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px4-firmware
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Merge branch 'beta' into rtl_heading

This commit is contained in:
Anton Babushkin 2014-02-18 18:19:12 +04:00
parent 36bd7a797b 3508a42f6a
commit b28b0d0fce
45 changed files with 1767 additions and 925 deletions
Show Stats Download Patch File Download Diff File Expand all files Collapse all files

4
ROMFS/px4fmu_common/init.d/10015_tbs_discovery
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@ -2,7 +2,7 @@
#
# Team Blacksheep Discovery Quadcopter
#
# Anton Babushkin <anton.babushkin@me.com>, Simon Wilks <sjwilks@gmail.com>
# Anton Babushkin <anton.babushkin@me.com>, Simon Wilks <sjwilks@gmail.com>, Thomas Gubler <thomasgubler@gmail.com>
#
sh /etc/init.d/rc.mc_defaults
@ -15,7 +15,7 @@ then
param set MC_ROLLRATE_I 0.05
param set MC_ROLLRATE_D 0.0017
param set MC_PITCH_P 8.0
param set MC_PITCHRATE_P 0.14
param set MC_PITCHRATE_P 0.1
param set MC_PITCHRATE_I 0.1
param set MC_PITCHRATE_D 0.0025
param set MC_YAW_P 2.8

1
ROMFS/px4fmu_common/init.d/rc.fw_defaults
View File

@ -10,4 +10,5 @@ then
param set NAV_LAND_ALT 90
param set NAV_RTL_ALT 100
param set NAV_RTL_LAND_T -1
param set NAV_ACCEPT_RAD 50
fi

BIN
ROMFS/px4fmu_common/logging/conv.zip
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88
ROMFS/px4fmu_logging/init.d/rcS
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@ -1,88 +0,0 @@
#!nsh
#
# PX4FMU startup script for logging purposes
#
#
# Try to mount the microSD card.
#
echo "[init] looking for microSD..."
if mount -t vfat /dev/mmcsd0 /fs/microsd
then
echo "[init] card mounted at /fs/microsd"
# Start playing the startup tune
tone_alarm start
else
echo "[init] no microSD card found"
# Play SOS
tone_alarm error
fi
uorb start
#
# Start sensor drivers here.
#
ms5611 start
adc start
# mag might be external
if hmc5883 start
then
echo "using HMC5883"
fi
if mpu6000 start
then
echo "using MPU6000"
fi
if l3gd20 start
then
echo "using L3GD20(H)"
fi
if lsm303d start
then
set BOARD fmuv2
else
set BOARD fmuv1
fi
# Start airspeed sensors
if meas_airspeed start
then
echo "using MEAS airspeed sensor"
else
if ets_airspeed start
then
echo "using ETS airspeed sensor (bus 3)"
else
if ets_airspeed start -b 1
then
echo "Using ETS airspeed sensor (bus 1)"
fi
fi
fi
#
# Start the sensor collection task.
# IMPORTANT: this also loads param offsets
# ALWAYS start this task before the
# preflight_check.
#
if sensors start
then
echo "SENSORS STARTED"
fi
sdlog2 start -r 250 -e -b 16
if sercon
then
echo "[init] USB interface connected"
# Try to get an USB console
nshterm /dev/ttyACM0 &
fi

BIN
ROMFS/px4fmu_logging/logging/conv.zip
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1
Tools/px4params/.gitignore vendored
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@ -1,3 +1,4 @@
parameters.wiki
parameters.xml
parameters.wikirpc.xml
cookies.txt

62
Tools/px4params/dokuwikiout.py
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@ -1,62 +0,0 @@
import output
from xml.sax.saxutils import escape
class DokuWikiOutput(output.Output):
def Generate(self, groups):
pre_text = """<?xml version='1.0'?>
<methodCall>
<methodName>wiki.putPage</methodName>
<params>
<param>
<value>
<string>:firmware:parameters</string>
</value>
</param>
<param>
<value>
<string>"""
result = "====== Parameter Reference ======\nThis list is auto-generated every few minutes and contains the most recent parameter names and default values."
for group in groups:
result += "==== %s ====\n\n" % group.GetName()
result += "|< 100% 20% 20% 10% 10% 10% 30%>|\n"
result += "^ Name ^ Description ^ Min ^ Max ^ Default ^ Comment ^\n"
for param in group.GetParams():
code = param.GetFieldValue("code")
name = param.GetFieldValue("short_desc")
name = name.replace("\n", "")
result += "| %s | %s " % (code, name)
min_val = param.GetFieldValue("min")
if min_val is not None:
result += " | %s " % min_val
else:
result += " | "
max_val = param.GetFieldValue("max")
if max_val is not None:
result += " | %s " % max_val
else:
result += " | "
def_val = param.GetFieldValue("default")
if def_val is not None:
result += "| %s " % def_val
else:
result += " | "
long_desc = param.GetFieldValue("long_desc")
if long_desc is not None:
long_desc = long_desc.replace("\n", "")
result += "| %s " % long_desc
else:
result += " | "
result += " |\n"
result += "\n"
post_text = """</string>
</value>
</param>
<param>
<value>
<name>sum</name>
<string>Updated parameters automagically from code.</string>
</value>
</param>
</params>
</methodCall>"""
return pre_text + escape(result) + post_text

5
Tools/px4params/output.py
View File

@ -1,5 +0,0 @@
class Output(object):
def Save(self, groups, fn):
data = self.Generate(groups)
with open(fn, 'w') as f:
f.write(data)

12
Tools/px4params/dokuwikiout_listings.py → Tools/px4params/output_dokuwiki_listings.py
View File

@ -1,7 +1,7 @@
import output
import codecs
class DokuWikiOutput(output.Output):
def Generate(self, groups):
class DokuWikiListingsOutput():
def __init__(self, groups):
result = ""
for group in groups:
result += "==== %s ====\n\n" % group.GetName()
@ -24,4 +24,8 @@ class DokuWikiOutput(output.Output):
if def_val is not None:
result += "* Default value: %s\n" % def_val
result += "\n"
return result
self.output = result
def Save(self, filename):
with codecs.open(filename, 'w', 'utf-8') as f:
f.write(self.output)

76
Tools/px4params/output_dokuwiki_tables.py Normal file
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@ -0,0 +1,76 @@
from xml.sax.saxutils import escape
import codecs
class DokuWikiTablesOutput():
def __init__(self, groups):
result = "====== Parameter Reference ======\nThis list is auto-generated every few minutes and contains the most recent parameter names and default values.\n\n"
for group in groups:
result += "==== %s ====\n\n" % group.GetName()
result += "|< 100% 20% 20% 10% 10% 10% 30%>|\n"
result += "^ Name ^ Description ^ Min ^ Max ^ Default ^ Comment ^\n"
for param in group.GetParams():
code = param.GetFieldValue("code")
name = param.GetFieldValue("short_desc")
min_val = param.GetFieldValue("min")
max_val = param.GetFieldValue("max")
def_val = param.GetFieldValue("default")
long_desc = param.GetFieldValue("long_desc")
name = name.replace("\n", " ")
result += "| %s | %s |" % (code, name)
if min_val is not None:
result += " %s |" % min_val
else:
result += " |"
if max_val is not None:
result += " %s |" % max_val
else:
result += " |"
if def_val is not None:
result += " %s |" % def_val
else:
result += " |"
if long_desc is not None:
long_desc = long_desc.replace("\n", " ")
result += " %s |" % long_desc
else:
result += " |"
result += "\n"
result += "\n"
self.output = result;
def Save(self, filename):
with codecs.open(filename, 'w', 'utf-8') as f:
f.write(self.output)
def SaveRpc(self, filename):
with codecs.open(filename, 'w', 'utf-8') as f:
f.write("""<?xml version='1.0'?>
<methodCall>
<methodName>wiki.putPage</methodName>
<params>
<param>
<value>
<string>:firmware:parameters</string>
</value>
</param>
<param>
<value>
<string>""")
f.write(escape(self.output))
f.write("""</string>
</value>
</param>
<param>
<value>
<name>sum</name>
<string>Updated parameters automagically from code.</string>
</value>
</param>
</params>
</methodCall>""")

12
Tools/px4params/xmlout.py → Tools/px4params/output_xml.py
View File

@ -1,8 +1,8 @@
import output
from xml.dom.minidom import getDOMImplementation
import codecs
class XMLOutput(output.Output):
def Generate(self, groups):
class XMLOutput():
def __init__(self, groups):
impl = getDOMImplementation()
xml_document = impl.createDocument(None, "parameters", None)
xml_parameters = xml_document.documentElement
@ -19,4 +19,8 @@ class XMLOutput(output.Output):
xml_param.appendChild(xml_field)
xml_value = xml_document.createTextNode(value)
xml_field.appendChild(xml_value)
return xml_document.toprettyxml(indent=" ", newl="\n", encoding="utf-8")
self.xml_document = xml_document
def Save(self, filename):
with codecs.open(filename, 'w', 'utf-8') as f:
self.xml_document.writexml(f, indent=" ", addindent=" ", newl="\n")

26
Tools/px4params/px_process_params.py
View File

@ -40,22 +40,28 @@
#
import scanner
import parser
import xmlout
import dokuwikiout
import srcparser
import output_xml
import output_dokuwiki_tables
import output_dokuwiki_listings
# Initialize parser
prs = parser.Parser()
prs = srcparser.Parser()
# Scan directories, and parse the files
sc = scanner.Scanner()
sc.ScanDir("../../src", prs)
output = prs.GetParamGroups()
groups = prs.GetParamGroups()
# Output into XML
out = xmlout.XMLOutput()
out.Save(output, "parameters.xml")
out = output_xml.XMLOutput(groups)
out.Save("parameters.xml")
# Output into DokuWiki
out = dokuwikiout.DokuWikiOutput()
out.Save(output, "parameters.wiki")
# Output to DokuWiki listings
#out = output_dokuwiki_listings.DokuWikiListingsOutput(groups)
#out.Save("parameters.wiki")
# Output to DokuWiki tables
out = output_dokuwiki_tables.DokuWikiTablesOutput(groups)
out.Save("parameters.wiki")
out.SaveRpc("parameters.wikirpc.xml")

3
Tools/px4params/scanner.py
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@ -1,5 +1,6 @@
import os
import re
import codecs
class Scanner(object):
"""
@ -29,6 +30,6 @@ class Scanner(object):
Scans provided file and passes its contents to the parser using
parser.Parse method.
"""
with open(path, 'r') as f:
with codecs.open(path, 'r', 'utf-8') as f:
contents = f.read()
parser.Parse(contents)

20
Tools/px4params/parser.py → Tools/px4params/srcparser.py
View File

@ -28,8 +28,7 @@ class ParameterGroup(object):
state of the parser.
"""
return sorted(self.params,
cmp=lambda x, y: cmp(x.GetFieldValue("code"),
y.GetFieldValue("code")))
key=lambda x: x.GetFieldValue("code"))
class Parameter(object):
"""
@ -61,9 +60,10 @@ class Parameter(object):
"""
Return list of existing field codes in convenient order
"""
return sorted(self.fields.keys(),
cmp=lambda x, y: cmp(self.priority.get(y, 0),
self.priority.get(x, 0)) or cmp(x, y))
keys = self.fields.keys()
keys = sorted(keys)
keys = sorted(keys, key=lambda x: self.priority.get(x, 0), reverse=True)
return keys
def GetFieldValue(self, code):
"""
@ -197,7 +197,7 @@ class Parser(object):
if tag == "group":
group = tags[tag]
elif tag not in self.valid_tags:
sys.stderr.write("Skipping invalid"
sys.stderr.write("Skipping invalid "
"documentation tag: '%s'\n" % tag)
else:
param.SetField(tag, tags[tag])
@ -214,7 +214,7 @@ class Parser(object):
object. Note that returned object is not a copy. Modifications affect
state of the parser.
"""
return sorted(self.param_groups.values(),
cmp=lambda x, y: cmp(self.priority.get(y.GetName(), 0),
self.priority.get(x.GetName(), 0)) or cmp(x.GetName(),
y.GetName()))
groups = self.param_groups.values()
groups = sorted(groups, key=lambda x: x.GetName())
groups = sorted(groups, key=lambda x: self.priority.get(x.GetName(), 0), reverse=True)
return groups

2
Tools/px4params/xmlrpc.sh
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@ -2,4 +2,4 @@ python px_process_params.py
rm cookies.txt
curl --cookie cookies.txt --cookie-jar cookies.txt --user-agent Mozilla/4.0 --data "u=$XMLRPCUSER&p=$XMLRPCPASS" https://pixhawk.org/start?do=login
curl -k --cookie cookies.txt -H "Content-Type: application/xml" -X POST --data-binary @parameters.wiki "https://pixhawk.org/lib/exe/xmlrpc.php"
curl -k --cookie cookies.txt -H "Content-Type: application/xml" -X POST --data-binary @parameters.wikirpc.xml "https://pixhawk.org/lib/exe/xmlrpc.php"

0
Tools/README.txt → Tools/sdlog2/README.txt
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1070
Tools/logconv.m → Tools/sdlog2/logconv.m
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File diff suppressed because it is too large Load Diff

0
Tools/sdlog2_dump.py → Tools/sdlog2/sdlog2_dump.py
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6
nuttx-configs/px4fmu-v2/include/board.h
View File

@ -141,9 +141,9 @@
#define STM32_APB2_TIM1_CLKIN (2*STM32_PCLK2_FREQUENCY)
#define STM32_APB2_TIM8_CLKIN (2*STM32_PCLK2_FREQUENCY)
#define STM32_APB2_TIM9_CLKIN (2*STM32_PCLK1_FREQUENCY)
#define STM32_APB2_TIM10_CLKIN (2*STM32_PCLK1_FREQUENCY)
#define STM32_APB2_TIM11_CLKIN (2*STM32_PCLK1_FREQUENCY)
#define STM32_APB2_TIM9_CLKIN (2*STM32_PCLK2_FREQUENCY)
#define STM32_APB2_TIM10_CLKIN (2*STM32_PCLK2_FREQUENCY)
#define STM32_APB2_TIM11_CLKIN (2*STM32_PCLK2_FREQUENCY)
/* Timer Frequencies, if APBx is set to 1, frequency is same to APBx
* otherwise frequency is 2xAPBx.

4
src/drivers/airspeed/airspeed.cpp
View File

@ -76,8 +76,8 @@
#include <drivers/airspeed/airspeed.h>
Airspeed::Airspeed(int bus, int address, unsigned conversion_interval) :
I2C("Airspeed", AIRSPEED_DEVICE_PATH, bus, address, 100000),
Airspeed::Airspeed(int bus, int address, unsigned conversion_interval, const char* path) :
I2C("Airspeed", path, bus, address, 100000),
_reports(nullptr),
_buffer_overflows(perf_alloc(PC_COUNT, "airspeed_buffer_overflows")),
_max_differential_pressure_pa(0),

2
src/drivers/airspeed/airspeed.h
View File

@ -90,7 +90,7 @@ static const int ERROR = -1;
class __EXPORT Airspeed : public device::I2C
{
public:
Airspeed(int bus, int address, unsigned conversion_interval);
Airspeed(int bus, int address, unsigned conversion_interval, const char* path);
virtual ~Airspeed();
virtual int init();

7
src/drivers/ets_airspeed/ets_airspeed.cpp
View File

@ -77,6 +77,7 @@
/* I2C bus address */
#define I2C_ADDRESS 0x75 /* 7-bit address. 8-bit address is 0xEA */
#define ETS_PATH "/dev/ets_airspeed"
/* Register address */
#define READ_CMD 0x07 /* Read the data */
@ -93,7 +94,7 @@
class ETSAirspeed : public Airspeed
{
public:
ETSAirspeed(int bus, int address = I2C_ADDRESS);
ETSAirspeed(int bus, int address = I2C_ADDRESS, const char* path = ETS_PATH);
protected:
@ -112,8 +113,8 @@ protected:
*/
extern "C" __EXPORT int ets_airspeed_main(int argc, char *argv[]);
ETSAirspeed::ETSAirspeed(int bus, int address) : Airspeed(bus, address,
CONVERSION_INTERVAL)
ETSAirspeed::ETSAirspeed(int bus, int address, const char* path) : Airspeed(bus, address,
CONVERSION_INTERVAL, path)
{
}

17
src/drivers/meas_airspeed/meas_airspeed.cpp
View File

@ -50,6 +50,7 @@
* - Interfacing to MEAS Digital Pressure Modules (http://www.meas-spec.com/downloads/Interfacing_to_MEAS_Digital_Pressure_Modules.pdf)
*/
#include <nuttx/config.h>
#include <drivers/device/i2c.h>
@ -89,8 +90,10 @@
/* I2C bus address is 1010001x */
#define I2C_ADDRESS_MS4525DO 0x28 //0x51 /* 7-bit address. */
#define PATH_MS4525 "/dev/ms4525"
/* The MS5525DSO address is 111011Cx, where C is the complementary value of the pin CSB */
#define I2C_ADDRESS_MS5525DSO 0x77 //0x77/* 7-bit address, addr. pin pulled low */
#define PATH_MS5525 "/dev/ms5525"
/* Register address */
#define ADDR_READ_MR 0x00 /* write to this address to start conversion */
@ -101,7 +104,7 @@
class MEASAirspeed : public Airspeed
{
public:
MEASAirspeed(int bus, int address = I2C_ADDRESS_MS4525DO);
MEASAirspeed(int bus, int address = I2C_ADDRESS_MS4525DO, const char* path = PATH_MS4525);
protected:
@ -120,8 +123,8 @@ protected:
*/
extern "C" __EXPORT int meas_airspeed_main(int argc, char *argv[]);
MEASAirspeed::MEASAirspeed(int bus, int address) : Airspeed(bus, address,
CONVERSION_INTERVAL)
MEASAirspeed::MEASAirspeed(int bus, int address, const char* path) : Airspeed(bus, address,
CONVERSION_INTERVAL, path)
{
}
@ -304,7 +307,7 @@ start(int i2c_bus)
errx(1, "already started");
/* create the driver, try the MS4525DO first */
g_dev = new MEASAirspeed(i2c_bus, I2C_ADDRESS_MS4525DO);
g_dev = new MEASAirspeed(i2c_bus, I2C_ADDRESS_MS4525DO, PATH_MS4525);
/* check if the MS4525DO was instantiated */
if (g_dev == nullptr)
@ -313,7 +316,7 @@ start(int i2c_bus)
/* try the MS5525DSO next if init fails */
if (OK != g_dev->Airspeed::init()) {
delete g_dev;
g_dev = new MEASAirspeed(i2c_bus, I2C_ADDRESS_MS5525DSO);
g_dev = new MEASAirspeed(i2c_bus, I2C_ADDRESS_MS5525DSO, PATH_MS5525);
/* check if the MS5525DSO was instantiated */
if (g_dev == nullptr)
@ -386,7 +389,7 @@ test()
err(1, "immediate read failed");
warnx("single read");
warnx("diff pressure: %d pa", (double)report.differential_pressure_pa);
warnx("diff pressure: %8.4f pa", (double)report.differential_pressure_pa);
/* start the sensor polling at 2Hz */
if (OK != ioctl(fd, SENSORIOCSPOLLRATE, 2))
@ -411,7 +414,7 @@ test()
err(1, "periodic read failed");
warnx("periodic read %u", i);
warnx("diff pressure: %d pa", report.differential_pressure_pa);
warnx("diff pressure: %8.4f pa", (double)report.differential_pressure_pa);
warnx("temperature: %d C (0x%02x)", (int)report.temperature, (unsigned) report.temperature);
}

2
src/drivers/mkblctrl/mkblctrl.cpp
View File

@ -705,7 +705,7 @@ MK::mk_check_for_blctrl(unsigned int count, bool showOutput, bool initI2C)
Motor[i].State |= MOTOR_STATE_PRESENT_MASK; // set present bit;
foundMotorCount++;
if (Motor[i].MaxPWM == 250) {
if ((Motor[i].MaxPWM & 252) == 248) {
Motor[i].Version = BLCTRL_NEW;
} else {

1
src/drivers/mpu6000/mpu6000.cpp
View File

@ -1353,6 +1353,7 @@ MPU6000::print_info()
MPU6000_gyro::MPU6000_gyro(MPU6000 *parent) :
CDev("MPU6000_gyro", MPU_DEVICE_PATH_GYRO),
_parent(parent),
_gyro_topic(-1),
_gyro_class_instance(-1)
{
}

48
src/lib/launchdetection/launchdetection_params.c
View File

@ -45,28 +45,46 @@
#include <systemlib/param/param.h>
/*
* Launch detection parameters, accessible via MAVLink
* Catapult launch detection parameters, accessible via MAVLink
*
*/
/* Catapult Launch detection */
// @DisplayName Switch to enable launchdetection
// @Description if set to 1 launchdetection is enabled
// @Range 0 or 1
/**
* Enable launch detection.
*
* @min 0
* @max 1
* @group Launch detection
*/
PARAM_DEFINE_INT32(LAUN_ALL_ON, 0);
// @DisplayName Catapult Accelerometer Threshold
// @Description LAUN_CAT_A * LAUN_CAT_T serves as threshold to trigger launch detection
// @Range > 0
/**
* Catapult accelerometer theshold.
*
* LAUN_CAT_A * LAUN_CAT_T serves as threshold to trigger launch detection.
*
* @min 0
* @group Launch detection
*/
PARAM_DEFINE_FLOAT(LAUN_CAT_A, 30.0f);
// @DisplayName Catapult Time Threshold
// @Description LAUN_CAT_A * LAUN_CAT_T serves as threshold to trigger launch detection
// @Range > 0, in seconds
/**
* Catapult time theshold.
*
* LAUN_CAT_A * LAUN_CAT_T serves as threshold to trigger launch detection.
*
* @min 0
* @group Launch detection
*/
PARAM_DEFINE_FLOAT(LAUN_CAT_T, 0.05f);
// @DisplayName Throttle setting while detecting the launch
// @Description The throttle is set to this value while the system is waiting for the takeoff
// @Range 0 to 1
/**
* Throttle setting while detecting launch.
*
* The throttle is set to this value while the system is waiting for the take-off.
*
* @min 0
* @max 1
* @group Launch detection
*/
PARAM_DEFINE_FLOAT(LAUN_THR_PRE, 0.0f);

20
src/modules/commander/commander.cpp
View File

@ -152,6 +152,7 @@ static uint64_t last_print_mode_reject_time = 0;
static bool on_usb_power = false;
static float takeoff_alt = 5.0f;
static int parachute_enabled = 0;
static struct vehicle_status_s status;
static struct actuator_armed_s armed;
@ -429,7 +430,7 @@ bool handle_command(struct vehicle_status_s *status, const struct safety_s *safe
arming_res = TRANSITION_NOT_CHANGED;
if (base_mode & MAV_MODE_FLAG_SAFETY_ARMED) {
if ((safety->safety_switch_available && !safety->safety_off) && status->hil_state == HIL_STATE_OFF) {
if (safety->safety_switch_available && !safety->safety_off && status->hil_state == HIL_STATE_OFF) {
print_reject_arm("NOT ARMING: Press safety switch first.");
arming_res = TRANSITION_DENIED;
@ -515,7 +516,7 @@ bool handle_command(struct vehicle_status_s *status, const struct safety_s *safe
transition_result_t arming_res = TRANSITION_NOT_CHANGED;
if (!armed->armed && ((int)(cmd->param1 + 0.5f)) == 1) {
if (safety->safety_switch_available && !safety->safety_off) {
if (safety->safety_switch_available && !safety->safety_off && status->hil_state == HIL_STATE_OFF) {
print_reject_arm("NOT ARMING: Press safety switch first.");
arming_res = TRANSITION_DENIED;
@ -563,7 +564,9 @@ bool handle_command(struct vehicle_status_s *status, const struct safety_s *safe
/* Flight termination */
case VEHICLE_CMD_DO_SET_SERVO: { //xxx: needs its own mavlink command
if (armed->armed && cmd->param3 > 0.5) { //xxx: for safety only for now, param3 is unused by VEHICLE_CMD_DO_SET_SERVO
//XXX: to enable the parachute, a param needs to be set
//xxx: for safety only for now, param3 is unused by VEHICLE_CMD_DO_SET_SERVO
if (armed->armed && cmd->param3 > 0.5 && parachute_enabled) {
transition_result_t failsafe_res = failsafe_state_transition(status, FAILSAFE_STATE_TERMINATION);
result = VEHICLE_CMD_RESULT_ACCEPTED;
ret = true;
@ -615,6 +618,7 @@ int commander_thread_main(int argc, char *argv[])
param_t _param_system_id = param_find("MAV_SYS_ID");
param_t _param_component_id = param_find("MAV_COMP_ID");
param_t _param_takeoff_alt = param_find("NAV_TAKEOFF_ALT");
param_t _param_enable_parachute = param_find("NAV_PARACHUTE_EN");
/* welcome user */
warnx("starting");
@ -860,10 +864,10 @@ int commander_thread_main(int argc, char *argv[])
/* re-check RC calibration */
rc_calibration_ok = (OK == rc_calibration_check(mavlink_fd));
/* navigation parameters */
param_get(_param_takeoff_alt, &takeoff_alt);
}
/* navigation parameters */
param_get(_param_takeoff_alt, &takeoff_alt);
param_get(_param_enable_parachute, &parachute_enabled);
}
orb_check(sp_man_sub, &updated);
@ -1152,7 +1156,7 @@ int commander_thread_main(int argc, char *argv[])
if (status.arming_state == ARMING_STATE_STANDBY &&
sp_man.yaw > STICK_ON_OFF_LIMIT && sp_man.throttle < STICK_THRUST_RANGE * 0.1f) {
if (stick_on_counter > STICK_ON_OFF_COUNTER_LIMIT) {
if (safety.safety_switch_available && !safety.safety_off) {
if (safety.safety_switch_available && !safety.safety_off && status.hil_state == HIL_STATE_OFF) {
print_reject_arm("NOT ARMING: Press safety switch first.");
} else if (status.main_state != MAIN_STATE_MANUAL) {
@ -1251,7 +1255,7 @@ int commander_thread_main(int argc, char *argv[])
// TODO remove this hack
/* flight termination in manual mode if assisted switch is on easy position */
if (!status.is_rotary_wing && armed.armed && status.main_state == MAIN_STATE_MANUAL && sp_man.assisted_switch > STICK_ON_OFF_LIMIT) {
if (!status.is_rotary_wing && parachute_enabled && armed.armed && status.main_state == MAIN_STATE_MANUAL && sp_man.assisted_switch > STICK_ON_OFF_LIMIT) {
if (TRANSITION_CHANGED == failsafe_state_transition(&status, FAILSAFE_STATE_TERMINATION)) {
tune_positive();
}

32
src/modules/commander/commander_params.c
View File

@ -48,7 +48,39 @@
PARAM_DEFINE_FLOAT(TRIM_ROLL, 0.0f);
PARAM_DEFINE_FLOAT(TRIM_PITCH, 0.0f);
PARAM_DEFINE_FLOAT(TRIM_YAW, 0.0f);
/**
* Empty cell voltage.
*
* Defines the voltage where a single cell of the battery is considered empty.
*
* @group Battery Calibration
*/
PARAM_DEFINE_FLOAT(BAT_V_EMPTY, 3.4f);
/**
* Full cell voltage.
*
* Defines the voltage where a single cell of the battery is considered full.
*
* @group Battery Calibration
*/
PARAM_DEFINE_FLOAT(BAT_V_FULL, 3.9f);
/**
* Number of cells.
*
* Defines the number of cells the attached battery consists of.
*
* @group Battery Calibration
*/
PARAM_DEFINE_INT32(BAT_N_CELLS, 3);
/**
* Battery capacity.
*
* Defines the capacity of the attached battery.
*
* @group Battery Calibration
*/
PARAM_DEFINE_FLOAT(BAT_CAPACITY, -1.0f);

280
src/modules/fw_pos_control_l1/fw_pos_control_l1_params.c
View File

@ -40,12 +40,10 @@
*/
#include <nuttx/config.h>
#include <systemlib/param/param.h>
/*
* Controller parameters, accessible via MAVLink
*
*/
/**
@ -119,58 +117,268 @@ PARAM_DEFINE_FLOAT(FW_P_LIM_MIN, -45.0f);
*/
PARAM_DEFINE_FLOAT(FW_P_LIM_MAX, 45.0f);
/**
* Controller roll limit
*
* The maximum roll the controller will output.
*
* @unit degrees
* @min 0.0
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_R_LIM, 45.0f);
PARAM_DEFINE_FLOAT(FW_THR_MIN, 0.0f);
/**
* Throttle limit max
*
* This is the maximum throttle % that can be used by the controller.
* For overpowered aircraft, this should be reduced to a value that
* provides sufficient thrust to climb at the maximum pitch angle PTCH_MAX.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_THR_MAX, 1.0f);
/**
* Throttle limit min
*
* This is the minimum throttle % that can be used by the controller.
* For electric aircraft this will normally be set to zero, but can be set
* to a small non-zero value if a folding prop is fitted to prevent the
* prop from folding and unfolding repeatedly in-flight or to provide
* some aerodynamic drag from a turning prop to improve the descent rate.
*
* For aircraft with internal combustion engine this parameter should be set
* for desired idle rpm.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_THR_MIN, 0.0f);
/**
* Throttle limit value before flare
*
* This throttle value will be set as throttle limit at FW_LND_TLALT,
* before arcraft will flare.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_THR_LND_MAX, 1.0f);
/**
* Maximum climb rate
*
* This is the best climb rate that the aircraft can achieve with
* the throttle set to THR_MAX and the airspeed set to the
* default value. For electric aircraft make sure this number can be
* achieved towards the end of flight when the battery voltage has reduced.
* The setting of this parameter can be checked by commanding a positive
* altitude change of 100m in loiter, RTL or guided mode. If the throttle
* required to climb is close to THR_MAX and the aircraft is maintaining
* airspeed, then this parameter is set correctly. If the airspeed starts
* to reduce, then the parameter is set to high, and if the throttle
* demand required to climb and maintain speed is noticeably less than
* FW_THR_MAX, then either FW_T_CLMB_MAX should be increased or
* FW_THR_MAX reduced.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_CLMB_MAX, 5.0f);
/**
* Minimum descent rate
*
* This is the sink rate of the aircraft with the throttle
* set to THR_MIN and flown at the same airspeed as used
* to measure FW_T_CLMB_MAX.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_SINK_MIN, 2.0f);
PARAM_DEFINE_FLOAT(FW_T_TIME_CONST, 5.0f);
PARAM_DEFINE_FLOAT(FW_T_THR_DAMP, 0.5f);
PARAM_DEFINE_FLOAT(FW_T_INTEG_GAIN, 0.1f);
PARAM_DEFINE_FLOAT(FW_T_VERT_ACC, 7.0f);
PARAM_DEFINE_FLOAT(FW_T_HGT_OMEGA, 3.0f);
PARAM_DEFINE_FLOAT(FW_T_SPD_OMEGA, 2.0f);
PARAM_DEFINE_FLOAT(FW_T_RLL2THR, 10.0f);
PARAM_DEFINE_FLOAT(FW_T_SPDWEIGHT, 1.0f);
PARAM_DEFINE_FLOAT(FW_T_PTCH_DAMP, 0.0f);
/**
* Maximum descent rate
*
* This sets the maximum descent rate that the controller will use.
* If this value is too large, the aircraft can over-speed on descent.
* This should be set to a value that can be achieved without
* exceeding the lower pitch angle limit and without over-speeding
* the aircraft.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_SINK_MAX, 5.0f);
/**
* TECS time constant
*
* This is the time constant of the TECS control algorithm (in seconds).
* Smaller values make it faster to respond, larger values make it slower
* to respond.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_TIME_CONST, 5.0f);
/**
* Throttle damping factor
*
* This is the damping gain for the throttle demand loop.
* Increase to add damping to correct for oscillations in speed and height.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_THR_DAMP, 0.5f);
/**
* Integrator gain
*
* This is the integrator gain on the control loop.
* Increasing this gain increases the speed at which speed
* and height offsets are trimmed out, but reduces damping and
* increases overshoot.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_INTEG_GAIN, 0.1f);
/**
* Maximum vertical acceleration
*
* This is the maximum vertical acceleration (in metres/second^2)
* either up or down that the controller will use to correct speed
* or height errors. The default value of 7 m/s/s (equivalent to +- 0.7 g)
* allows for reasonably aggressive pitch changes if required to recover
* from under-speed conditions.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_VERT_ACC, 7.0f);
/**
* Complementary filter "omega" parameter for height
*
* This is the cross-over frequency (in radians/second) of the complementary
* filter used to fuse vertical acceleration and barometric height to obtain
* an estimate of height rate and height. Increasing this frequency weights
* the solution more towards use of the barometer, whilst reducing it weights
* the solution more towards use of the accelerometer data.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_HGT_OMEGA, 3.0f);
/**
* Complementary filter "omega" parameter for speed
*
* This is the cross-over frequency (in radians/second) of the complementary
* filter used to fuse longitudinal acceleration and airspeed to obtain an
* improved airspeed estimate. Increasing this frequency weights the solution
* more towards use of the arispeed sensor, whilst reducing it weights the
* solution more towards use of the accelerometer data.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_SPD_OMEGA, 2.0f);
/**
* Roll -> Throttle feedforward
*
* Increasing this gain turn increases the amount of throttle that will
* be used to compensate for the additional drag created by turning.
* Ideally this should be set to approximately 10 x the extra sink rate
* in m/s created by a 45 degree bank turn. Increase this gain if
* the aircraft initially loses energy in turns and reduce if the
* aircraft initially gains energy in turns. Efficient high aspect-ratio
* aircraft (eg powered sailplanes) can use a lower value, whereas
* inefficient low aspect-ratio models (eg delta wings) can use a higher value.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_RLL2THR, 10.0f);
/**
* Speed <--> Altitude priority
*
* This parameter adjusts the amount of weighting that the pitch control
* applies to speed vs height errors. Setting it to 0.0 will cause the
* pitch control to control height and ignore speed errors. This will
* normally improve height accuracy but give larger airspeed errors.
* Setting it to 2.0 will cause the pitch control loop to control speed
* and ignore height errors. This will normally reduce airspeed errors,
* but give larger height errors. The default value of 1.0 allows the pitch
* control to simultaneously control height and speed.
* Note to Glider Pilots - set this parameter to 2.0 (The glider will
* adjust its pitch angle to maintain airspeed, ignoring changes in height).
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_SPDWEIGHT, 1.0f);
/**
* Pitch damping factor
*
* This is the damping gain for the pitch demand loop. Increase to add
* damping to correct for oscillations in height. The default value of 0.0
* will work well provided the pitch to servo controller has been tuned
* properly.
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_PTCH_DAMP, 0.0f);
/**
* Height rate P factor
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_HRATE_P, 0.05f);
/**
* Speed rate P factor
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_T_SRATE_P, 0.05f);
/**
* Landing slope angle
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_LND_ANG, 5.0f);
/**
* Landing slope length
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_LND_SLLR, 0.9f);
/**
*
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_LND_HVIRT, 10.0f);
/**
* Landing flare altitude (relative)
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_LND_FLALT, 15.0f);
/**
* Landing throttle limit altitude (relative)
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_LND_TLALT, 5.0f);
/**
* Landing heading hold horizontal distance
*
* @group L1 Control
*/
PARAM_DEFINE_FLOAT(FW_LND_HHDIST, 15.0f);

12
src/modules/mavlink/mavlink.c
View File

@ -76,8 +76,20 @@
#include <uORB/topics/mission_result.h>
/* define MAVLink specific parameters */
/**
* MAVLink system ID
* @group MAVLink
*/
PARAM_DEFINE_INT32(MAV_SYS_ID, 1);
/**
* MAVLink component ID
* @group MAVLink
*/
PARAM_DEFINE_INT32(MAV_COMP_ID, 50);
/**
* MAVLink type
* @group MAVLink
*/
PARAM_DEFINE_INT32(MAV_TYPE, MAV_TYPE_FIXED_WING);
__EXPORT int mavlink_main(int argc, char *argv[]);

2
src/modules/mavlink/mavlink_receiver.cpp
View File

@ -351,7 +351,7 @@ handle_message(mavlink_message_t *msg)
tstatus.rxerrors = rstatus.rxerrors;
tstatus.fixed = rstatus.fixed;
if (telemetry_status_pub == 0) {
if (telemetry_status_pub <= 0) {
telemetry_status_pub = orb_advertise(ORB_ID(telemetry_status), &tstatus);
} else {

61
src/modules/mc_att_control/mc_att_control_main.cpp
View File

@ -53,11 +53,9 @@
#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>
@ -71,7 +69,6 @@
#include <uORB/topics/parameter_update.h>
#include <systemlib/param/param.h>
#include <systemlib/err.h>
#include <systemlib/pid/pid.h>
#include <systemlib/perf_counter.h>
#include <systemlib/systemlib.h>
#include <mathlib/mathlib.h>
@ -84,9 +81,9 @@
*/
extern "C" __EXPORT int mc_att_control_main(int argc, char *argv[]);
#define MIN_TAKEOFF_THROTTLE 0.3f
#define YAW_DEADZONE 0.05f
#define RATES_I_LIMIT 0.5f
#define MIN_TAKEOFF_THRUST 0.2f
#define RATES_I_LIMIT 0.3f
class MulticopterAttitudeControl
{
@ -135,15 +132,13 @@ private:
perf_counter_t _loop_perf; /**< loop performance counter */
math::Matrix<3, 3> _R_sp; /**< attitude setpoint rotation matrix */
math::Matrix<3, 3> _R; /**< rotation matrix for current state */
math::Vector<3> _rates_prev; /**< angular rates on previous step */
math::Vector<3> _rates_sp; /**< angular rates setpoint */
math::Vector<3> _rates_int; /**< angular rates integral error */
float _thrust_sp; /**< thrust setpoint */
math::Vector<3> _att_control; /**< attitude control vector */
math::Matrix<3, 3> I; /**< identity matrix */
math::Matrix<3, 3> _I; /**< identity matrix */
bool _reset_yaw_sp; /**< reset yaw setpoint flag */
@ -262,7 +257,7 @@ MulticopterAttitudeControl::MulticopterAttitudeControl() :
_actuators_0_pub(-1),
/* performance counters */
_loop_perf(perf_alloc(PC_ELAPSED, "fw att control"))
_loop_perf(perf_alloc(PC_ELAPSED, "mc_att_control"))
{
memset(&_v_att, 0, sizeof(_v_att));
@ -276,15 +271,13 @@ MulticopterAttitudeControl::MulticopterAttitudeControl() :
_params.rate_i.zero();
_params.rate_d.zero();
_R_sp.identity();
_R.identity();
_rates_prev.zero();
_rates_sp.zero();
_rates_int.zero();
_thrust_sp = 0.0f;
_att_control.zero();
I.identity();
_I.identity();
_params_handles.roll_p = param_find("MC_ROLL_P");
_params_handles.roll_rate_p = param_find("MC_ROLLRATE_P");
@ -535,16 +528,18 @@ MulticopterAttitudeControl::control_attitude(float dt)
_thrust_sp = _v_att_sp.thrust;
/* construct attitude setpoint rotation matrix */
math::Matrix<3, 3> R_sp;
if (_v_att_sp.R_valid) {
/* rotation matrix in _att_sp is valid, use it */
_R_sp.set(&_v_att_sp.R_body[0][0]);
R_sp.set(&_v_att_sp.R_body[0][0]);
} else {
/* rotation matrix in _att_sp is not valid, use euler angles instead */
_R_sp.from_euler(_v_att_sp.roll_body, _v_att_sp.pitch_body, _v_att_sp.yaw_body);
R_sp.from_euler(_v_att_sp.roll_body, _v_att_sp.pitch_body, _v_att_sp.yaw_body);
/* copy rotation matrix back to setpoint struct */
memcpy(&_v_att_sp.R_body[0][0], &_R_sp.data[0][0], sizeof(_v_att_sp.R_body));
memcpy(&_v_att_sp.R_body[0][0], &R_sp.data[0][0], sizeof(_v_att_sp.R_body));
_v_att_sp.R_valid = true;
}
@ -561,23 +556,24 @@ MulticopterAttitudeControl::control_attitude(float dt)
}
/* rotation matrix for current state */
_R.set(_v_att.R);
math::Matrix<3, 3> R;
R.set(_v_att.R);
/* all input data is ready, run controller itself */
/* try to move thrust vector shortest way, because yaw response is slower than roll/pitch */
math::Vector<3> R_z(_R(0, 2), _R(1, 2), _R(2, 2));
math::Vector<3> R_sp_z(_R_sp(0, 2), _R_sp(1, 2), _R_sp(2, 2));
math::Vector<3> R_z(R(0, 2), R(1, 2), R(2, 2));
math::Vector<3> R_sp_z(R_sp(0, 2), R_sp(1, 2), R_sp(2, 2));
/* axis and sin(angle) of desired rotation */
math::Vector<3> e_R = _R.transposed() * (R_z % R_sp_z);
math::Vector<3> e_R = R.transposed() * (R_z % R_sp_z);
/* calculate angle error */
float e_R_z_sin = e_R.length();
float e_R_z_cos = R_z * R_sp_z;
/* calculate weight for yaw control */
float yaw_w = _R_sp(2, 2) * _R_sp(2, 2);
float yaw_w = R_sp(2, 2) * R_sp(2, 2);
/* calculate rotation matrix after roll/pitch only rotation */
math::Matrix<3, 3> R_rp;
@ -600,15 +596,15 @@ MulticopterAttitudeControl::control_attitude(float dt)
e_R_cp(2, 1) = e_R_z_axis(0);
/* rotation matrix for roll/pitch only rotation */
R_rp = _R * (I + e_R_cp * e_R_z_sin + e_R_cp * e_R_cp * (1.0f - e_R_z_cos));
R_rp = R * (_I + e_R_cp * e_R_z_sin + e_R_cp * e_R_cp * (1.0f - e_R_z_cos));
} else {
/* zero roll/pitch rotation */
R_rp = _R;
R_rp = R;
}
/* R_rp and _R_sp has the same Z axis, calculate yaw error */
math::Vector<3> R_sp_x(_R_sp(0, 0), _R_sp(1, 0), _R_sp(2, 0));
/* R_rp and R_sp has the same Z axis, calculate yaw error */
math::Vector<3> R_sp_x(R_sp(0, 0), R_sp(1, 0), R_sp(2, 0));
math::Vector<3> R_rp_x(R_rp(0, 0), R_rp(1, 0), R_rp(2, 0));
e_R(2) = atan2f((R_rp_x % R_sp_x) * R_sp_z, R_rp_x * R_sp_x) * yaw_w;
@ -616,7 +612,7 @@ MulticopterAttitudeControl::control_attitude(float dt)
/* for large thrust vector rotations use another rotation method:
* calculate angle and axis for R -> R_sp rotation directly */
math::Quaternion q;
q.from_dcm(_R.transposed() * _R_sp);
q.from_dcm(R.transposed() * R_sp);
math::Vector<3> e_R_d = q.imag();
e_R_d.normalize();
e_R_d *= 2.0f * atan2f(e_R_d.length(), q(0));
@ -658,7 +654,7 @@ MulticopterAttitudeControl::control_attitude_rates(float dt)
_rates_prev = rates;
/* update integral only if not saturated on low limit */
if (_thrust_sp > 0.1f) {
if (_thrust_sp > MIN_TAKEOFF_THRUST) {
for (int i = 0; i < 3; i++) {
if (fabsf(_att_control(i)) < _thrust_sp) {
float rate_i = _rates_int(i) + _params.rate_i(i) * rates_err(i) * dt;
@ -695,9 +691,6 @@ MulticopterAttitudeControl::task_main()
_manual_control_sp_sub = orb_subscribe(ORB_ID(manual_control_setpoint));
_armed_sub = orb_subscribe(ORB_ID(actuator_armed));
/* rate limit attitude updates to 200Hz, failsafe against spam, normally runs at the same rate as attitude estimator */
orb_set_interval(_v_att_sub, 5);
/* initialize parameters cache */
parameters_update();
@ -767,10 +760,12 @@ MulticopterAttitudeControl::task_main()
}
} else {
/* attitude controller disabled */
// TODO poll 'attitude_rates_setpoint' topic
_rates_sp.zero();
_thrust_sp = 0.0f;
/* attitude controller disabled, poll rates setpoint topic */
vehicle_rates_setpoint_poll();
_rates_sp(0) = _v_rates_sp.roll;
_rates_sp(1) = _v_rates_sp.pitch;
_rates_sp(2) = _v_rates_sp.yaw;
_thrust_sp = _v_rates_sp.thrust;
}
if (_v_control_mode.flag_control_rates_enabled) {

119
src/modules/mc_att_control/mc_att_control_params.c
View File

@ -41,16 +41,135 @@
#include <systemlib/param/param.h>
/**
* Roll P gain
*
* Roll proportional gain, i.e. desired angular speed in rad/s for error 1 rad.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_ROLL_P, 6.0f);
/**
* Roll rate P gain
*
* Roll rate proportional gain, i.e. control output for angular speed error 1 rad/s.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_ROLLRATE_P, 0.1f);
/**
* Roll rate I gain
*
* Roll rate integral gain. Can be set to compensate static thrust difference or gravity center offset.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_ROLLRATE_I, 0.0f);
/**
* Roll rate D gain
*
* Roll rate differential gain. Small values help reduce fast oscillations. If value is too big oscillations will appear again.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_ROLLRATE_D, 0.002f);
/**
* Pitch P gain
*
* Pitch proportional gain, i.e. desired angular speed in rad/s for error 1 rad.
*
* @unit 1/s
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_PITCH_P, 6.0f);
/**
* Pitch rate P gain
*
* Pitch rate proportional gain, i.e. control output for angular speed error 1 rad/s.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_PITCHRATE_P, 0.1f);
/**
* Pitch rate I gain
*
* Pitch rate integral gain. Can be set to compensate static thrust difference or gravity center offset.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_PITCHRATE_I, 0.0f);
/**
* Pitch rate D gain
*
* Pitch rate differential gain. Small values help reduce fast oscillations. If value is too big oscillations will appear again.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_PITCHRATE_D, 0.002f);
/**
* Yaw P gain
*
* Yaw proportional gain, i.e. desired angular speed in rad/s for error 1 rad.
*
* @unit 1/s
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_YAW_P, 2.0f);
/**
* Yaw rate P gain
*
* Yaw rate proportional gain, i.e. control output for angular speed error 1 rad/s.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_YAWRATE_P, 0.3f);
/**
* Yaw rate I gain
*
* Yaw rate integral gain. Can be set to compensate static thrust difference or gravity center offset.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_YAWRATE_I, 0.0f);
/**
* Yaw rate D gain
*
* Yaw rate differential gain. Small values help reduce fast oscillations. If value is too big oscillations will appear again.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_YAWRATE_D, 0.0f);
/**
* Yaw feed forward
*
* Feed forward weight for manual yaw control. 0 will give slow responce and no overshot, 1 - fast responce and big overshot.
*
* @min 0.0
* @max 1.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_YAW_FF, 0.5f);

2
src/modules/mc_pos_control/mc_pos_control_main.cpp
View File

@ -51,7 +51,6 @@
#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>
@ -68,7 +67,6 @@
#include <uORB/topics/vehicle_global_velocity_setpoint.h>
#include <systemlib/param/param.h>
#include <systemlib/err.h>
#include <systemlib/pid/pid.h>
#include <systemlib/systemlib.h>
#include <mathlib/mathlib.h>
#include <lib/geo/geo.h>

146
src/modules/mc_pos_control/mc_pos_control_params.c
View File

@ -39,20 +39,164 @@
#include <systemlib/param/param.h>
PARAM_DEFINE_FLOAT(MPC_THR_MIN, 0.0f);
/**
* Minimum thrust
*
* Minimum vertical thrust. It's recommended to set it > 0 to avoid free fall with zero thrust.
*
* @min 0.0
* @max 1.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_THR_MIN, 0.1f);
/**
* Maximum thrust
*
* Limit max allowed thrust.
*
* @min 0.0
* @max 1.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_THR_MAX, 1.0f);
/**
* Proportional gain for vertical position error
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_Z_P, 1.0f);
/**
* Proportional gain for vertical velocity error
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_Z_VEL_P, 0.1f);
/**
* Integral gain for vertical velocity error
*
* Non zero value allows hovering thrust estimation on stabilized or autonomous takeoff.
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_Z_VEL_I, 0.02f);
/**
* Differential gain for vertical velocity error
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_Z_VEL_D, 0.0f);
/**
* Maximum vertical velocity
*
* Maximum vertical velocity in AUTO mode and endpoint for stabilized modes (SEATBELT, EASY).
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_Z_VEL_MAX, 5.0f);
/**
* Vertical velocity feed forward
*
* Feed forward weight for altitude control in stabilized modes (SEATBELT, EASY). 0 will give slow responce and no overshot, 1 - fast responce and big overshot.
*
* @min 0.0
* @max 1.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_Z_FF, 0.5f);
/**
* Proportional gain for horizontal position error
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_XY_P, 1.0f);
/**
* Proportional gain for horizontal velocity error
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_XY_VEL_P, 0.1f);
/**
* Integral gain for horizontal velocity error
*
* Non-zero value allows to resist wind.
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_XY_VEL_I, 0.02f);
/**
* Differential gain for horizontal velocity error. Small values help reduce fast oscillations. If value is too big oscillations will appear again.
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_XY_VEL_D, 0.01f);
/**
* Maximum horizontal velocity
*
* Maximum horizontal velocity in AUTO mode and endpoint for position stabilized mode (EASY).
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_XY_VEL_MAX, 5.0f);
/**
* Horizontal velocity feed forward
*
* Feed forward weight for position control in position control mode (EASY). 0 will give slow responce and no overshot, 1 - fast responce and big overshot.
*
* @min 0.0
* @max 1.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_XY_FF, 0.5f);
/**
* Maximum tilt
*
* Limits maximum tilt in AUTO and EASY modes.
*
* @min 0.0
* @max 1.57
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_TILT_MAX, 1.0f);
/**
* Landing descend rate
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_LAND_SPEED, 1.0f);
/**
* Maximum landing tilt
*
* Limits maximum tilt on landing.
*
* @min 0.0
* @max 1.57
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_LAND_TILT, 0.3f);

16
src/modules/navigator/geofence_params.c
View File

@ -45,11 +45,17 @@
#include <systemlib/param/param.h>
/*
* geofence parameters, accessible via MAVLink
*
* Geofence parameters, accessible via MAVLink
*/
// @DisplayName Switch to enable geofence
// @Description if set to 1 geofence is enabled, defaults to 1 because geofence is only enabled when the geofence.txt file is present
// @Range 0 or 1
/**
* Enable geofence.
*
* Set to 1 to enable geofence.
* Defaults to 1 because geofence is only enabled when the geofence.txt file is present.
*
* @min 0
* @max 1
* @group Geofence
*/
PARAM_DEFINE_INT32(GF_ON, 1);

71
src/modules/navigator/navigator_main.cpp
View File

@ -305,6 +305,12 @@ private:
void start_land();
void start_land_home();
/**
* Fork for state transitions
*/
void request_loiter_or_ready();
void request_mission_if_available();
/**
* Guards offboard mission
*/
@ -699,24 +705,17 @@ Navigator::task_main()
} else {
/* MISSION switch */
if (_vstatus.mission_switch == MISSION_SWITCH_LOITER) {
dispatch(EVENT_LOITER_REQUESTED);
request_loiter_or_ready();
stick_mode = true;
} else if (_vstatus.mission_switch == MISSION_SWITCH_MISSION) {
/* switch to mission only if available */
if (_mission.current_mission_available()) {
dispatch(EVENT_MISSION_REQUESTED);
} else {
dispatch(EVENT_LOITER_REQUESTED);
}
request_mission_if_available();
stick_mode = true;
}
if (!stick_mode && _vstatus.return_switch == RETURN_SWITCH_NORMAL && myState == NAV_STATE_RTL) {
/* RETURN switch is in normal mode, no MISSION switch mapped, interrupt if in RTL state */
dispatch(EVENT_LOITER_REQUESTED);
request_mission_if_available();
stick_mode = true;
}
}
@ -733,17 +732,11 @@ Navigator::task_main()
break;
case NAV_STATE_LOITER:
dispatch(EVENT_LOITER_REQUESTED);
request_loiter_or_ready();
break;
case NAV_STATE_MISSION:
if (_mission.current_mission_available()) {
dispatch(EVENT_MISSION_REQUESTED);
} else {
dispatch(EVENT_LOITER_REQUESTED);
}
request_mission_if_available();
break;
case NAV_STATE_RTL:
@ -770,12 +763,7 @@ Navigator::task_main()
} else {
/* on first switch to AUTO try mission by default, if none is available fallback to loiter */
if (myState == NAV_STATE_NONE) {
if (_mission.current_mission_available()) {
dispatch(EVENT_MISSION_REQUESTED);
} else {
dispatch(EVENT_LOITER_REQUESTED);
}
request_mission_if_available();
}
}
}
@ -1071,7 +1059,7 @@ Navigator::start_loiter()
float min_alt_amsl = _parameters.min_altitude + _home_pos.alt;
/* use current altitude if above min altitude set by parameter */
if (_global_pos.alt < min_alt_amsl) {
if (_global_pos.alt < min_alt_amsl && !_vstatus.is_rotary_wing) {
_pos_sp_triplet.current.alt = min_alt_amsl;
mavlink_log_info(_mavlink_fd, "[navigator] loiter %.1fm higher", (double)(min_alt_amsl - _global_pos.alt));
@ -1080,9 +1068,8 @@ Navigator::start_loiter()
mavlink_log_info(_mavlink_fd, "[navigator] loiter at current altitude");
}
_pos_sp_triplet.current.type = SETPOINT_TYPE_LOITER;
}
_pos_sp_triplet.current.type = SETPOINT_TYPE_LOITER;
_pos_sp_triplet.current.loiter_radius = _parameters.loiter_radius;
_pos_sp_triplet.current.loiter_direction = 1;
_pos_sp_triplet.previous.valid = false;
@ -1405,6 +1392,28 @@ Navigator::set_rtl_item()
_pos_sp_triplet_updated = true;
}
void
Navigator::request_loiter_or_ready()
{
if (_vstatus.condition_landed) {
dispatch(EVENT_READY_REQUESTED);
} else {
dispatch(EVENT_LOITER_REQUESTED);
}
}
void
Navigator::request_mission_if_available()
{
if (_mission.current_mission_available()) {
dispatch(EVENT_MISSION_REQUESTED);
} else {
request_loiter_or_ready();
}
}
void
Navigator::position_setpoint_from_mission_item(position_setpoint_s *sp, mission_item_s *item)
{
@ -1574,13 +1583,7 @@ Navigator::on_mission_item_reached()
/* loiter at last waypoint */
_reset_loiter_pos = false;
mavlink_log_info(_mavlink_fd, "[navigator] mission completed");
if (_vstatus.condition_landed) {
dispatch(EVENT_READY_REQUESTED);
} else {
dispatch(EVENT_LOITER_REQUESTED);
}
request_loiter_or_ready();
}
} else if (myState == NAV_STATE_RTL) {

87
src/modules/navigator/navigator_params.c
View File

@ -50,14 +50,91 @@
/*
* Navigator parameters, accessible via MAVLink
*
*/
/**
* Minimum altitude (fixed wing only)
*
* Minimum altitude above home for LOITER.
*
* @unit meters
* @group Navigation
*/
PARAM_DEFINE_FLOAT(NAV_MIN_ALT, 50.0f);
/**
* Waypoint acceptance radius
*
* Default value of acceptance radius (if not specified in mission item).
*
* @unit meters
* @min 0.0
* @group Navigation
*/
PARAM_DEFINE_FLOAT(NAV_ACCEPT_RAD, 10.0f);
/**
* Loiter radius (fixed wing only)
*
* Default value of loiter radius (if not specified in mission item).
*
* @unit meters
* @min 0.0
* @group Navigation
*/
PARAM_DEFINE_FLOAT(NAV_LOITER_RAD, 50.0f);
/**
* Enable onboard mission
*
* @group Navigation
*/
PARAM_DEFINE_INT32(NAV_ONB_MIS_EN, 0);
PARAM_DEFINE_FLOAT(NAV_TAKEOFF_ALT, 10.0f); // default TAKEOFF altitude
PARAM_DEFINE_FLOAT(NAV_LAND_ALT, 5.0f); // slow descend from this altitude when landing
PARAM_DEFINE_FLOAT(NAV_RTL_ALT, 30.0f); // min altitude for going home in RTL mode
PARAM_DEFINE_FLOAT(NAV_RTL_LAND_T, -1.0f); // delay after descend before landing, if set to -1 the system will not land but loiter at NAV_LAND_ALT
/**
* Take-off altitude
*
* Even if first waypoint has altitude less then NAV_TAKEOFF_ALT above home position, system will climb to NAV_TAKEOFF_ALT on takeoff, then go to waypoint.
*
* @unit meters
* @group Navigation
*/
PARAM_DEFINE_FLOAT(NAV_TAKEOFF_ALT, 10.0f);
/**
* Landing altitude
*
* Stay at this altitude above home position after RTL descending. Land (i.e. slowly descend) from this altitude if autolanding allowed.
*
* @unit meters
* @group Navigation
*/
PARAM_DEFINE_FLOAT(NAV_LAND_ALT, 5.0f);
/**
* Return-To-Launch altitude
*
* Minimum altitude above home position for going home in RTL mode.
*
* @unit meters
* @group Navigation
*/
PARAM_DEFINE_FLOAT(NAV_RTL_ALT, 30.0f);
/**
* Return-To-Launch delay
*
* Delay after descend before landing in RTL mode.
* If set to -1 the system will not land but loiter at NAV_LAND_ALT.
*
* @unit seconds
* @group Navigation
*/
PARAM_DEFINE_FLOAT(NAV_RTL_LAND_T, -1.0f);
/**
* Enable parachute deployment
*
* @group Navigation
*/
PARAM_DEFINE_INT32(NAV_PARACHUTE_EN, 0);

3
src/modules/position_estimator_inav/position_estimator_inav_main.c
View File

@ -42,14 +42,11 @@
#include <stdio.h>
#include <stdbool.h>
#include <fcntl.h>
#include <float.h>
#include <string.h>
#include <nuttx/config.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/parameter_update.h>

2
src/modules/px4iofirmware/mixer.cpp
View File

@ -179,7 +179,7 @@ mixer_tick(void)
((r_setup_arming & PX4IO_P_SETUP_ARMING_FMU_ARMED)
/* and there is valid input via or mixer */ && (r_status_flags & PX4IO_P_STATUS_FLAGS_MIXER_OK) )
/* or direct PWM is set */ || (r_status_flags & PX4IO_P_STATUS_FLAGS_RAW_PWM)
/* or failsafe was set manually */ || (r_setup_arming & PX4IO_P_SETUP_ARMING_FAILSAFE_CUSTOM)
/* or failsafe was set manually */ || ((r_setup_arming & PX4IO_P_SETUP_ARMING_FAILSAFE_CUSTOM) && !(r_status_flags & PX4IO_P_STATUS_FLAGS_FMU_OK))
)
);

24
src/modules/sdlog2/sdlog2.c
View File

@ -82,6 +82,7 @@
#include <uORB/topics/airspeed.h>
#include <uORB/topics/rc_channels.h>
#include <uORB/topics/esc_status.h>
#include <uORB/topics/telemetry_status.h>
#include <systemlib/systemlib.h>
#include <systemlib/param/param.h>
@ -758,6 +759,7 @@ int sdlog2_thread_main(int argc, char *argv[])
struct esc_status_s esc;
struct vehicle_global_velocity_setpoint_s global_vel_sp;
struct battery_status_s battery;
struct telemetry_status_s telemetry;
} buf;
memset(&buf, 0, sizeof(buf));
@ -783,6 +785,7 @@ int sdlog2_thread_main(int argc, char *argv[])
int esc_sub;
int global_vel_sp_sub;
int battery_sub;
int telemetry_sub;
} subs;
/* log message buffer: header + body */
@ -811,6 +814,7 @@ int sdlog2_thread_main(int argc, char *argv[])
struct log_GVSP_s log_GVSP;
struct log_BATT_s log_BATT;
struct log_DIST_s log_DIST;
struct log_TELE_s log_TELE;
} body;
} log_msg = {
LOG_PACKET_HEADER_INIT(0)
@ -946,6 +950,12 @@ int sdlog2_thread_main(int argc, char *argv[])
fds[fdsc_count].events = POLLIN;
fdsc_count++;
/* --- TELEMETRY STATUS --- */
subs.telemetry_sub = orb_subscribe(ORB_ID(telemetry_status));
fds[fdsc_count].fd = subs.telemetry_sub;
fds[fdsc_count].events = POLLIN;
fdsc_count++;
/* WARNING: If you get the error message below,
* then the number of registered messages (fdsc)
* differs from the number of messages in the above list.
@ -1347,6 +1357,20 @@ int sdlog2_thread_main(int argc, char *argv[])
LOGBUFFER_WRITE_AND_COUNT(BATT);
}
/* --- TELEMETRY --- */
if (fds[ifds++].revents & POLLIN) {
orb_copy(ORB_ID(telemetry_status), subs.telemetry_sub, &buf.telemetry);
log_msg.msg_type = LOG_TELE_MSG;
log_msg.body.log_TELE.rssi = buf.telemetry.rssi;
log_msg.body.log_TELE.remote_rssi = buf.telemetry.remote_rssi;
log_msg.body.log_TELE.noise = buf.telemetry.noise;
log_msg.body.log_TELE.remote_noise = buf.telemetry.remote_noise;
log_msg.body.log_TELE.rxerrors = buf.telemetry.rxerrors;
log_msg.body.log_TELE.fixed = buf.telemetry.fixed;
log_msg.body.log_TELE.txbuf = buf.telemetry.txbuf;
LOGBUFFER_WRITE_AND_COUNT(TELE);
}
/* signal the other thread new data, but not yet unlock */
if (logbuffer_count(&lb) > MIN_BYTES_TO_WRITE) {
/* only request write if several packets can be written at once */

14
src/modules/sdlog2/sdlog2_messages.h
View File

@ -264,6 +264,18 @@ struct log_DIST_s {
uint8_t flags;
};
/* --- TELE - TELEMETRY STATUS --- */
#define LOG_TELE_MSG 22
struct log_TELE_s {
uint8_t rssi;
uint8_t remote_rssi;
uint8_t noise;
uint8_t remote_noise;
uint16_t rxerrors;
uint16_t fixed;
uint8_t txbuf;
};
/********** SYSTEM MESSAGES, ID > 0x80 **********/
/* --- TIME - TIME STAMP --- */
@ -311,6 +323,8 @@ static const struct log_format_s log_formats[] = {
LOG_FORMAT(GVSP, "fff", "VX,VY,VZ"),
LOG_FORMAT(BATT, "ffff", "V,VFilt,C,Discharged"),
LOG_FORMAT(DIST, "ffB", "Bottom,BottomRate,Flags"),
LOG_FORMAT(TELE, "BBBBHHB", "RSSI,RemRSSI,Noise,RemNoise,RXErr,Fixed,TXBuf"),
/* system-level messages, ID >= 0x80 */
// FMT: don't write format of format message, it's useless
LOG_FORMAT(TIME, "Q", "StartTime"),

303
src/modules/sensors/sensor_params.c
View File

@ -42,13 +42,10 @@
*/
#include <nuttx/config.h>
#include <systemlib/param/param.h>
/**
* Gyro X offset
*
* This is an X-axis offset for the gyro. Adjust it according to the calibration data.
* Gyro X-axis offset
*
* @min -10.0
* @max 10.0
@ -57,7 +54,7 @@
PARAM_DEFINE_FLOAT(SENS_GYRO_XOFF, 0.0f);
/**
* Gyro Y offset
* Gyro Y-axis offset
*
* @min -10.0
* @max 10.0
@ -66,7 +63,7 @@ PARAM_DEFINE_FLOAT(SENS_GYRO_XOFF, 0.0f);
PARAM_DEFINE_FLOAT(SENS_GYRO_YOFF, 0.0f);
/**
* Gyro Z offset
* Gyro Z-axis offset
*
* @min -5.0
* @max 5.0
@ -75,9 +72,7 @@ PARAM_DEFINE_FLOAT(SENS_GYRO_YOFF, 0.0f);
PARAM_DEFINE_FLOAT(SENS_GYRO_ZOFF, 0.0f);
/**
* Gyro X scaling
*
* X-axis scaling.
* Gyro X-axis scaling factor
*
* @min -1.5
* @max 1.5
@ -86,9 +81,7 @@ PARAM_DEFINE_FLOAT(SENS_GYRO_ZOFF, 0.0f);
PARAM_DEFINE_FLOAT(SENS_GYRO_XSCALE, 1.0f);
/**
* Gyro Y scaling
*
* Y-axis scaling.
* Gyro Y-axis scaling factor
*
* @min -1.5
* @max 1.5
@ -97,9 +90,7 @@ PARAM_DEFINE_FLOAT(SENS_GYRO_XSCALE, 1.0f);
PARAM_DEFINE_FLOAT(SENS_GYRO_YSCALE, 1.0f);
/**
* Gyro Z scaling
*
* Z-axis scaling.
* Gyro Z-axis scaling factor
*
* @min -1.5
* @max 1.5
@ -107,10 +98,9 @@ PARAM_DEFINE_FLOAT(SENS_GYRO_YSCALE, 1.0f);
*/
PARAM_DEFINE_FLOAT(SENS_GYRO_ZSCALE, 1.0f);
/**
* Magnetometer X offset
*
* This is an X-axis offset for the magnetometer.
* Magnetometer X-axis offset
*
* @min -500.0
* @max 500.0
@ -119,9 +109,7 @@ PARAM_DEFINE_FLOAT(SENS_GYRO_ZSCALE, 1.0f);
PARAM_DEFINE_FLOAT(SENS_MAG_XOFF, 0.0f);
/**
* Magnetometer Y offset
*
* This is an Y-axis offset for the magnetometer.
* Magnetometer Y-axis offset
*
* @min -500.0
* @max 500.0
@ -130,9 +118,7 @@ PARAM_DEFINE_FLOAT(SENS_MAG_XOFF, 0.0f);
PARAM_DEFINE_FLOAT(SENS_MAG_YOFF, 0.0f);
/**
* Magnetometer Z offset
*
* This is an Z-axis offset for the magnetometer.
* Magnetometer Z-axis offset
*
* @min -500.0
* @max 500.0
@ -140,24 +126,134 @@ PARAM_DEFINE_FLOAT(SENS_MAG_YOFF, 0.0f);
*/
PARAM_DEFINE_FLOAT(SENS_MAG_ZOFF, 0.0f);
/**
* Magnetometer X-axis scaling factor
*
* @group Sensor Calibration
*/
PARAM_DEFINE_FLOAT(SENS_MAG_XSCALE, 1.0f);
/**
* Magnetometer Y-axis scaling factor
*
* @group Sensor Calibration
*/
PARAM_DEFINE_FLOAT(SENS_MAG_YSCALE, 1.0f);
/**
* Magnetometer Z-axis scaling factor
*
* @group Sensor Calibration
*/
PARAM_DEFINE_FLOAT(SENS_MAG_ZSCALE, 1.0f);
/**
* Accelerometer X-axis offset
*
* @group Sensor Calibration
*/
PARAM_DEFINE_FLOAT(SENS_ACC_XOFF, 0.0f);
/**
* Accelerometer Y-axis offset
*
* @group Sensor Calibration
*/
PARAM_DEFINE_FLOAT(SENS_ACC_YOFF, 0.0f);
/**
* Accelerometer Z-axis offset
*
* @group Sensor Calibration
*/
PARAM_DEFINE_FLOAT(SENS_ACC_ZOFF, 0.0f);
/**
* Accelerometer X-axis scaling factor
*
* @group Sensor Calibration
*/
PARAM_DEFINE_FLOAT(SENS_ACC_XSCALE, 1.0f);
/**
* Accelerometer Y-axis scaling factor
*
* @group Sensor Calibration
*/
PARAM_DEFINE_FLOAT(SENS_ACC_YSCALE, 1.0f);
/**
* Accelerometer Z-axis scaling factor
*
* @group Sensor Calibration
*/
PARAM_DEFINE_FLOAT(SENS_ACC_ZSCALE, 1.0f);
/**
* Differential pressure sensor offset
*
* @group Sensor Calibration
*/
PARAM_DEFINE_FLOAT(SENS_DPRES_OFF, 0.0f);
/**
* Differential pressure sensor analog enabled
*
* @group Sensor Calibration
*/
PARAM_DEFINE_INT32(SENS_DPRES_ANA, 0);
/**
* Board rotation
*
* This parameter defines the rotation of the FMU board relative to the platform.
* Possible values are:
* 0 = No rotation
* 1 = Yaw 45°
* 2 = Yaw 90°
* 3 = Yaw 135°
* 4 = Yaw 180°
* 5 = Yaw 225°
* 6 = Yaw 270°
* 7 = Yaw 315°
* 8 = Roll 180°
* 9 = Roll 180°, Yaw 45°
* 10 = Roll 180°, Yaw 90°
* 11 = Roll 180°, Yaw 135°
* 12 = Pitch 180°
* 13 = Roll 180°, Yaw 225°
* 14 = Roll 180°, Yaw 270°
* 15 = Roll 180°, Yaw 315°
* 16 = Roll 90°
* 17 = Roll 90°, Yaw 45°
* 18 = Roll 90°, Yaw 90°
* 19 = Roll 90°, Yaw 135°
* 20 = Roll 270°
* 21 = Roll 270°, Yaw 45°
* 22 = Roll 270°, Yaw 90°
* 23 = Roll 270°, Yaw 135°
* 24 = Pitch 90°
* 25 = Pitch 270°
*
* @group Sensor Calibration
*/
PARAM_DEFINE_INT32(SENS_BOARD_ROT, 0);
/**
* External magnetometer rotation
*
* This parameter defines the rotation of the external magnetometer relative
* to the platform (not relative to the FMU).
* See SENS_BOARD_ROT for possible values.
*
* @group Sensor Calibration
*/
PARAM_DEFINE_INT32(SENS_EXT_MAG_ROT, 0);
/**
* RC Channel 1 Minimum
*
@ -367,20 +463,52 @@ PARAM_DEFINE_FLOAT(RC18_DZ, 0.0f);
#ifdef CONFIG_ARCH_BOARD_PX4FMU_V1
PARAM_DEFINE_INT32(RC_RL1_DSM_VCC, 0); /* Relay 1 controls DSM VCC */
#endif
PARAM_DEFINE_INT32(RC_DSM_BIND, -1); /* -1 = Idle, 0 = Start DSM2 bind, 1 = Start DSMX bind */
/**
* DSM binding trigger.
*
* -1 = Idle, 0 = Start DSM2 bind, 1 = Start DSMX bind
*
* @group Radio Calibration
*/
PARAM_DEFINE_INT32(RC_DSM_BIND, -1);
/**
* Scaling factor for battery voltage sensor on PX4IO.
*
* @group Battery Calibration
*/
PARAM_DEFINE_INT32(BAT_V_SCALE_IO, 10000);
#ifdef CONFIG_ARCH_BOARD_PX4FMU_V2
/**
* Scaling factor for battery voltage sensor on FMU v2.
*
* @group Battery Calibration
*/
PARAM_DEFINE_FLOAT(BAT_V_SCALING, 0.0082f);
#else
/* default is conversion factor for the PX4IO / PX4IOAR board, the factor for PX4FMU standalone is different */
/* PX4IOAR: 0.00838095238 */
/* FMU standalone: 1/(10 / (47+10)) * (3.3 / 4095) = 0.00459340659 */
/* FMU with PX4IOAR: (3.3f * 52.0f / 5.0f / 4095.0f) */
/**
* Scaling factor for battery voltage sensor on FMU v1.
*
* FMUv1 standalone: 1/(10 / (47+10)) * (3.3 / 4095) = 0.00459340659
* FMUv1 with PX4IO: 0.00459340659
* FMUv1 with PX4IOAR: (3.3f * 52.0f / 5.0f / 4095.0f) = 0.00838095238
*
* @group Battery Calibration
*/
PARAM_DEFINE_FLOAT(BAT_V_SCALING, 0.00459340659f);
#endif
/**
* Scaling factor for battery current sensor.
*
* @group Battery Calibration
*/
PARAM_DEFINE_FLOAT(BAT_C_SCALING, 0.0124); /* scaling for 3DR power brick */
/**
* Roll control channel mapping.
*
@ -446,22 +574,127 @@ PARAM_DEFINE_INT32(RC_MAP_YAW, 4);
* @group Radio Calibration
*/
PARAM_DEFINE_INT32(RC_MAP_MODE_SW, 0);
/**
* Return switch channel mapping.
*
* @min 0
* @max 18
* @group Radio Calibration
*/
PARAM_DEFINE_INT32(RC_MAP_RETURN_SW, 0);
/**
* Assist switch channel mapping.
*
* @min 0
* @max 18
* @group Radio Calibration
*/
PARAM_DEFINE_INT32(RC_MAP_ASSIST_SW, 0);
/**
* Mission switch channel mapping.
*
* @min 0
* @max 18
* @group Radio Calibration
*/
PARAM_DEFINE_INT32(RC_MAP_MISSIO_SW, 0);
//PARAM_DEFINE_INT32(RC_MAP_OFFB_SW, 0);
/**
* Flaps channel mapping.
*
* @min 0
* @max 18
* @group Radio Calibration
*/
PARAM_DEFINE_INT32(RC_MAP_FLAPS, 0);
PARAM_DEFINE_INT32(RC_MAP_AUX1, 0); /**< default function: camera pitch */
PARAM_DEFINE_INT32(RC_MAP_AUX2, 0); /**< default function: camera roll */
PARAM_DEFINE_INT32(RC_MAP_AUX3, 0); /**< default function: camera azimuth / yaw */
/**
* Auxiliary switch 1 channel mapping.
*
* Default function: Camera pitch
*
* @min 0
* @max 18
* @group Radio Calibration
*/
PARAM_DEFINE_INT32(RC_MAP_AUX1, 0);
/**
* Auxiliary switch 2 channel mapping.
*
* Default function: Camera roll
*
* @min 0
* @max 18
* @group Radio Calibration
*/
PARAM_DEFINE_INT32(RC_MAP_AUX2, 0); /**< default function: camera roll */
/**
* Auxiliary switch 3 channel mapping.
*
* Default function: Camera azimuth / yaw
*
* @min 0
* @max 18
* @group Radio Calibration
*/
PARAM_DEFINE_INT32(RC_MAP_AUX3, 0);
/**
* Roll scaling factor
*
* @group Radio Calibration
*/
PARAM_DEFINE_FLOAT(RC_SCALE_ROLL, 0.6f);
/**
* Pitch scaling factor
*
* @group Radio Calibration
*/
PARAM_DEFINE_FLOAT(RC_SCALE_PITCH, 0.6f);
/**
* Yaw scaling factor
*
* @group Radio Calibration
*/
PARAM_DEFINE_FLOAT(RC_SCALE_YAW, 2.0f);
PARAM_DEFINE_INT32(RC_FS_CH, 0); /**< RC failsafe channel, 0 = disable */
PARAM_DEFINE_INT32(RC_FS_MODE, 0); /**< RC failsafe mode: 0 = too low means signal loss, 1 = too high means signal loss */
PARAM_DEFINE_FLOAT(RC_FS_THR, 800); /**< RC failsafe PWM threshold */
/**
* Failsafe channel mapping.
*
* @min 0
* @max 18
* @group Radio Calibration
*/
PARAM_DEFINE_INT32(RC_FS_CH, 0);
/**
* Failsafe channel mode.
*
* 0 = too low means signal loss,
* 1 = too high means signal loss
*
* @min 0
* @max 1
* @group Radio Calibration
*/
PARAM_DEFINE_INT32(RC_FS_MODE, 0);
/**
* Failsafe channel PWM threshold.
*
* @min 0
* @max 1
* @group Radio Calibration
*/
PARAM_DEFINE_FLOAT(RC_FS_THR, 800);

19
src/modules/systemlib/system_params.c
View File

@ -40,8 +40,23 @@
#include <nuttx/config.h>
#include <systemlib/param/param.h>
// Auto-start script with index #n
/**
* Auto-start script index.
*
* Defines the auto-start script used to bootstrap the system.
*
* @group System
*/
PARAM_DEFINE_INT32(SYS_AUTOSTART, 0);
// Automatically configure default values
/**
* Automatically configure default values.
*
* Set to 1 to set platform-specific parameters to their default
* values on next system startup.
*
* @min 0
* @max 1
* @group System
*/
PARAM_DEFINE_INT32(SYS_AUTOCONFIG, 0);

10
src/modules/uORB/topics/telemetry_status.h
View File

@ -58,10 +58,10 @@ enum TELEMETRY_STATUS_RADIO_TYPE {
struct telemetry_status_s {
uint64_t timestamp;
enum TELEMETRY_STATUS_RADIO_TYPE type; /**< type of the radio hardware */
unsigned rssi; /**< local signal strength */
unsigned remote_rssi; /**< remote signal strength */
unsigned rxerrors; /**< receive errors */
unsigned fixed; /**< count of error corrected packets */
uint8_t rssi; /**< local signal strength */
uint8_t remote_rssi; /**< remote signal strength */
uint16_t rxerrors; /**< receive errors */
uint16_t fixed; /**< count of error corrected packets */
uint8_t noise; /**< background noise level */
uint8_t remote_noise; /**< remote background noise level */
uint8_t txbuf; /**< how full the tx buffer is as a percentage */
@ -73,4 +73,4 @@ struct telemetry_status_s {
ORB_DECLARE(telemetry_status);
#endif /* TOPIC_TELEMETRY_STATUS_H */
#endif /* TOPIC_TELEMETRY_STATUS_H */