ORB_ID_VEHICLE_CONTROLS : ORB_ID(actuator_outputs_1), _outputs_pub, &outputs);
}
}
}
/* check arming state */
bool updated = false;
orb_check(_armed_sub, &updated);
if (updated) {
orb_copy(ORB_ID(actuator_armed), _armed_sub, &_armed);
/* update the armed status and check that we're not locked down */
bool set_armed = _armed.armed && !_armed.lockdown;
if (_servo_armed != set_armed)
_servo_armed = set_armed;
/* update PWM status if armed or if disarmed PWM values are set */
bool pwm_on = (_armed.armed || _num_disarmed_set > 0);
if (_pwm_on != pwm_on) {
_pwm_on = pwm_on;
up_pwm_servo_arm(pwm_on);
}
}
@@ -661,8 +707,13 @@ PX4FMU::task_main()
}
::close(_t_actuators);
::close(_t_actuator_armed);
for (unsigned i = 0; i < NUM_ACTUATOR_CONTROL_GROUPS; i++) {
if (_control_subs > 0) {
::close(_control_subs[i]);
_control_subs[i] = -1;
}
}
::close(_armed_sub);
/* make sure servos are off */
up_pwm_servo_deinit();
@@ -684,7 +735,7 @@ PX4FMU::control_callback(uintptr_t handle,
{
const actuator_controls_s *controls = (actuator_controls_s *)handle;
input = controls->control[control_index];
input = controls[control_group].control[control_index];
return 0;
}
@@ -1053,6 +1104,7 @@ PX4FMU::pwm_ioctl(file *filp, int cmd, unsigned long arg)
if (_mixers != nullptr) {
delete _mixers;
_mixers = nullptr;
_groups_required = 0;
}
break;
@@ -1061,18 +1113,20 @@ PX4FMU::pwm_ioctl(file *filp, int cmd, unsigned long arg)
mixer_simple_s *mixinfo = (mixer_simple_s *)arg;
SimpleMixer *mixer = new SimpleMixer(control_callback,
(uintptr_t)&_controls, mixinfo);
(uintptr_t)_controls, mixinfo);
if (mixer->check()) {
delete mixer;
_groups_required = 0;
ret = -EINVAL;
} else {
if (_mixers == nullptr)
_mixers = new MixerGroup(control_callback,
(uintptr_t)&_controls);
(uintptr_t)_controls);
_mixers->add_mixer(mixer);
_mixers->groups_required(_groups_required);
}
break;
@@ -1083,9 +1137,10 @@ PX4FMU::pwm_ioctl(file *filp, int cmd, unsigned long arg)
unsigned buflen = strnlen(buf, 1024);
if (_mixers == nullptr)
_mixers = new MixerGroup(control_callback, (uintptr_t)&_controls);
_mixers = new MixerGroup(control_callback, (uintptr_t)_controls);
if (_mixers == nullptr) {
_groups_required = 0;
ret = -ENOMEM;
} else {
@@ -1096,7 +1151,11 @@ PX4FMU::pwm_ioctl(file *filp, int cmd, unsigned long arg)
debug("mixer load failed with %d", ret);
delete _mixers;
_mixers = nullptr;
_groups_required = 0;
ret = -EINVAL;
} else {
_mixers->groups_required(_groups_required);
}
}
src/drivers/px4io/px4io.cpp
+20 -4
View File
@@ -683,6 +683,25 @@ PX4IO::init()
/* send command to arm system via command API */
vehicle_command_s cmd;
/* send this to itself */
param_t sys_id_param = param_find("MAV_SYS_ID");
param_t comp_id_param = param_find("MAV_COMP_ID");
int32_t sys_id;
int32_t comp_id;
if (param_get(sys_id_param, &sys_id)) {
errx(1, "PRM SYSID");
}
if (param_get(comp_id_param, &comp_id)) {
errx(1, "PRM CMPID");
}
cmd.target_system = sys_id;
cmd.target_component = comp_id;
cmd.source_system = sys_id;
cmd.source_component = comp_id;
/* request arming */
cmd.param1 = 1.0f;
cmd.param2 = 0;
@@ -692,10 +711,7 @@ PX4IO::init()
cmd.param6 = 0;
cmd.param7 = 0;
cmd.command = VEHICLE_CMD_COMPONENT_ARM_DISARM;
// cmd.target_system = status.system_id;
// cmd.target_component = status.component_id;
// cmd.source_system = status.system_id;
// cmd.source_component = status.component_id;
/* ask to confirm command */
cmd.confirmation = 1;
src/lib/mathlib/CMSIS/Include/arm_math.h
+1 -1
View File
@@ -5193,7 +5193,7 @@ void arm_rfft_fast_f32(
*pIa = Ialpha;
/* Calculating pIb from Ialpha and Ibeta by equation pIb = -(1/2) * Ialpha + (sqrt(3)/2) * Ibeta */
*pIb = -0.5 * Ialpha + (float32_t) 0.8660254039 *Ibeta;
*pIb = (float32_t)-0.5 * Ialpha + (float32_t) 0.8660254039 *Ibeta;
}
src/modules/commander/commander.cpp
+42 -6
View File
@@ -117,9 +117,10 @@ extern struct system_load_s system_load;
#define STICK_ON_OFF_HYSTERESIS_TIME_MS 1000
#define STICK_ON_OFF_COUNTER_LIMIT (STICK_ON_OFF_HYSTERESIS_TIME_MS*COMMANDER_MONITORING_LOOPSPERMSEC)
#define POSITION_TIMEOUT 100000 /**< consider the local or global position estimate invalid after 100ms */
#define RC_TIMEOUT 500000
#define DIFFPRESS_TIMEOUT 2000000
#define POSITION_TIMEOUT (600 * 1000) /**< consider the local or global position estimate invalid after 600ms */
#define FAILSAFE_DEFAULT_TIMEOUT (3 * 1000 * 1000) /**< hysteresis time - the failsafe will trigger after 3 seconds in this state */
#define RC_TIMEOUT 500000
#define DIFFPRESS_TIMEOUT 2000000
#define PRINT_INTERVAL 5000000
#define PRINT_MODE_REJECT_INTERVAL 2000000
@@ -484,6 +485,11 @@ bool handle_command(struct vehicle_status_s *status, const struct safety_s *safe
if (cmd->param1 != 0.0f && (fabsf(cmd->param1 - 1.0f) > 2.0f * FLT_EPSILON)) {
mavlink_log_info(mavlink_fd, "Unsupported ARM_DISARM parameter: %.6f", cmd->param1);
} else {
// Flick to inair restore first if this comes from an onboard system
if (cmd->source_system == status->system_id && cmd->source_component == status->component_id) {
status->arming_state = ARMING_STATE_IN_AIR_RESTORE;
}
transition_result_t arming_res = arm_disarm(cmd->param1 != 0.0f, mavlink_fd, "arm/disarm component command");
if (arming_res == TRANSITION_DENIED) {
mavlink_log_critical(mavlink_fd, "#audio: REJECTING component arm cmd");
@@ -741,8 +747,9 @@ int commander_thread_main(int argc, char *argv[])
bool low_battery_voltage_actions_done = false;
bool critical_battery_voltage_actions_done = false;
uint64_t last_idle_time = 0;
uint64_t start_time = 0;
hrt_abstime last_idle_time = 0;
hrt_abstime start_time = 0;
hrt_abstime last_auto_state_valid = 0;
bool status_changed = true;
bool param_init_forced = true;
@@ -771,6 +778,9 @@ int commander_thread_main(int argc, char *argv[])
int global_position_sub = orb_subscribe(ORB_ID(vehicle_global_position));
struct vehicle_global_position_s global_position;
memset(&global_position, 0, sizeof(global_position));
/* Init EPH and EPV */
global_position.eph = 1000.0f;
global_position.epv = 1000.0f;
/* Subscribe to local position data */
int local_position_sub = orb_subscribe(ORB_ID(vehicle_local_position));
@@ -933,11 +943,15 @@ int commander_thread_main(int argc, char *argv[])
if (status.condition_global_position_valid) {
if (global_position.eph > eph_epv_threshold * 2.0f || global_position.epv > eph_epv_threshold * 2.0f) {
eph_epv_good = false;
} else {
eph_epv_good = true;
}
} else {
if (global_position.eph < eph_epv_threshold && global_position.epv < eph_epv_threshold) {
eph_epv_good = true;
} else {
eph_epv_good = false;
}
}
check_valid(global_position.timestamp, POSITION_TIMEOUT, eph_epv_good, &(status.condition_global_position_valid), &status_changed);
@@ -1259,13 +1273,25 @@ int commander_thread_main(int argc, char *argv[])
/* check if AUTO mode still allowed */
transition_result_t res = main_state_transition(&status, MAIN_STATE_AUTO);
if (res == TRANSITION_DENIED) {
if (res == TRANSITION_NOT_CHANGED) {
last_auto_state_valid = hrt_absolute_time();
}
/* still invalid state after the timeout interval, execute failsafe */
if ((hrt_elapsed_time(&last_auto_state_valid) > FAILSAFE_DEFAULT_TIMEOUT) && (res == TRANSITION_DENIED)) {
/* AUTO mode denied, don't try RTL, switch to failsafe state LAND */
res = failsafe_state_transition(&status, FAILSAFE_STATE_LAND);
if (res == TRANSITION_DENIED) {
/* LAND not allowed, set TERMINATION state */
transition_result_t res = failsafe_state_transition(&status, FAILSAFE_STATE_TERMINATION);
if (res == TRANSITION_CHANGED) {
mavlink_log_critical(mavlink_fd, "#a FAILSAFE: TERMINATION");
}
} else if (res == TRANSITION_CHANGED) {
mavlink_log_critical(mavlink_fd, "#a FAILSAFE: LANDING");
}
}
@@ -1276,15 +1302,25 @@ int commander_thread_main(int argc, char *argv[])
if (!status.condition_landed) {
/* vehicle is not landed, try to perform RTL */
res = failsafe_state_transition(&status, FAILSAFE_STATE_RTL);
if (res == TRANSITION_CHANGED) {
mavlink_log_critical(mavlink_fd, "#a FAILSAFE: RETURN TO LAND");
}
}
if (res == TRANSITION_DENIED) {
/* RTL not allowed (no global position estimate) or not wanted, try LAND */
res = failsafe_state_transition(&status, FAILSAFE_STATE_LAND);
if (res == TRANSITION_CHANGED) {
mavlink_log_critical(mavlink_fd, "#a FAILSAFE: LANDING");
}
if (res == TRANSITION_DENIED) {
/* LAND not allowed, set TERMINATION state */
res = failsafe_state_transition(&status, FAILSAFE_STATE_TERMINATION);
} else if (res == TRANSITION_CHANGED) {
mavlink_log_critical(mavlink_fd, "#a FAILSAFE: TERMINATION");
}
}
}
src/modules/fixedwing_att_control/fixedwing_att_control_att.c
-169
View File
@@ -1,169 +0,0 @@
/****************************************************************************
*
* Copyright (C) 2012 PX4 Development Team. All rights reserved.
* Author: @author Thomas Gubler <thomasgubler@student.ethz.ch>
*
* Redistribution and use in source and binary forms, with or without
* modification, are permitted provided that the following conditions
* are met:
*
* 1. Redistributions of source code must retain the above copyright
* notice, this list of conditions and the following disclaimer.
* 2. Redistributions in binary form must reproduce the above copyright
* notice, this list of conditions and the following disclaimer in
* the documentation and/or other materials provided with the
* distribution.
* 3. Neither the name PX4 nor the names of its contributors may be
* used to endorse or promote products derived from this software
* without specific prior written permission.
*
* THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
* "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
* LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
* FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
* COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
* INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
* BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
* OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
* AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
* LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
* ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
* POSSIBILITY OF SUCH DAMAGE.
*
****************************************************************************/
/**
* @file fixedwing_att_control_rate.c
* Implementation of a fixed wing attitude controller.
*/
#include <nuttx/config.h>
#include <stdio.h>
#include <stdlib.h>
#include <string.h>
#include <unistd.h>
#include <fcntl.h>
#include <errno.h>
#include <math.h>
#include <poll.h>
#include <time.h>
#include <drivers/drv_hrt.h>
#include <arch/board/board.h>
#include <uORB/uORB.h>
#include <uORB/topics/vehicle_attitude.h>
#include <uORB/topics/vehicle_attitude_setpoint.h>
#include <uORB/topics/manual_control_setpoint.h>
#include <systemlib/param/param.h>
#include <systemlib/pid/pid.h>
#include <systemlib/geo/geo.h>
#include <systemlib/systemlib.h>
#include "fixedwing_att_control_att.h"
struct fw_att_control_params {
float roll_p;
float rollrate_lim;
float pitch_p;
float pitchrate_lim;
float yawrate_lim;
float pitch_roll_compensation_p;
};
struct fw_pos_control_param_handles {
param_t roll_p;
param_t rollrate_lim;
param_t pitch_p;
param_t pitchrate_lim;
param_t yawrate_lim;
param_t pitch_roll_compensation_p;
};
/* Internal Prototypes */
static int parameters_init(struct fw_pos_control_param_handles *h);
static int parameters_update(const struct fw_pos_control_param_handles *h, struct fw_att_control_params *p);
static int parameters_init(struct fw_pos_control_param_handles *h)
{
/* PID parameters */
h->roll_p = param_find("FW_ROLL_P");
h->rollrate_lim = param_find("FW_ROLLR_LIM");
h->pitch_p = param_find("FW_PITCH_P");
h->pitchrate_lim = param_find("FW_PITCHR_LIM");
h->yawrate_lim = param_find("FW_YAWR_LIM");
h->pitch_roll_compensation_p = param_find("FW_PITCH_RCOMP");
return OK;
}
static int parameters_update(const struct fw_pos_control_param_handles *h, struct fw_att_control_params *p)
{
param_get(h->roll_p, &(p->roll_p));
param_get(h->rollrate_lim, &(p->rollrate_lim));
param_get(h->pitch_p, &(p->pitch_p));
param_get(h->pitchrate_lim, &(p->pitchrate_lim));
param_get(h->yawrate_lim, &(p->yawrate_lim));
param_get(h->pitch_roll_compensation_p, &(p->pitch_roll_compensation_p));
return OK;
}
int fixedwing_att_control_attitude(const struct vehicle_attitude_setpoint_s *att_sp,
const struct vehicle_attitude_s *att,
const float speed_body[],
struct vehicle_rates_setpoint_s *rates_sp)
{
static int counter = 0;
static bool initialized = false;
static struct fw_att_control_params p;
static struct fw_pos_control_param_handles h;
static PID_t roll_controller;
static PID_t pitch_controller;
if (!initialized) {
parameters_init(&h);
parameters_update(&h, &p);
pid_init(&roll_controller, p.roll_p, 0, 0, 0, p.rollrate_lim, PID_MODE_DERIVATIV_NONE, 0.0f); //P Controller
pid_init(&pitch_controller, p.pitch_p, 0, 0, 0, p.pitchrate_lim, PID_MODE_DERIVATIV_NONE, 0.0f); //P Controller
initialized = true;
}
/* load new parameters with lower rate */
if (counter % 100 == 0) {
/* update parameters from storage */
parameters_update(&h, &p);
pid_set_parameters(&roll_controller, p.roll_p, 0, 0, 0, p.rollrate_lim);
pid_set_parameters(&pitch_controller, p.pitch_p, 0, 0, 0, p.pitchrate_lim);
}
/* Roll (P) */
rates_sp->roll = pid_calculate(&roll_controller, att_sp->roll_body, att->roll, 0, 0);
/* Pitch (P) */
/* compensate feedforward for loss of lift due to non-horizontal angle of wing */
float pitch_sp_rollcompensation = p.pitch_roll_compensation_p * fabsf(sinf(att_sp->roll_body));
/* set pitch plus feedforward roll compensation */
rates_sp->pitch = pid_calculate(&pitch_controller,
att_sp->pitch_body + pitch_sp_rollcompensation,
att->pitch, 0, 0);
/* Yaw (from coordinated turn constraint or lateral force) */
rates_sp->yaw = (att->rollspeed * rates_sp->roll + 9.81f * sinf(att->roll) * cosf(att->pitch) + speed_body[0] * rates_sp->pitch * sinf(att->roll))
/ (speed_body[0] * cosf(att->roll) * cosf(att->pitch) + speed_body[2] * sinf(att->pitch));
// printf("rates_sp->yaw %.4f \n", (double)rates_sp->yaw);
counter++;
return 0;
}
src/modules/fixedwing_att_control/fixedwing_att_control_att.h
-51
View File
@@ -1,51 +0,0 @@
/****************************************************************************
*
* Copyright (C) 2012 PX4 Development Team. All rights reserved.
* Author: @author Thomas Gubler <thomasgubler@student.ethz.ch>
*
*
* Redistribution and use in source and binary forms, with or without
* modification, are permitted provided that the following conditions
* are met:
*
* 1. Redistributions of source code must retain the above copyright
* notice, this list of conditions and the following disclaimer.
* 2. Redistributions in binary form must reproduce the above copyright
* notice, this list of conditions and the following disclaimer in
* the documentation and/or other materials provided with the
* distribution.
* 3. Neither the name PX4 nor the names of its contributors may be
* used to endorse or promote products derived from this software
* without specific prior written permission.
*
* THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
* "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
* LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
* FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
* COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
* INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
* BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
* OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
* AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
* LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
* ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
* POSSIBILITY OF SUCH DAMAGE.
*
****************************************************************************/
/* @file Fixed Wing Attitude Control */
#ifndef FIXEDWING_ATT_CONTROL_ATT_H_
#define FIXEDWING_ATT_CONTROL_ATT_H_
#include <uORB/topics/vehicle_rates_setpoint.h>
#include <uORB/topics/vehicle_attitude_setpoint.h>
#include <uORB/topics/vehicle_attitude.h>
#include <uORB/topics/vehicle_global_position.h>
int fixedwing_att_control_attitude(const struct vehicle_attitude_setpoint_s *att_sp,
const struct vehicle_attitude_s *att,
const float speed_body[],
struct vehicle_rates_setpoint_s *rates_sp);
#endif /* FIXEDWING_ATT_CONTROL_ATT_H_ */
src/modules/fixedwing_att_control/fixedwing_att_control_main.c
-367
View File
@@ -1,367 +0,0 @@
/****************************************************************************
*
* Copyright (C) 2012 PX4 Development Team. All rights reserved.
* Author: @author Thomas Gubler <thomasgubler@student.ethz.ch>
* @author Doug Weibel <douglas.weibel@colorado.edu>
*
* Redistribution and use in source and binary forms, with or without
* modification, are permitted provided that the following conditions
* are met:
*
* 1. Redistributions of source code must retain the above copyright
* notice, this list of conditions and the following disclaimer.
* 2. Redistributions in binary form must reproduce the above copyright
* notice, this list of conditions and the following disclaimer in
* the documentation and/or other materials provided with the
* distribution.
* 3. Neither the name PX4 nor the names of its contributors may be
* used to endorse or promote products derived from this software
* without specific prior written permission.
*
* THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
* "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
* LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
* FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
* COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
* INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
* BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
* OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
* AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
* LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
* ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
* POSSIBILITY OF SUCH DAMAGE.
*
****************************************************************************/
/**
* @file fixedwing_att_control.c
* Implementation of a fixed wing attitude controller.
*/
#include <nuttx/config.h>
#include <stdio.h>
#include <stdlib.h>
#include <string.h>
#include <unistd.h>
#include <fcntl.h>
#include <errno.h>
#include <math.h>
#include <poll.h>
#include <time.h>
#include <drivers/drv_hrt.h>
#include <arch/board/board.h>
#include <uORB/uORB.h>
#include <uORB/topics/vehicle_global_position.h>
#include <uORB/topics/vehicle_global_position_setpoint.h>
#include <uORB/topics/vehicle_attitude.h>
#include <uORB/topics/vehicle_control_mode.h>
#include <uORB/topics/vehicle_status.h>
#include <uORB/topics/vehicle_attitude_setpoint.h>
#include <uORB/topics/manual_control_setpoint.h>
#include <uORB/topics/actuator_controls.h>
#include <uORB/topics/vehicle_rates_setpoint.h>
#include <uORB/topics/vehicle_global_position.h>
#include <uORB/topics/debug_key_value.h>
#include <systemlib/param/param.h>
#include <systemlib/pid/pid.h>
#include <systemlib/geo/geo.h>
#include <systemlib/perf_counter.h>
#include <systemlib/systemlib.h>
#include "fixedwing_att_control_rate.h"
#include "fixedwing_att_control_att.h"
/* Prototypes */
/**
* Deamon management function.
*/
__EXPORT int fixedwing_att_control_main(int argc, char *argv[]);
/**
* Mainloop of deamon.
*/
int fixedwing_att_control_thread_main(int argc, char *argv[]);
/**
* Print the correct usage.
*/
static void usage(const char *reason);
/* Variables */
static bool thread_should_exit = false; /**< Deamon exit flag */
static bool thread_running = false; /**< Deamon status flag */
static int deamon_task; /**< Handle of deamon task / thread */
/* Main Thread */
int fixedwing_att_control_thread_main(int argc, char *argv[])
{
/* read arguments */
bool verbose = false;
for (int i = 1; i < argc; i++) {
if (strcmp(argv[i], "-v") == 0 || strcmp(argv[i], "--verbose") == 0) {
verbose = true;
}
}
/* welcome user */
printf("[fixedwing att control] started\n");
/* declare and safely initialize all structs */
struct vehicle_attitude_s att;
memset(&att, 0, sizeof(att));
struct vehicle_attitude_setpoint_s att_sp;
memset(&att_sp, 0, sizeof(att_sp));
struct vehicle_rates_setpoint_s rates_sp;
memset(&rates_sp, 0, sizeof(rates_sp));
struct vehicle_global_position_s global_pos;
memset(&global_pos, 0, sizeof(global_pos));
struct manual_control_setpoint_s manual_sp;
memset(&manual_sp, 0, sizeof(manual_sp));
struct vehicle_control_mode_s control_mode;
memset(&control_mode, 0, sizeof(control_mode));
struct vehicle_status_s vstatus;
memset(&vstatus, 0, sizeof(vstatus));
/* output structs */
struct actuator_controls_s actuators;
memset(&actuators, 0, sizeof(actuators));
/* publish actuator controls */
for (unsigned i = 0; i < NUM_ACTUATOR_CONTROLS; i++) {
actuators.control[i] = 0.0f;
}
orb_advert_t actuator_pub = orb_advertise(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, &actuators);
orb_advert_t rates_pub = orb_advertise(ORB_ID(vehicle_rates_setpoint), &rates_sp);
/* subscribe */
int att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
int att_sp_sub = orb_subscribe(ORB_ID(vehicle_attitude_setpoint));
int global_pos_sub = orb_subscribe(ORB_ID(vehicle_global_position));
int manual_sp_sub = orb_subscribe(ORB_ID(manual_control_setpoint));
int control_mode_sub = orb_subscribe(ORB_ID(vehicle_control_mode));
int vehicle_status_sub = orb_subscribe(ORB_ID(vehicle_status));
/* Setup of loop */
float gyro[3] = {0.0f, 0.0f, 0.0f};
float speed_body[3] = {0.0f, 0.0f, 0.0f};
struct pollfd fds = { .fd = att_sub, .events = POLLIN };
while (!thread_should_exit) {
/* wait for a sensor update, check for exit condition every 500 ms */
poll(&fds, 1, 500);
/* Check if there is a new position measurement or attitude setpoint */
bool pos_updated;
orb_check(global_pos_sub, &pos_updated);
bool att_sp_updated;
orb_check(att_sp_sub, &att_sp_updated);
/* get a local copy of attitude */
orb_copy(ORB_ID(vehicle_attitude), att_sub, &att);
if (att_sp_updated)
orb_copy(ORB_ID(vehicle_attitude_setpoint), att_sp_sub, &att_sp);
if (pos_updated) {
orb_copy(ORB_ID(vehicle_global_position), global_pos_sub, &global_pos);
if (att.R_valid) {
speed_body[0] = att.R[0][0] * global_pos.vx + att.R[0][1] * global_pos.vy + att.R[0][2] * global_pos.vz;
speed_body[1] = att.R[1][0] * global_pos.vx + att.R[1][1] * global_pos.vy + att.R[1][2] * global_pos.vz;
speed_body[2] = att.R[2][0] * global_pos.vx + att.R[2][1] * global_pos.vy + att.R[2][2] * global_pos.vz;
} else {
speed_body[0] = 0;
speed_body[1] = 0;
speed_body[2] = 0;
printf("FW ATT CONTROL: Did not get a valid R\n");
}
}
orb_copy(ORB_ID(manual_control_setpoint), manual_sp_sub, &manual_sp);
orb_copy(ORB_ID(vehicle_control_mode), control_mode_sub, &control_mode);
orb_copy(ORB_ID(vehicle_status), vehicle_status_sub, &vstatus);
gyro[0] = att.rollspeed;
gyro[1] = att.pitchspeed;
gyro[2] = att.yawspeed;
/* set manual setpoints if required */
if (control_mode.flag_control_manual_enabled) {
if (control_mode.flag_control_attitude_enabled) {
/* if the RC signal is lost, try to stay level and go slowly back down to ground */
if (vstatus.rc_signal_lost) {
/* put plane into loiter */
att_sp.roll_body = 0.3f;
att_sp.pitch_body = 0.0f;
/* limit throttle to 60 % of last value if sane */
if (isfinite(manual_sp.throttle) &&
(manual_sp.throttle >= 0.0f) &&
(manual_sp.throttle <= 1.0f)) {
att_sp.thrust = 0.6f * manual_sp.throttle;
} else {
att_sp.thrust = 0.0f;
}
att_sp.yaw_body = 0;
// XXX disable yaw control, loiter
} else {
att_sp.roll_body = manual_sp.roll;
att_sp.pitch_body = manual_sp.pitch;
att_sp.yaw_body = 0;
att_sp.thrust = manual_sp.throttle;
}
att_sp.timestamp = hrt_absolute_time();
/* pass through flaps */
if (isfinite(manual_sp.flaps)) {
actuators.control[4] = manual_sp.flaps;
} else {
actuators.control[4] = 0.0f;
}
} else {
/* directly pass through values */
actuators.control[0] = manual_sp.roll;
/* positive pitch means negative actuator -> pull up */
actuators.control[1] = manual_sp.pitch;
actuators.control[2] = manual_sp.yaw;
actuators.control[3] = manual_sp.throttle;
if (isfinite(manual_sp.flaps)) {
actuators.control[4] = manual_sp.flaps;
} else {
actuators.control[4] = 0.0f;
}
}
}
/* execute attitude control if requested */
if (control_mode.flag_control_attitude_enabled) {
/* attitude control */
fixedwing_att_control_attitude(&att_sp, &att, speed_body, &rates_sp);
/* angular rate control */
fixedwing_att_control_rates(&rates_sp, gyro, &actuators);
/* pass through throttle */
actuators.control[3] = att_sp.thrust;
/* set flaps to zero */
actuators.control[4] = 0.0f;
}
/* publish rates */
orb_publish(ORB_ID(vehicle_rates_setpoint), rates_pub, &rates_sp);
/* sanity check and publish actuator outputs */
if (isfinite(actuators.control[0]) &&
isfinite(actuators.control[1]) &&
isfinite(actuators.control[2]) &&
isfinite(actuators.control[3])) {
orb_publish(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, actuator_pub, &actuators);
}
}
printf("[fixedwing_att_control] exiting, stopping all motors.\n");
thread_running = false;
/* kill all outputs */
for (unsigned i = 0; i < NUM_ACTUATOR_CONTROLS; i++)
actuators.control[i] = 0.0f;
orb_publish(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, actuator_pub, &actuators);
close(att_sub);
close(actuator_pub);
close(rates_pub);
fflush(stdout);
exit(0);
return 0;
}
/* Startup Functions */
static void
usage(const char *reason)
{
if (reason)
fprintf(stderr, "%s\n", reason);
fprintf(stderr, "usage: fixedwing_att_control {start|stop|status}\n\n");
exit(1);
}
/**
* The deamon app only briefly exists to start
* the background job. The stack size assigned in the
* Makefile does only apply to this management task.
*
* The actual stack size should be set in the call
* to task_create().
*/
int fixedwing_att_control_main(int argc, char *argv[])
{
if (argc < 1)
usage("missing command");
if (!strcmp(argv[1], "start")) {
if (thread_running) {
printf("fixedwing_att_control already running\n");
/* this is not an error */
exit(0);
}
thread_should_exit = false;
deamon_task = task_spawn_cmd("fixedwing_att_control",
SCHED_DEFAULT,
SCHED_PRIORITY_MAX - 20,
2048,
fixedwing_att_control_thread_main,
(argv) ? (const char **)&argv[2] : (const char **)NULL);
thread_running = true;
exit(0);
}
if (!strcmp(argv[1], "stop")) {
thread_should_exit = true;
exit(0);
}
if (!strcmp(argv[1], "status")) {
if (thread_running) {
printf("\tfixedwing_att_control is running\n");
} else {
printf("\tfixedwing_att_control not started\n");
}
exit(0);
}
usage("unrecognized command");
exit(1);
}
src/modules/fixedwing_att_control/fixedwing_att_control_rate.c
-211
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@@ -1,211 +0,0 @@
/****************************************************************************
*
* Copyright (C) 2012 PX4 Development Team. All rights reserved.
* Author: Thomas Gubler <thomasgubler@student.ethz.ch>
*
* Redistribution and use in source and binary forms, with or without
* modification, are permitted provided that the following conditions
* are met:
*
* 1. Redistributions of source code must retain the above copyright
* notice, this list of conditions and the following disclaimer.
* 2. Redistributions in binary form must reproduce the above copyright
* notice, this list of conditions and the following disclaimer in
* the documentation and/or other materials provided with the
* distribution.
* 3. Neither the name PX4 nor the names of its contributors may be
* used to endorse or promote products derived from this software
* without specific prior written permission.
*
* THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
* "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
* LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
* FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
* COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
* INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
* BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
* OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
* AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
* LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
* ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
* POSSIBILITY OF SUCH DAMAGE.
*
****************************************************************************/
/**
* @file fixedwing_att_control_rate.c
* @author Thomas Gubler <thomasgubler@student.ethz.ch>
*
* Implementation of a fixed wing attitude controller.
*
*/
#include <nuttx/config.h>
#include <stdio.h>
#include <stdlib.h>
#include <string.h>
#include <unistd.h>
#include <fcntl.h>
#include <errno.h>
#include <math.h>
#include <poll.h>
#include <time.h>
#include <drivers/drv_hrt.h>
#include <arch/board/board.h>
#include <uORB/uORB.h>
#include <uORB/topics/vehicle_attitude.h>
#include <uORB/topics/vehicle_attitude_setpoint.h>
#include <uORB/topics/manual_control_setpoint.h>
#include <systemlib/param/param.h>
#include <systemlib/pid/pid.h>
#include <systemlib/geo/geo.h>
#include <systemlib/systemlib.h>
#include "fixedwing_att_control_rate.h"
/*
* Controller parameters, accessible via MAVLink
*
*/
// Roll control parameters
PARAM_DEFINE_FLOAT(FW_ROLLR_P, 0.9f);
PARAM_DEFINE_FLOAT(FW_ROLLR_I, 0.2f);
PARAM_DEFINE_FLOAT(FW_ROLLR_AWU, 0.9f);
PARAM_DEFINE_FLOAT(FW_ROLLR_LIM, 0.7f); // Roll rate limit in radians/sec, applies to the roll controller
PARAM_DEFINE_FLOAT(FW_ROLL_P, 4.0f);
PARAM_DEFINE_FLOAT(FW_PITCH_RCOMP, 0.1f);
//Pitch control parameters
PARAM_DEFINE_FLOAT(FW_PITCHR_P, 0.8f);
PARAM_DEFINE_FLOAT(FW_PITCHR_I, 0.2f);
PARAM_DEFINE_FLOAT(FW_PITCHR_AWU, 0.8f);
PARAM_DEFINE_FLOAT(FW_PITCHR_LIM, 0.35f); // Pitch rate limit in radians/sec, applies to the pitch controller
PARAM_DEFINE_FLOAT(FW_PITCH_P, 8.0f);
//Yaw control parameters //XXX TODO this is copy paste, asign correct values
PARAM_DEFINE_FLOAT(FW_YAWR_P, 0.3f);
PARAM_DEFINE_FLOAT(FW_YAWR_I, 0.0f);
PARAM_DEFINE_FLOAT(FW_YAWR_AWU, 0.0f);
PARAM_DEFINE_FLOAT(FW_YAWR_LIM, 0.35f); // Yaw rate limit in radians/sec
/* feedforward compensation */
PARAM_DEFINE_FLOAT(FW_PITCH_THR_P, 0.1f); /**< throttle to pitch coupling feedforward */
struct fw_rate_control_params {
float rollrate_p;
float rollrate_i;
float rollrate_awu;
float pitchrate_p;
float pitchrate_i;
float pitchrate_awu;
float yawrate_p;
float yawrate_i;
float yawrate_awu;
float pitch_thr_ff;
};
struct fw_rate_control_param_handles {
param_t rollrate_p;
param_t rollrate_i;
param_t rollrate_awu;
param_t pitchrate_p;
param_t pitchrate_i;
param_t pitchrate_awu;
param_t yawrate_p;
param_t yawrate_i;
param_t yawrate_awu;
param_t pitch_thr_ff;
};
/* Internal Prototypes */
static int parameters_init(struct fw_rate_control_param_handles *h);
static int parameters_update(const struct fw_rate_control_param_handles *h, struct fw_rate_control_params *p);
static int parameters_init(struct fw_rate_control_param_handles *h)
{
/* PID parameters */
h->rollrate_p = param_find("FW_ROLLR_P"); //TODO define rate params for fixed wing
h->rollrate_i = param_find("FW_ROLLR_I");
h->rollrate_awu = param_find("FW_ROLLR_AWU");
h->pitchrate_p = param_find("FW_PITCHR_P");
h->pitchrate_i = param_find("FW_PITCHR_I");
h->pitchrate_awu = param_find("FW_PITCHR_AWU");
h->yawrate_p = param_find("FW_YAWR_P");
h->yawrate_i = param_find("FW_YAWR_I");
h->yawrate_awu = param_find("FW_YAWR_AWU");
h->pitch_thr_ff = param_find("FW_PITCH_THR_P");
return OK;
}
static int parameters_update(const struct fw_rate_control_param_handles *h, struct fw_rate_control_params *p)
{
param_get(h->rollrate_p, &(p->rollrate_p));
param_get(h->rollrate_i, &(p->rollrate_i));
param_get(h->rollrate_awu, &(p->rollrate_awu));
param_get(h->pitchrate_p, &(p->pitchrate_p));
param_get(h->pitchrate_i, &(p->pitchrate_i));
param_get(h->pitchrate_awu, &(p->pitchrate_awu));
param_get(h->yawrate_p, &(p->yawrate_p));
param_get(h->yawrate_i, &(p->yawrate_i));
param_get(h->yawrate_awu, &(p->yawrate_awu));
param_get(h->pitch_thr_ff, &(p->pitch_thr_ff));
return OK;
}
int fixedwing_att_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
const float rates[],
struct actuator_controls_s *actuators)
{
static int counter = 0;
static bool initialized = false;
static struct fw_rate_control_params p;
static struct fw_rate_control_param_handles h;
static PID_t roll_rate_controller;
static PID_t pitch_rate_controller;
static PID_t yaw_rate_controller;
static uint64_t last_run = 0;
const float deltaT = (hrt_absolute_time() - last_run) / 1000000.0f;
last_run = hrt_absolute_time();
if (!initialized) {
parameters_init(&h);
parameters_update(&h, &p);
pid_init(&roll_rate_controller, p.rollrate_p, p.rollrate_i, 0, p.rollrate_awu, 1, PID_MODE_DERIVATIV_NONE, 0.0f); // set D part to 0 because the controller layout is with a PI rate controller
pid_init(&pitch_rate_controller, p.pitchrate_p, p.pitchrate_i, 0, p.pitchrate_awu, 1, PID_MODE_DERIVATIV_NONE, 0.0f); // set D part to 0 because the contpitcher layout is with a PI rate contpitcher
pid_init(&yaw_rate_controller, p.yawrate_p, p.yawrate_i, 0, p.yawrate_awu, 1, PID_MODE_DERIVATIV_NONE, 0.0f); // set D part to 0 because the contpitcher layout is with a PI rate contpitcher
initialized = true;
}
/* load new parameters with lower rate */
if (counter % 100 == 0) {
/* update parameters from storage */
parameters_update(&h, &p);
pid_set_parameters(&roll_rate_controller, p.rollrate_p, p.rollrate_i, 0, p.rollrate_awu, 1);
pid_set_parameters(&pitch_rate_controller, p.pitchrate_p, p.pitchrate_i, 0, p.pitchrate_awu, 1);
pid_set_parameters(&yaw_rate_controller, p.yawrate_p, p.yawrate_i, 0, p.yawrate_awu, 1);
}
/* roll rate (PI) */
actuators->control[0] = pid_calculate(&roll_rate_controller, rate_sp->roll, rates[0], 0.0f, deltaT);
/* pitch rate (PI) */
actuators->control[1] = -pid_calculate(&pitch_rate_controller, rate_sp->pitch, rates[1], 0.0f, deltaT);
/* yaw rate (PI) */
actuators->control[2] = pid_calculate(&yaw_rate_controller, rate_sp->yaw, rates[2], 0.0f, deltaT);
counter++;
return 0;
}
src/modules/fixedwing_att_control/fixedwing_att_control_rate.h
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@@ -1,48 +0,0 @@
/****************************************************************************
*
* Copyright (C) 2012 PX4 Development Team. All rights reserved.
* Author: @author Thomas Gubler <thomasgubler@student.ethz.ch>
*
*
* Redistribution and use in source and binary forms, with or without
* modification, are permitted provided that the following conditions
* are met:
*
* 1. Redistributions of source code must retain the above copyright
* notice, this list of conditions and the following disclaimer.
* 2. Redistributions in binary form must reproduce the above copyright
* notice, this list of conditions and the following disclaimer in
* the documentation and/or other materials provided with the
* distribution.
* 3. Neither the name PX4 nor the names of its contributors may be
* used to endorse or promote products derived from this software
* without specific prior written permission.
*
* THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
* "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
* LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
* FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
* COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
* INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
* BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
* OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
* AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
* LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
* ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
* POSSIBILITY OF SUCH DAMAGE.
*
****************************************************************************/
/* @file Fixed Wing Attitude Rate Control */
#ifndef FIXEDWING_ATT_CONTROL_RATE_H_
#define FIXEDWING_ATT_CONTROL_RATE_H_
#include <uORB/topics/vehicle_rates_setpoint.h>
#include <uORB/topics/actuator_controls.h>
int fixedwing_att_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
const float rates[],
struct actuator_controls_s *actuators);
#endif /* FIXEDWING_ATT_CONTROL_RATE_H_ */
src/modules/fixedwing_att_control/module.mk
-42
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@@ -1,42 +0,0 @@
############################################################################
#
# Copyright (c) 2012, 2013 PX4 Development Team. All rights reserved.
#
# Redistribution and use in source and binary forms, with or without
# modification, are permitted provided that the following conditions
# are met:
#
# 1. Redistributions of source code must retain the above copyright
# notice, this list of conditions and the following disclaimer.
# 2. Redistributions in binary form must reproduce the above copyright
# notice, this list of conditions and the following disclaimer in
# the documentation and/or other materials provided with the
# distribution.
# 3. Neither the name PX4 nor the names of its contributors may be
# used to endorse or promote products derived from this software
# without specific prior written permission.
#
# THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
# "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
# LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
# FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
# COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
# INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
# BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
# OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
# AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
# LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
# ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
# POSSIBILITY OF SUCH DAMAGE.
#
############################################################################
#
# Fixedwing Attitude Control application
#
MODULE_COMMAND = fixedwing_att_control
SRCS = fixedwing_att_control_main.c \
fixedwing_att_control_att.c \
fixedwing_att_control_rate.c
src/modules/fixedwing_pos_control/fixedwing_pos_control_main.c
-479
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@@ -1,479 +0,0 @@
/****************************************************************************
*
* Copyright (C) 2012 PX4 Development Team. All rights reserved.
* Author: @author Thomas Gubler <thomasgubler@student.ethz.ch>
* @author Doug Weibel <douglas.weibel@colorado.edu>
*
* Redistribution and use in source and binary forms, with or without
* modification, are permitted provided that the following conditions
* are met:
*
* 1. Redistributions of source code must retain the above copyright
* notice, this list of conditions and the following disclaimer.
* 2. Redistributions in binary form must reproduce the above copyright
* notice, this list of conditions and the following disclaimer in
* the documentation and/or other materials provided with the
* distribution.
* 3. Neither the name PX4 nor the names of its contributors may be
* used to endorse or promote products derived from this software
* without specific prior written permission.
*
* THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
* "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
* LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
* FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
* COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
* INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
* BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
* OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
* AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
* LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
* ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
* POSSIBILITY OF SUCH DAMAGE.
*
****************************************************************************/
/**
* @file fixedwing_pos_control.c
* Implementation of a fixed wing attitude controller.
*/
#include <nuttx/config.h>
#include <stdio.h>
#include <stdlib.h>
#include <string.h>
#include <unistd.h>
#include <fcntl.h>
#include <errno.h>
#include <math.h>
#include <poll.h>
#include <time.h>
#include <drivers/drv_hrt.h>
#include <arch/board/board.h>
#include <uORB/uORB.h>
#include <uORB/topics/vehicle_global_position.h>
#include <uORB/topics/vehicle_global_position_setpoint.h>
#include <uORB/topics/vehicle_attitude_setpoint.h>
#include <uORB/topics/manual_control_setpoint.h>
#include <uORB/topics/actuator_controls.h>
#include <uORB/topics/vehicle_rates_setpoint.h>
#include <uORB/topics/vehicle_attitude.h>
#include <uORB/topics/parameter_update.h>
#include <systemlib/param/param.h>
#include <systemlib/pid/pid.h>
#include <systemlib/geo/geo.h>
#include <systemlib/perf_counter.h>
#include <systemlib/systemlib.h>
/*
* Controller parameters, accessible via MAVLink
*
*/
PARAM_DEFINE_FLOAT(FW_HEAD_P, 0.1f);
PARAM_DEFINE_FLOAT(FW_HEADR_I, 0.1f);
PARAM_DEFINE_FLOAT(FW_HEADR_LIM, 1.5f); //TODO: think about reasonable value
PARAM_DEFINE_FLOAT(FW_XTRACK_P, 0.01745f); // Radians per meter off track
PARAM_DEFINE_FLOAT(FW_ALT_P, 0.1f);
PARAM_DEFINE_FLOAT(FW_ROLL_LIM, 0.7f); // Roll angle limit in radians
PARAM_DEFINE_FLOAT(FW_HEADR_P, 0.1f);
PARAM_DEFINE_FLOAT(FW_PITCH_LIM, 0.35f); /**< Pitch angle limit in radians per second */
struct fw_pos_control_params {
float heading_p;
float headingr_p;
float headingr_i;
float headingr_lim;
float xtrack_p;
float altitude_p;
float roll_lim;
float pitch_lim;
};
struct fw_pos_control_param_handles {
param_t heading_p;
param_t headingr_p;
param_t headingr_i;
param_t headingr_lim;
param_t xtrack_p;
param_t altitude_p;
param_t roll_lim;
param_t pitch_lim;
};
struct planned_path_segments_s {
bool segment_type;
double start_lat; // Start of line or center of arc
double start_lon;
double end_lat;
double end_lon;
float radius; // Radius of arc
float arc_start_bearing; // Bearing from center to start of arc
float arc_sweep; // Angle (radians) swept out by arc around center.
// Positive for clockwise, negative for counter-clockwise
};
/* Prototypes */
/* Internal Prototypes */
static int parameters_init(struct fw_pos_control_param_handles *h);
static int parameters_update(const struct fw_pos_control_param_handles *h, struct fw_pos_control_params *p);
/**
* Deamon management function.
*/
__EXPORT int fixedwing_pos_control_main(int argc, char *argv[]);
/**
* Mainloop of deamon.
*/
int fixedwing_pos_control_thread_main(int argc, char *argv[]);
/**
* Print the correct usage.
*/
static void usage(const char *reason);
/* Variables */
static bool thread_should_exit = false; /**< Deamon exit flag */
static bool thread_running = false; /**< Deamon status flag */
static int deamon_task; /**< Handle of deamon task / thread */
/**
* Parameter management
*/
static int parameters_init(struct fw_pos_control_param_handles *h)
{
/* PID parameters */
h->heading_p = param_find("FW_HEAD_P");
h->headingr_p = param_find("FW_HEADR_P");
h->headingr_i = param_find("FW_HEADR_I");
h->headingr_lim = param_find("FW_HEADR_LIM");
h->xtrack_p = param_find("FW_XTRACK_P");
h->altitude_p = param_find("FW_ALT_P");
h->roll_lim = param_find("FW_ROLL_LIM");
h->pitch_lim = param_find("FW_PITCH_LIM");
return OK;
}
static int parameters_update(const struct fw_pos_control_param_handles *h, struct fw_pos_control_params *p)
{
param_get(h->heading_p, &(p->heading_p));
param_get(h->headingr_p, &(p->headingr_p));
param_get(h->headingr_i, &(p->headingr_i));
param_get(h->headingr_lim, &(p->headingr_lim));
param_get(h->xtrack_p, &(p->xtrack_p));
param_get(h->altitude_p, &(p->altitude_p));
param_get(h->roll_lim, &(p->roll_lim));
param_get(h->pitch_lim, &(p->pitch_lim));
return OK;
}
/* Main Thread */
int fixedwing_pos_control_thread_main(int argc, char *argv[])
{
/* read arguments */
bool verbose = false;
for (int i = 1; i < argc; i++) {
if (strcmp(argv[i], "-v") == 0 || strcmp(argv[i], "--verbose") == 0) {
verbose = true;
}
}
/* welcome user */
printf("[fixedwing pos control] started\n");
/* declare and safely initialize all structs */
struct vehicle_global_position_s global_pos;
memset(&global_pos, 0, sizeof(global_pos));
struct vehicle_global_position_s start_pos; // Temporary variable, replace with
memset(&start_pos, 0, sizeof(start_pos)); // previous waypoint when available
struct vehicle_global_position_setpoint_s global_setpoint;
memset(&global_setpoint, 0, sizeof(global_setpoint));
struct vehicle_attitude_s att;
memset(&att, 0, sizeof(att));
struct crosstrack_error_s xtrack_err;
memset(&xtrack_err, 0, sizeof(xtrack_err));
struct parameter_update_s param_update;
memset(&param_update, 0, sizeof(param_update));
/* output structs */
struct vehicle_attitude_setpoint_s attitude_setpoint;
memset(&attitude_setpoint, 0, sizeof(attitude_setpoint));
/* publish attitude setpoint */
attitude_setpoint.roll_body = 0.0f;
attitude_setpoint.pitch_body = 0.0f;
attitude_setpoint.yaw_body = 0.0f;
attitude_setpoint.thrust = 0.0f;
orb_advert_t attitude_setpoint_pub = orb_advertise(ORB_ID(vehicle_attitude_setpoint), &attitude_setpoint);
/* subscribe */
int global_pos_sub = orb_subscribe(ORB_ID(vehicle_global_position));
int global_setpoint_sub = orb_subscribe(ORB_ID(vehicle_global_position_setpoint));
int att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
int param_sub = orb_subscribe(ORB_ID(parameter_update));
/* Setup of loop */
struct pollfd fds[2] = {
{ .fd = param_sub, .events = POLLIN },
{ .fd = att_sub, .events = POLLIN }
};
bool global_sp_updated_set_once = false;
float psi_track = 0.0f;
int counter = 0;
struct fw_pos_control_params p;
struct fw_pos_control_param_handles h;
PID_t heading_controller;
PID_t heading_rate_controller;
PID_t offtrack_controller;
PID_t altitude_controller;
parameters_init(&h);
parameters_update(&h, &p);
pid_init(&heading_controller, p.heading_p, 0.0f, 0.0f, 0.0f, 10000.0f, PID_MODE_DERIVATIV_NONE, 0.0f); //arbitrary high limit
pid_init(&heading_rate_controller, p.headingr_p, p.headingr_i, 0.0f, 0.0f, p.roll_lim, PID_MODE_DERIVATIV_NONE, 0.0f);
pid_init(&altitude_controller, p.altitude_p, 0.0f, 0.0f, 0.0f, p.pitch_lim, PID_MODE_DERIVATIV_NONE, 0.0f);
pid_init(&offtrack_controller, p.xtrack_p, 0.0f, 0.0f, 0.0f , 60.0f * M_DEG_TO_RAD, PID_MODE_DERIVATIV_NONE, 0.0f); //TODO: remove hardcoded value
/* error and performance monitoring */
perf_counter_t fw_interval_perf = perf_alloc(PC_INTERVAL, "fixedwing_pos_control_interval");
perf_counter_t fw_err_perf = perf_alloc(PC_COUNT, "fixedwing_pos_control_err");
while (!thread_should_exit) {
/* wait for a sensor update, check for exit condition every 500 ms */
int ret = poll(fds, 2, 500);
if (ret < 0) {
/* poll error, count it in perf */
perf_count(fw_err_perf);
} else if (ret == 0) {
/* no return value, ignore */
} else {
/* only update parameters if they changed */
if (fds[0].revents & POLLIN) {
/* read from param to clear updated flag */
struct parameter_update_s update;
orb_copy(ORB_ID(parameter_update), param_sub, &update);
/* update parameters from storage */
parameters_update(&h, &p);
pid_set_parameters(&heading_controller, p.heading_p, 0, 0, 0, 10000.0f); //arbitrary high limit
pid_set_parameters(&heading_rate_controller, p.headingr_p, p.headingr_i, 0, 0, p.roll_lim);
pid_set_parameters(&altitude_controller, p.altitude_p, 0, 0, 0, p.pitch_lim);
pid_set_parameters(&offtrack_controller, p.xtrack_p, 0, 0, 0, 60.0f * M_DEG_TO_RAD); //TODO: remove hardcoded value
}
/* only run controller if attitude changed */
if (fds[1].revents & POLLIN) {
static uint64_t last_run = 0;
const float deltaT = (hrt_absolute_time() - last_run) / 1000000.0f;
last_run = hrt_absolute_time();
/* check if there is a new position or setpoint */
bool pos_updated;
orb_check(global_pos_sub, &pos_updated);
bool global_sp_updated;
orb_check(global_setpoint_sub, &global_sp_updated);
/* load local copies */
orb_copy(ORB_ID(vehicle_attitude), att_sub, &att);
if (pos_updated) {
orb_copy(ORB_ID(vehicle_global_position), global_pos_sub, &global_pos);
}
if (global_sp_updated) {
orb_copy(ORB_ID(vehicle_global_position_setpoint), global_setpoint_sub, &global_setpoint);
start_pos = global_pos; //for now using the current position as the startpoint (= approx. last waypoint because the setpoint switch occurs at the waypoint)
global_sp_updated_set_once = true;
psi_track = get_bearing_to_next_waypoint(global_pos.lat, global_pos.lon,
(double)global_setpoint.lat / (double)1e7d, (double)global_setpoint.lon / (double)1e7d);
printf("next wp direction: %0.4f\n", (double)psi_track);
}
/* Simple Horizontal Control */
if (global_sp_updated_set_once) {
// if (counter % 100 == 0)
// printf("lat_sp %d, ln_sp %d, lat: %d, lon: %d\n", global_setpoint.lat, global_setpoint.lon, global_pos.lat, global_pos.lon);
/* calculate crosstrack error */
// Only the case of a straight line track following handled so far
int distance_res = get_distance_to_line(&xtrack_err, (double)global_pos.lat / (double)1e7d, (double)global_pos.lon / (double)1e7d,
(double)start_pos.lat / (double)1e7d, (double)start_pos.lon / (double)1e7d,
(double)global_setpoint.lat / (double)1e7d, (double)global_setpoint.lon / (double)1e7d);
// XXX what is xtrack_err.past_end?
if (distance_res == OK /*&& !xtrack_err.past_end*/) {
float delta_psi_c = pid_calculate(&offtrack_controller, 0, xtrack_err.distance, 0.0f, 0.0f); //p.xtrack_p * xtrack_err.distance
float psi_c = psi_track + delta_psi_c;
float psi_e = psi_c - att.yaw;
/* wrap difference back onto -pi..pi range */
psi_e = _wrap_pi(psi_e);
if (verbose) {
printf("xtrack_err.distance %.4f ", (double)xtrack_err.distance);
printf("delta_psi_c %.4f ", (double)delta_psi_c);
printf("psi_c %.4f ", (double)psi_c);
printf("att.yaw %.4f ", (double)att.yaw);
printf("psi_e %.4f ", (double)psi_e);
}
/* calculate roll setpoint, do this artificially around zero */
float delta_psi_rate_c = pid_calculate(&heading_controller, psi_e, 0.0f, 0.0f, 0.0f);
float psi_rate_track = 0; //=V_gr/r_track , this will be needed for implementation of arc following
float psi_rate_c = delta_psi_rate_c + psi_rate_track;
/* limit turn rate */
if (psi_rate_c > p.headingr_lim) {
psi_rate_c = p.headingr_lim;
} else if (psi_rate_c < -p.headingr_lim) {
psi_rate_c = -p.headingr_lim;
}
float psi_rate_e = psi_rate_c - att.yawspeed;
// XXX sanity check: Assume 10 m/s stall speed and no stall condition
float ground_speed = sqrtf(global_pos.vx * global_pos.vx + global_pos.vy * global_pos.vy);
if (ground_speed < 10.0f) {
ground_speed = 10.0f;
}
float psi_rate_e_scaled = psi_rate_e * ground_speed / 9.81f; //* V_gr / g
attitude_setpoint.roll_body = pid_calculate(&heading_rate_controller, psi_rate_e_scaled, 0.0f, 0.0f, deltaT);
if (verbose) {
printf("psi_rate_c %.4f ", (double)psi_rate_c);
printf("psi_rate_e_scaled %.4f ", (double)psi_rate_e_scaled);
printf("rollbody %.4f\n", (double)attitude_setpoint.roll_body);
}
if (verbose && counter % 100 == 0)
printf("xtrack_err.distance: %0.4f, delta_psi_c: %0.4f\n", xtrack_err.distance, delta_psi_c);
} else {
if (verbose && counter % 100 == 0)
printf("distance_res: %d, past_end %d\n", distance_res, xtrack_err.past_end);
}
/* Very simple Altitude Control */
if (pos_updated) {
//TODO: take care of relative vs. ab. altitude
attitude_setpoint.pitch_body = pid_calculate(&altitude_controller, global_setpoint.altitude, global_pos.alt, 0.0f, 0.0f);
}
// XXX need speed control
attitude_setpoint.thrust = 0.7f;
/* publish the attitude setpoint */
orb_publish(ORB_ID(vehicle_attitude_setpoint), attitude_setpoint_pub, &attitude_setpoint);
/* measure in what intervals the controller runs */
perf_count(fw_interval_perf);
counter++;
} else {
// XXX no setpoint, decent default needed (loiter?)
}
}
}
}
printf("[fixedwing_pos_control] exiting.\n");
thread_running = false;
close(attitude_setpoint_pub);
fflush(stdout);
exit(0);
return 0;
}
/* Startup Functions */
static void
usage(const char *reason)
{
if (reason)
fprintf(stderr, "%s\n", reason);
fprintf(stderr, "usage: fixedwing_pos_control {start|stop|status}\n\n");
exit(1);
}
/**
* The deamon app only briefly exists to start
* the background job. The stack size assigned in the
* Makefile does only apply to this management task.
*
* The actual stack size should be set in the call
* to task_create().
*/
int fixedwing_pos_control_main(int argc, char *argv[])
{
if (argc < 1)
usage("missing command");
if (!strcmp(argv[1], "start")) {
if (thread_running) {
printf("fixedwing_pos_control already running\n");
/* this is not an error */
exit(0);
}
thread_should_exit = false;
deamon_task = task_spawn_cmd("fixedwing_pos_control",
SCHED_DEFAULT,
SCHED_PRIORITY_MAX - 20,
2048,
fixedwing_pos_control_thread_main,
(argv) ? (const char **)&argv[2] : (const char **)NULL);
thread_running = true;
exit(0);
}
if (!strcmp(argv[1], "stop")) {
thread_should_exit = true;
exit(0);
}
if (!strcmp(argv[1], "status")) {
if (thread_running) {
printf("\tfixedwing_pos_control is running\n");
} else {
printf("\tfixedwing_pos_control not started\n");
}
exit(0);
}
usage("unrecognized command");
exit(1);
}
src/modules/fixedwing_pos_control/module.mk
-40
View File
@@ -1,40 +0,0 @@
############################################################################
#
# Copyright (c) 2012, 2013 PX4 Development Team. All rights reserved.
#
# Redistribution and use in source and binary forms, with or without
# modification, are permitted provided that the following conditions
# are met:
#
# 1. Redistributions of source code must retain the above copyright
# notice, this list of conditions and the following disclaimer.
# 2. Redistributions in binary form must reproduce the above copyright
# notice, this list of conditions and the following disclaimer in
# the documentation and/or other materials provided with the
# distribution.
# 3. Neither the name PX4 nor the names of its contributors may be
# used to endorse or promote products derived from this software
# without specific prior written permission.
#
# THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
# "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
# LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
# FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
# COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
# INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
# BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
# OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
# AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
# LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
# ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
# POSSIBILITY OF SUCH DAMAGE.
#
############################################################################
#
# Fixedwing PositionControl application
#
MODULE_COMMAND = fixedwing_pos_control
SRCS = fixedwing_pos_control_main.c
src/modules/mavlink/mavlink_main.cpp
+2
View File
@@ -1544,6 +1544,8 @@ Mavlink::mavlink_missionlib_send_gcs_string(const char *string)
{
const int len = MAVLINK_MSG_STATUSTEXT_FIELD_TEXT_LEN;
mavlink_statustext_t statustext;
statustext.severity = MAV_SEVERITY_INFO;
int i = 0;
while (i < len - 1) {
src/modules/mavlink/mavlink_messages.cpp
+18 -17
View File
@@ -819,11 +819,11 @@ protected:
void send(const hrt_abstime t)
{
bool updated = status_sub->update(t);
updated |= pos_sp_triplet_sub->update(t);
updated |= act_sub->update(t);
bool updated = act_sub->update(t);
(void)pos_sp_triplet_sub->update(t);
(void)status_sub->update(t);
if (updated) {
if (updated && (status->arming_state == ARMING_STATE_ARMED)) {
/* translate the current syste state to mavlink state and mode */
uint8_t mavlink_state;
uint8_t mavlink_base_mode;
@@ -1339,22 +1339,23 @@ protected:
void send(const hrt_abstime t)
{
(void)range_sub->update(t);
if (range_sub->update(t)) {
uint8_t type;
uint8_t type;
switch (range->type) {
case RANGE_FINDER_TYPE_LASER:
type = MAV_DISTANCE_SENSOR_LASER;
break;
switch (range->type) {
case RANGE_FINDER_TYPE_LASER:
type = MAV_DISTANCE_SENSOR_LASER;
break;
}
uint8_t id = 0;
uint8_t orientation = 0;
uint8_t covariance = 20;
mavlink_msg_distance_sensor_send(_channel, range->timestamp / 1000, type, id, orientation,
range->minimum_distance*100, range->maximum_distance*100, range->distance*100, covariance);
}
uint8_t id = 0;
uint8_t orientation = 0;
uint8_t covariance = 20;
mavlink_msg_distance_sensor_send(_channel, range->timestamp / 1000, type, id, orientation,
range->minimum_distance*100, range->maximum_distance*100, range->distance*100, covariance);
}
};
src/modules/mavlink/mavlink_receiver.cpp
+8 -2
View File
@@ -217,6 +217,12 @@ MavlinkReceiver::handle_message_command_long(mavlink_message_t *msg)
_mavlink->_task_should_exit = true;
} else {
if (msg->sysid == mavlink_system.sysid && msg->compid == mavlink_system.compid) {
warnx("ignoring CMD spoofed with same SYS/COMP ID");
return;
}
struct vehicle_command_s vcmd;
memset(&vcmd, 0, sizeof(vcmd));
@@ -432,8 +438,8 @@ MavlinkReceiver::handle_message_manual_control(mavlink_message_t *msg)
memset(&manual, 0, sizeof(manual));
manual.timestamp = hrt_absolute_time();
manual.roll = man.x / 1000.0f;
manual.pitch = man.y / 1000.0f;
manual.pitch = man.x / 1000.0f;
manual.roll = man.y / 1000.0f;
manual.yaw = man.r / 1000.0f;
manual.throttle = man.z / 1000.0f;
src/modules/position_estimator/module.mk
-44
View File
@@ -1,44 +0,0 @@
############################################################################
#
# Copyright (c) 2012, 2013 PX4 Development Team. All rights reserved.
#
# Redistribution and use in source and binary forms, with or without
# modification, are permitted provided that the following conditions
# are met:
#
# 1. Redistributions of source code must retain the above copyright
# notice, this list of conditions and the following disclaimer.
# 2. Redistributions in binary form must reproduce the above copyright
# notice, this list of conditions and the following disclaimer in
# the documentation and/or other materials provided with the
# distribution.
# 3. Neither the name PX4 nor the names of its contributors may be
# used to endorse or promote products derived from this software
# without specific prior written permission.
#
# THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
# "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
# LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
# FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
# COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
# INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
# BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
# OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
# AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
# LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
# ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
# POSSIBILITY OF SUCH DAMAGE.
#
############################################################################
#
# Makefile to build the position estimator
#
MODULE_COMMAND = position_estimator
# XXX this should be converted to a deamon, its a pretty bad example app
MODULE_PRIORITY = SCHED_PRIORITY_DEFAULT
MODULE_STACKSIZE = 4096
SRCS = position_estimator_main.c
src/modules/position_estimator/position_estimator_main.c
-423
View File
@@ -1,423 +0,0 @@
/****************************************************************************
*
* Copyright (C) 2008-2012 PX4 Development Team. All rights reserved.
* Author: Tobias Naegeli <naegelit@student.ethz.ch>
* Thomas Gubler <thomasgubler@student.ethz.ch>
* Julian Oes <joes@student.ethz.ch>
* Lorenz Meier <lm@inf.ethz.ch>
*
* Redistribution and use in source and binary forms, with or without
* modification, are permitted provided that the following conditions
* are met:
*
* 1. Redistributions of source code must retain the above copyright
* notice, this list of conditions and the following disclaimer.
* 2. Redistributions in binary form must reproduce the above copyright
* notice, this list of conditions and the following disclaimer in
* the documentation and/or other materials provided with the
* distribution.
* 3. Neither the name PX4 nor the names of its contributors may be
* used to endorse or promote products derived from this software
* without specific prior written permission.
*
* THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
* "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
* LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
* FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
* COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
* INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
* BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
* OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
* AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
* LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
* ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
* POSSIBILITY OF SUCH DAMAGE.
*
****************************************************************************/
/**
* @file position_estimator_main.c
* Model-identification based position estimator for multirotors
*/
#include <nuttx/config.h>
#include <unistd.h>
#include <stdlib.h>
#include <stdio.h>
#include <stdbool.h>
#include <fcntl.h>
#include <float.h>
#include <nuttx/sched.h>
#include <sys/prctl.h>
#include <termios.h>
#include <errno.h>
#include <limits.h>
#include <math.h>
#include <uORB/uORB.h>
#include <uORB/topics/vehicle_status.h>
#include <uORB/topics/vehicle_attitude.h>
#include <uORB/topics/vehicle_gps_position.h>
#include <uORB/topics/vehicle_global_position.h>
#include <uORB/topics/vehicle_local_position.h>
#include <poll.h>
#define N_STATES 6
#define ERROR_COVARIANCE_INIT 3
#define R_EARTH 6371000.0
#define PROJECTION_INITIALIZE_COUNTER_LIMIT 5000
#define REPROJECTION_COUNTER_LIMIT 125
__EXPORT int position_estimator_main(int argc, char *argv[]);
static uint16_t position_estimator_counter_position_information;
/* values for map projection */
static double phi_1;
static double sin_phi_1;
static double cos_phi_1;
static double lambda_0;
static double scale;
/**
* Initializes the map transformation.
*
* Initializes the transformation between the geographic coordinate system and the azimuthal equidistant plane
* @param lat in degrees (47.1234567°, not 471234567°)
* @param lon in degrees (8.1234567°, not 81234567°)
*/
static void map_projection_init(double lat_0, double lon_0) //lat_0, lon_0 are expected to be in correct format: -> 47.1234567 and not 471234567
{
/* notation and formulas according to: http://mathworld.wolfram.com/AzimuthalEquidistantProjection.html */
phi_1 = lat_0 / 180.0 * M_PI;
lambda_0 = lon_0 / 180.0 * M_PI;
sin_phi_1 = sin(phi_1);
cos_phi_1 = cos(phi_1);
/* calculate local scale by using the relation of true distance and the distance on plane */ //TODO: this is a quick solution, there are probably easier ways to determine the scale
/* 1) calculate true distance d on sphere to a point: http://www.movable-type.co.uk/scripts/latlong.html */
const double r_earth = 6371000;
double lat1 = phi_1;
double lon1 = lambda_0;
double lat2 = phi_1 + 0.5 / 180 * M_PI;
double lon2 = lambda_0 + 0.5 / 180 * M_PI;
double sin_lat_2 = sin(lat2);
double cos_lat_2 = cos(lat2);
double d = acos(sin(lat1) * sin_lat_2 + cos(lat1) * cos_lat_2 * cos(lon2 - lon1)) * r_earth;
/* 2) calculate distance rho on plane */
double k_bar = 0;
double c = acos(sin_phi_1 * sin_lat_2 + cos_phi_1 * cos_lat_2 * cos(lon2 - lambda_0));
if (0 != c)
k_bar = c / sin(c);
double x2 = k_bar * (cos_lat_2 * sin(lon2 - lambda_0)); //Projection of point 2 on plane
double y2 = k_bar * ((cos_phi_1 * sin_lat_2 - sin_phi_1 * cos_lat_2 * cos(lon2 - lambda_0)));
double rho = sqrt(pow(x2, 2) + pow(y2, 2));
scale = d / rho;
}
/**
* Transforms a point in the geographic coordinate system to the local azimuthal equidistant plane
* @param x north
* @param y east
* @param lat in degrees (47.1234567°, not 471234567°)
* @param lon in degrees (8.1234567°, not 81234567°)
*/
static void map_projection_project(double lat, double lon, float *x, float *y)
{
/* notation and formulas accoring to: http://mathworld.wolfram.com/AzimuthalEquidistantProjection.html */
double phi = lat / 180.0 * M_PI;
double lambda = lon / 180.0 * M_PI;
double sin_phi = sin(phi);
double cos_phi = cos(phi);
double k_bar = 0;
/* using small angle approximation (formula in comment is without aproximation) */
double c = acos(sin_phi_1 * sin_phi + cos_phi_1 * cos_phi * (1 - pow((lambda - lambda_0), 2) / 2)); //double c = acos( sin_phi_1 * sin_phi + cos_phi_1 * cos_phi * cos(lambda - lambda_0) );
if (0 != c)
k_bar = c / sin(c);
/* using small angle approximation (formula in comment is without aproximation) */
*y = k_bar * (cos_phi * (lambda - lambda_0)) * scale;//*y = k_bar * (cos_phi * sin(lambda - lambda_0)) * scale;
*x = k_bar * ((cos_phi_1 * sin_phi - sin_phi_1 * cos_phi * (1 - pow((lambda - lambda_0), 2) / 2))) * scale; // *x = k_bar * ((cos_phi_1 * sin_phi - sin_phi_1 * cos_phi * cos(lambda - lambda_0))) * scale;
// printf("%phi_1=%.10f, lambda_0 =%.10f\n", phi_1, lambda_0);
}
/**
* Transforms a point in the local azimuthal equidistant plane to the geographic coordinate system
*
* @param x north
* @param y east
* @param lat in degrees (47.1234567°, not 471234567°)
* @param lon in degrees (8.1234567°, not 81234567°)
*/
static void map_projection_reproject(float x, float y, double *lat, double *lon)
{
/* notation and formulas accoring to: http://mathworld.wolfram.com/AzimuthalEquidistantProjection.html */
double x_descaled = x / scale;
double y_descaled = y / scale;
double c = sqrt(pow(x_descaled, 2) + pow(y_descaled, 2));
double sin_c = sin(c);
double cos_c = cos(c);
double lat_sphere = 0;
if (c != 0)
lat_sphere = asin(cos_c * sin_phi_1 + (x_descaled * sin_c * cos_phi_1) / c);
else
lat_sphere = asin(cos_c * sin_phi_1);
// printf("lat_sphere = %.10f\n",lat_sphere);
double lon_sphere = 0;
if (phi_1 == M_PI / 2) {
//using small angle approximation (formula in comment is without aproximation)
lon_sphere = (lambda_0 - y_descaled / x_descaled); //lon_sphere = (lambda_0 + atan2(-y_descaled, x_descaled));
} else if (phi_1 == -M_PI / 2) {
//using small angle approximation (formula in comment is without aproximation)
lon_sphere = (lambda_0 + y_descaled / x_descaled); //lon_sphere = (lambda_0 + atan2(y_descaled, x_descaled));
} else {
lon_sphere = (lambda_0 + atan2(y_descaled * sin_c , c * cos_phi_1 * cos_c - x_descaled * sin_phi_1 * sin_c));
//using small angle approximation
// double denominator = (c * cos_phi_1 * cos_c - x_descaled * sin_phi_1 * sin_c);
// if(denominator != 0)
// {
// lon_sphere = (lambda_0 + (y_descaled * sin_c) / denominator);
// }
// else
// {
// ...
// }
}
// printf("lon_sphere = %.10f\n",lon_sphere);
*lat = lat_sphere * 180.0 / M_PI;
*lon = lon_sphere * 180.0 / M_PI;
}
/****************************************************************************
* main
****************************************************************************/
int position_estimator_main(int argc, char *argv[])
{
/* welcome user */
printf("[multirotor position_estimator] started\n");
/* initialize values */
static float u[2] = {0, 0};
static float z[3] = {0, 0, 0};
static float xapo[N_STATES] = {0, 0, 0, 0, 0, 0};
static float Papo[N_STATES * N_STATES] = {ERROR_COVARIANCE_INIT, 0, 0, 0, 0, 0,
ERROR_COVARIANCE_INIT, 0, 0, 0, 0, 0,
ERROR_COVARIANCE_INIT, 0, 0, 0, 0, 0,
ERROR_COVARIANCE_INIT, 0, 0, 0, 0, 0,
ERROR_COVARIANCE_INIT, 0, 0, 0, 0, 0,
ERROR_COVARIANCE_INIT, 0, 0, 0, 0, 0
};
static float xapo1[N_STATES];
static float Papo1[36];
static float gps_covariance[3] = {0.0f, 0.0f, 0.0f};
static uint16_t counter = 0;
position_estimator_counter_position_information = 0;
uint8_t predict_only = 1;
bool gps_valid = false;
bool new_initialization = true;
static double lat_current = 0.0d;//[°]] --> 47.0
static double lon_current = 0.0d; //[°]] -->8.5
float alt_current = 0.0f;
//TODO: handle flight without gps but with estimator
/* subscribe to vehicle status, attitude, gps */
struct vehicle_gps_position_s gps;
gps.fix_type = 0;
struct vehicle_status_s vstatus;
struct vehicle_attitude_s att;
int vehicle_gps_sub = orb_subscribe(ORB_ID(vehicle_gps_position));
int vehicle_status_sub = orb_subscribe(ORB_ID(vehicle_status));
/* subscribe to attitude at 100 Hz */
int vehicle_attitude_sub = orb_subscribe(ORB_ID(vehicle_attitude));
/* wait until gps signal turns valid, only then can we initialize the projection */
while (gps.fix_type < 3) {
struct pollfd fds[1] = { {.fd = vehicle_gps_sub, .events = POLLIN} };
/* wait for GPS updates, BUT READ VEHICLE STATUS (!)
* this choice is critical, since the vehicle status might not
* actually change, if this app is started after GPS lock was
* aquired.
*/
if (poll(fds, 1, 5000)) {
/* Wait for the GPS update to propagate (we have some time) */
usleep(5000);
/* Read wether the vehicle status changed */
orb_copy(ORB_ID(vehicle_gps_position), vehicle_gps_sub, &gps);
gps_valid = (gps.fix_type > 2);
}
}
/* get gps value for first initialization */
orb_copy(ORB_ID(vehicle_gps_position), vehicle_gps_sub, &gps);
lat_current = ((double)(gps.lat)) * 1e-7;
lon_current = ((double)(gps.lon)) * 1e-7;
alt_current = gps.alt * 1e-3;
/* initialize coordinates */
map_projection_init(lat_current, lon_current);
/* publish global position messages only after first GPS message */
struct vehicle_local_position_s local_pos = {
.x = 0,
.y = 0,
.z = 0
};
orb_advert_t local_pos_pub = orb_advertise(ORB_ID(vehicle_local_position), &local_pos);
printf("[multirotor position estimator] initialized projection with: lat: %.10f, lon:%.10f\n", lat_current, lon_current);
while (1) {
/*This runs at the rate of the sensors, if we have also a new gps update this is used in the position_estimator function */
struct pollfd fds[1] = { {.fd = vehicle_attitude_sub, .events = POLLIN} };
if (poll(fds, 1, 5000) <= 0) {
/* error / timeout */
} else {
orb_copy(ORB_ID(vehicle_attitude), vehicle_attitude_sub, &att);
/* got attitude, updating pos as well */
orb_copy(ORB_ID(vehicle_gps_position), vehicle_gps_sub, &gps);
orb_copy(ORB_ID(vehicle_status), vehicle_status_sub, &vstatus);
/*copy attitude */
u[0] = att.roll;
u[1] = att.pitch;
/* initialize map projection with the last estimate (not at full rate) */
if (gps.fix_type > 2) {
/* Project gps lat lon (Geographic coordinate system) to plane*/
map_projection_project(((double)(gps.lat)) * 1e-7, ((double)(gps.lon)) * 1e-7, &(z[0]), &(z[1]));
local_pos.x = z[0];
local_pos.y = z[1];
/* negative offset from initialization altitude */
local_pos.z = alt_current - (gps.alt) * 1e-3;
orb_publish(ORB_ID(vehicle_local_position), local_pos_pub, &local_pos);
}
// gps_covariance[0] = gps.eph; //TODO: needs scaling
// gps_covariance[1] = gps.eph;
// gps_covariance[2] = gps.epv;
// } else {
// /* we can not use the gps signal (it is of low quality) */
// predict_only = 1;
// }
// // predict_only = 0; //TODO: only for testing, removeme, XXX
// // z[0] = sinf(((float)counter)/180.0f*3.14159265f); //TODO: only for testing, removeme, XXX
// // usleep(100000); //TODO: only for testing, removeme, XXX
// /*Get new estimation (this is calculated in the plane) */
// //TODO: if new_initialization == true: use 0,0,0, else use xapo
// if (true == new_initialization) { //TODO,XXX: uncomment!
// xapo[0] = 0; //we have a new plane initialization. the current estimate is in the center of the plane
// xapo[2] = 0;
// xapo[4] = 0;
// position_estimator(u, z, xapo, Papo, gps_covariance, predict_only, xapo1, Papo1);
// } else {
// position_estimator(u, z, xapo, Papo, gps_covariance, predict_only, xapo1, Papo1);
// }
// /* Copy values from xapo1 to xapo */
// int i;
// for (i = 0; i < N_STATES; i++) {
// xapo[i] = xapo1[i];
// }
// if ((counter % REPROJECTION_COUNTER_LIMIT == 0) || (counter % (PROJECTION_INITIALIZE_COUNTER_LIMIT - 1) == 0)) {
// /* Reproject from plane to geographic coordinate system */
// // map_projection_reproject(xapo1[0], xapo1[2], map_scale, phi_1, lambda_0, &lat_current, &lon_current) //TODO,XXX: uncomment!
// map_projection_reproject(z[0], z[1], &lat_current, &lon_current); //do not use estimator for projection testing, removeme
// // //DEBUG
// // if(counter%500 == 0)
// // {
// // printf("phi_1: %.10f\n", phi_1);
// // printf("lambda_0: %.10f\n", lambda_0);
// // printf("lat_estimated: %.10f\n", lat_current);
// // printf("lon_estimated: %.10f\n", lon_current);
// // printf("z[0]=%.10f, z[1]=%.10f, z[2]=%f\n", z[0], z[1], z[2]);
// // fflush(stdout);
// //
// // }
// // if(!isnan(lat_current) && !isnan(lon_current))// && !isnan(xapo1[4]) && !isnan(xapo1[1]) && !isnan(xapo1[3]) && !isnan(xapo1[5]))
// // {
// /* send out */
// global_pos.lat = lat_current;
// global_pos.lon = lon_current;
// global_pos.alt = xapo1[4];
// global_pos.vx = xapo1[1];
// global_pos.vy = xapo1[3];
// global_pos.vz = xapo1[5];
/* publish current estimate */
// orb_publish(ORB_ID(vehicle_global_position), global_pos_pub, &global_pos);
// }
// else
// {
// printf("[position estimator] ERROR: nan values, lat_current=%.4f, lon_current=%.4f, z[0]=%.4f z[1]=%.4f\n", lat_current, lon_current, z[0], z[1]);
// fflush(stdout);
// }
// }
counter++;
}
}
return 0;
}
src/modules/position_estimator_mc/codegen/kalman_dlqe1.c
-58
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@@ -1,58 +0,0 @@
/*
* kalman_dlqe1.c
*
* Code generation for function 'kalman_dlqe1'
*
* C source code generated on: Wed Feb 13 20:34:32 2013
*
*/
/* Include files */
#include "rt_nonfinite.h"
#include "kalman_dlqe1.h"
/* Type Definitions */
/* Named Constants */
/* Variable Declarations */
/* Variable Definitions */
/* Function Declarations */
/* Function Definitions */
void kalman_dlqe1(const real32_T A[9], const real32_T C[3], const real32_T K[3],
const real32_T x_aposteriori_k[3], real32_T z, real32_T
x_aposteriori[3])
{
printf("[dlqe input]: x_aposteriori_k %12.8f\t %12.8f\t %12.8f\t z:%12.8f\n", (double)(x_aposteriori_k[0]), (double)(x_aposteriori_k[1]), (double)(x_aposteriori_k[2]), (double)z);
printf("[dlqe input]: C[0]: %12.8f\tC[1] %12.8f\tC[2] %12.8f\n", (double)(C[0]), (double)(C[1]), (double)(C[2]));
real32_T y;
int32_T i0;
real32_T b_y[3];
int32_T i1;
real32_T f0;
y = 0.0F;
for (i0 = 0; i0 < 3; i0++) {
b_y[i0] = 0.0F;
for (i1 = 0; i1 < 3; i1++) {
b_y[i0] += C[i1] * A[i1 + 3 * i0];
}
y += b_y[i0] * x_aposteriori_k[i0];
}
y = z - y;
for (i0 = 0; i0 < 3; i0++) {
f0 = 0.0F;
for (i1 = 0; i1 < 3; i1++) {
f0 += A[i0 + 3 * i1] * x_aposteriori_k[i1];
}
x_aposteriori[i0] = f0 + K[i0] * y;
}
//printf("[dlqe output]: x_aposteriori %12.8f\t %12.8f\t %12.8f\n", (double)(x_aposteriori[0]), (double)(x_aposteriori[1]), (double)(x_aposteriori[2]));
}
/* End of code generation (kalman_dlqe1.c) */
src/modules/position_estimator_mc/codegen/kalman_dlqe1.h
-30
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@@ -1,30 +0,0 @@
/*
* kalman_dlqe1.h
*
* Code generation for function 'kalman_dlqe1'
*
* C source code generated on: Wed Feb 13 20:34:32 2013
*
*/
#ifndef __KALMAN_DLQE1_H__
#define __KALMAN_DLQE1_H__
/* Include files */
#include <stddef.h>
#include <stdlib.h>
#include "rtwtypes.h"
#include "kalman_dlqe1_types.h"
/* Type Definitions */
/* Named Constants */
/* Variable Declarations */
/* Variable Definitions */
/* Function Declarations */
extern void kalman_dlqe1(const real32_T A[9], const real32_T C[3], const real32_T K[3], const real32_T x_aposteriori_k[3], real32_T z, real32_T x_aposteriori[3]);
#endif
/* End of code generation (kalman_dlqe1.h) */
src/modules/position_estimator_mc/codegen/kalman_dlqe1_initialize.c
-31
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@@ -1,31 +0,0 @@
/*
* kalman_dlqe1_initialize.c
*
* Code generation for function 'kalman_dlqe1_initialize'
*
* C source code generated on: Wed Feb 13 20:34:31 2013
*
*/
/* Include files */
#include "rt_nonfinite.h"
#include "kalman_dlqe1.h"
#include "kalman_dlqe1_initialize.h"
/* Type Definitions */
/* Named Constants */
/* Variable Declarations */
/* Variable Definitions */
/* Function Declarations */
/* Function Definitions */
void kalman_dlqe1_initialize(void)
{
rt_InitInfAndNaN(8U);
}
/* End of code generation (kalman_dlqe1_initialize.c) */
src/modules/position_estimator_mc/codegen/kalman_dlqe1_initialize.h
-30
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@@ -1,30 +0,0 @@
/*
* kalman_dlqe1_initialize.h
*
* Code generation for function 'kalman_dlqe1_initialize'
*
* C source code generated on: Wed Feb 13 20:34:31 2013
*
*/
#ifndef __KALMAN_DLQE1_INITIALIZE_H__
#define __KALMAN_DLQE1_INITIALIZE_H__
/* Include files */
#include <stddef.h>
#include <stdlib.h>
#include "rtwtypes.h"
#include "kalman_dlqe1_types.h"
/* Type Definitions */
/* Named Constants */
/* Variable Declarations */
/* Variable Definitions */
/* Function Declarations */
extern void kalman_dlqe1_initialize(void);
#endif
/* End of code generation (kalman_dlqe1_initialize.h) */
src/modules/position_estimator_mc/codegen/kalman_dlqe1_terminate.c
-31
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@@ -1,31 +0,0 @@
/*
* kalman_dlqe1_terminate.c
*
* Code generation for function 'kalman_dlqe1_terminate'
*
* C source code generated on: Wed Feb 13 20:34:31 2013
*
*/
/* Include files */
#include "rt_nonfinite.h"
#include "kalman_dlqe1.h"
#include "kalman_dlqe1_terminate.h"
/* Type Definitions */
/* Named Constants */
/* Variable Declarations */
/* Variable Definitions */
/* Function Declarations */
/* Function Definitions */
void kalman_dlqe1_terminate(void)
{
/* (no terminate code required) */
}
/* End of code generation (kalman_dlqe1_terminate.c) */
src/modules/position_estimator_mc/codegen/kalman_dlqe1_terminate.h
-30
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@@ -1,30 +0,0 @@
/*
* kalman_dlqe1_terminate.h
*
* Code generation for function 'kalman_dlqe1_terminate'
*
* C source code generated on: Wed Feb 13 20:34:32 2013
*
*/
#ifndef __KALMAN_DLQE1_TERMINATE_H__
#define __KALMAN_DLQE1_TERMINATE_H__
/* Include files */
#include <stddef.h>
#include <stdlib.h>
#include "rtwtypes.h"
#include "kalman_dlqe1_types.h"
/* Type Definitions */
/* Named Constants */
/* Variable Declarations */
/* Variable Definitions */
/* Function Declarations */
extern void kalman_dlqe1_terminate(void);
#endif
/* End of code generation (kalman_dlqe1_terminate.h) */
src/modules/position_estimator_mc/codegen/kalman_dlqe1_types.h
-16
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@@ -1,16 +0,0 @@
/*
* kalman_dlqe1_types.h
*
* Code generation for function 'kalman_dlqe1'
*
* C source code generated on: Wed Feb 13 20:34:31 2013
*
*/
#ifndef __KALMAN_DLQE1_TYPES_H__
#define __KALMAN_DLQE1_TYPES_H__
/* Type Definitions */
#endif
/* End of code generation (kalman_dlqe1_types.h) */
src/modules/position_estimator_mc/codegen/kalman_dlqe2.c
-119
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@@ -1,119 +0,0 @@
/*
* kalman_dlqe2.c
*
* Code generation for function 'kalman_dlqe2'
*
* C source code generated on: Thu Feb 14 12:52:28 2013
*
*/
/* Include files */
#include "rt_nonfinite.h"
#include "kalman_dlqe2.h"
/* Type Definitions */
/* Named Constants */
/* Variable Declarations */
/* Variable Definitions */
/* Function Declarations */
static real32_T rt_powf_snf(real32_T u0, real32_T u1);
/* Function Definitions */
static real32_T rt_powf_snf(real32_T u0, real32_T u1)
{
real32_T y;
real32_T f1;
real32_T f2;
if (rtIsNaNF(u0) || rtIsNaNF(u1)) {
y = ((real32_T)rtNaN);
} else {
f1 = (real32_T)fabs(u0);
f2 = (real32_T)fabs(u1);
if (rtIsInfF(u1)) {
if (f1 == 1.0F) {
y = ((real32_T)rtNaN);
} else if (f1 > 1.0F) {
if (u1 > 0.0F) {
y = ((real32_T)rtInf);
} else {
y = 0.0F;
}
} else if (u1 > 0.0F) {
y = 0.0F;
} else {
y = ((real32_T)rtInf);
}
} else if (f2 == 0.0F) {
y = 1.0F;
} else if (f2 == 1.0F) {
if (u1 > 0.0F) {
y = u0;
} else {
y = 1.0F / u0;
}
} else if (u1 == 2.0F) {
y = u0 * u0;
} else if ((u1 == 0.5F) && (u0 >= 0.0F)) {
y = (real32_T)sqrt(u0);
} else if ((u0 < 0.0F) && (u1 > (real32_T)floor(u1))) {
y = ((real32_T)rtNaN);
} else {
y = (real32_T)pow(u0, u1);
}
}
return y;
}
void kalman_dlqe2(real32_T dt, real32_T k1, real32_T k2, real32_T k3, const
real32_T x_aposteriori_k[3], real32_T z, real32_T
x_aposteriori[3])
{
//printf("[dqle2] dt: %12.8f\tvk1 %12.8f\tk2: %12.8f\tk3: %12.8f\n", (double)(dt), (double)(k1), (double)(k2), (double)(k3));
//printf("[dqle2] dt: %8.4f\n", (double)(dt));//, (double)(k1), (double)(k2), (double)(k3));
real32_T A[9];
real32_T y;
int32_T i0;
static const int8_T iv0[3] = { 0, 0, 1 };
real32_T b_k1[3];
int32_T i1;
static const int8_T iv1[3] = { 1, 0, 0 };
real32_T f0;
A[0] = 1.0F;
A[3] = dt;
A[6] = 0.5F * rt_powf_snf(dt, 2.0F);
A[1] = 0.0F;
A[4] = 1.0F;
A[7] = dt;
y = 0.0F;
for (i0 = 0; i0 < 3; i0++) {
A[2 + 3 * i0] = (real32_T)iv0[i0];
b_k1[i0] = 0.0F;
for (i1 = 0; i1 < 3; i1++) {
b_k1[i0] += (real32_T)iv1[i1] * A[i1 + 3 * i0];
}
y += b_k1[i0] * x_aposteriori_k[i0];
}
y = z - y;
b_k1[0] = k1;
b_k1[1] = k2;
b_k1[2] = k3;
for (i0 = 0; i0 < 3; i0++) {
f0 = 0.0F;
for (i1 = 0; i1 < 3; i1++) {
f0 += A[i0 + 3 * i1] * x_aposteriori_k[i1];
}
x_aposteriori[i0] = f0 + b_k1[i0] * y;
}
}
/* End of code generation (kalman_dlqe2.c) */
src/modules/position_estimator_mc/codegen/kalman_dlqe2.h
-32
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@@ -1,32 +0,0 @@
/*
* kalman_dlqe2.h
*
* Code generation for function 'kalman_dlqe2'
*
* C source code generated on: Thu Feb 14 12:52:29 2013
*
*/
#ifndef __KALMAN_DLQE2_H__
#define __KALMAN_DLQE2_H__
/* Include files */
#include <math.h>
#include <stddef.h>
#include <stdlib.h>
#include "rt_nonfinite.h"
#include "rtwtypes.h"
#include "kalman_dlqe2_types.h"
/* Type Definitions */
/* Named Constants */
/* Variable Declarations */
/* Variable Definitions */
/* Function Declarations */
extern void kalman_dlqe2(real32_T dt, real32_T k1, real32_T k2, real32_T k3, const real32_T x_aposteriori_k[3], real32_T z, real32_T x_aposteriori[3]);
#endif
/* End of code generation (kalman_dlqe2.h) */
src/modules/position_estimator_mc/codegen/kalman_dlqe2_initialize.c
-31
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@@ -1,31 +0,0 @@
/*
* kalman_dlqe2_initialize.c
*
* Code generation for function 'kalman_dlqe2_initialize'
*
* C source code generated on: Thu Feb 14 12:52:28 2013
*
*/
/* Include files */
#include "rt_nonfinite.h"
#include "kalman_dlqe2.h"
#include "kalman_dlqe2_initialize.h"
/* Type Definitions */
/* Named Constants */
/* Variable Declarations */
/* Variable Definitions */
/* Function Declarations */
/* Function Definitions */
void kalman_dlqe2_initialize(void)
{
rt_InitInfAndNaN(8U);
}
/* End of code generation (kalman_dlqe2_initialize.c) */
src/modules/position_estimator_mc/codegen/kalman_dlqe2_initialize.h
-32
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@@ -1,32 +0,0 @@
/*
* kalman_dlqe2_initialize.h
*
* Code generation for function 'kalman_dlqe2_initialize'
*
* C source code generated on: Thu Feb 14 12:52:28 2013
*
*/
#ifndef __KALMAN_DLQE2_INITIALIZE_H__
#define __KALMAN_DLQE2_INITIALIZE_H__
/* Include files */
#include <math.h>
#include <stddef.h>
#include <stdlib.h>
#include "rt_nonfinite.h"
#include "rtwtypes.h"
#include "kalman_dlqe2_types.h"
/* Type Definitions */
/* Named Constants */
/* Variable Declarations */
/* Variable Definitions */
/* Function Declarations */
extern void kalman_dlqe2_initialize(void);
#endif
/* End of code generation (kalman_dlqe2_initialize.h) */
src/modules/position_estimator_mc/codegen/kalman_dlqe2_terminate.c
-31
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@@ -1,31 +0,0 @@
/*
* kalman_dlqe2_terminate.c
*
* Code generation for function 'kalman_dlqe2_terminate'
*
* C source code generated on: Thu Feb 14 12:52:28 2013
*
*/
/* Include files */
#include "rt_nonfinite.h"
#include "kalman_dlqe2.h"
#include "kalman_dlqe2_terminate.h"
/* Type Definitions */
/* Named Constants */
/* Variable Declarations */
/* Variable Definitions */
/* Function Declarations */
/* Function Definitions */
void kalman_dlqe2_terminate(void)
{
/* (no terminate code required) */
}
/* End of code generation (kalman_dlqe2_terminate.c) */
src/modules/position_estimator_mc/codegen/kalman_dlqe2_terminate.h
-32
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@@ -1,32 +0,0 @@
/*
* kalman_dlqe2_terminate.h
*
* Code generation for function 'kalman_dlqe2_terminate'
*
* C source code generated on: Thu Feb 14 12:52:28 2013
*
*/
#ifndef __KALMAN_DLQE2_TERMINATE_H__
#define __KALMAN_DLQE2_TERMINATE_H__
/* Include files */
#include <math.h>
#include <stddef.h>
#include <stdlib.h>
#include "rt_nonfinite.h"
#include "rtwtypes.h"
#include "kalman_dlqe2_types.h"
/* Type Definitions */
/* Named Constants */
/* Variable Declarations */
/* Variable Definitions */
/* Function Declarations */
extern void kalman_dlqe2_terminate(void);
#endif
/* End of code generation (kalman_dlqe2_terminate.h) */
src/modules/position_estimator_mc/codegen/kalman_dlqe2_types.h
-16
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@@ -1,16 +0,0 @@
/*
* kalman_dlqe2_types.h
*
* Code generation for function 'kalman_dlqe2'
*
* C source code generated on: Thu Feb 14 12:52:28 2013
*
*/
#ifndef __KALMAN_DLQE2_TYPES_H__
#define __KALMAN_DLQE2_TYPES_H__
/* Type Definitions */
#endif
/* End of code generation (kalman_dlqe2_types.h) */

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