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▼ Code File Link
http://instructables.tistory.com/723
/*
MultiWiiCopter by Alexandre Dubus
www.multiwii.com
March 2013 V2.2
This program is free software: you can redi stribute it and/or modify
it under the terms of the GNU General Public License as published by
the Free Software Foundation, either version 3 of the License, or
any later version. see <http://www.gnu.org/licenses/>
*/
#include <avr/io.h>
#include <Wire.h>
#include "config.h" //추가할것
#include "def.h"
#include <avr/pgmspace.h>
#define VERSION 220
#if defined(AIR)
volatile uint16_t serialRcValue[RC_CHANS]
= {1502, 1502, 1502, 1502, 1502, 1502, 1502, 1502};
uint8_t flightState = 0;
#endif
/*********** RC alias *****************/
enum rc
{
ROLL, //Y축 회전
PITCH, //X축 회전
YAW, //Z축 회전
THROTTLE, //이륙,착륙 담당
AUX1,
AUX2,
AUX3,
AUX4
};
enum pid
{
PIDROLL,
PIDPITCH,
PIDYAW,
PIDALT,
PIDPOS,
PIDPOSR,
PIDNAVR,
PIDLEVEL,
PIDMAG,
PIDVEL, // not used currently
PIDITEMS
};
const char pidnames[] PROGMEM =
"ROLL;"
"PITCH;"
"YAW;"
"ALT;"
"Pos;"
"PosR;"
"NavR;"
"LEVEL;"
"MAG;"
"VEL;"
;
enum box
{
BOXARM,
#if ACC
BOXANGLE,
BOXHORIZON,
#endif
#if BARO && (!defined(SUPPRESS_BARO_ALTHOLD))
BOXBARO,
#endif
#ifdef VARIOMETER
BOXVARIO,
#endif
#if MAG
BOXMAG,
BOXHEADFREE,
BOXHEADADJ, // acquire heading for HEADFREE mode
#endif
#if defined(SERVO_TILT) || defined(GIMBAL) || defined(SERVO_MIX_TILT)
BOXCAMSTAB,
#endif
#if defined(CAMTRIG)
BOXCAMTRIG,
#endif
#if GPS
BOXGPSHOME,
BOXGPSHOLD,
#endif
#if defined(FIXEDWING) || defined(HELICOPTER)
BOXPASSTHRU,
#endif
#if defined(BUZZER)
BOXBEEPERON,
#endif
#if defined(LED_FLASHER)
BOXLEDMAX, // we want maximum illumination
BOXLEDLOW, // low/no lights
#endif
#if defined(LANDING_LIGHTS_DDR)
BOXLLIGHTS, // enable landing lights at any altitude
#endif
#ifdef INFLIGHT_ACC_CALIBRATION
BOXCALIB,
#endif
#ifdef GOVERNOR_P
BOXGOV,
#endif
#ifdef OSD_SWITCH
BOXOSD,
#endif
CHECKBOXITEMS
};
const char boxnames[] PROGMEM = // names for dynamic generation of config GUI
"ARM;"
#if ACC
"ANGLE;"
"HORIZON;"
#endif
#if BARO && (!defined(SUPPRESS_BARO_ALTHOLD))
"BARO;"
#endif
#ifdef VARIOMETER
"VARIO;"
#endif
#if MAG //Sensors.ino 안에 MAG
"MAG;"
"HEADFREE;"
"HEADADJ;"
#endif
#if defined(SERVO_TILT) || defined(GIMBAL)|| defined(SERVO_MIX_TILT)
"CAMSTAB;"
#endif
#if defined(CAMTRIG) //CAM Trig 정의
"CAMTRIG;"
#endif
#if GPS
"GPS HOME;" //GPS.ino 안에서 GPS_HOME_MODE 로 쓰인다.
"GPS HOLD;"
#endif
#if defined(FIXEDWING) || defined(HELICOPTER)
"PASSTHRU;"
#endif
#if defined(BUZZER) //Alarms.ino 안에서 Buzzer로 쓰인다.
"BEEPER;"
#endif
#if defined(LED_FLASHER)
"LEDMAX;"
"LEDLOW;"
#endif
#if defined(LANDING_LIGHTS_DDR)
"LLIGHTS;"
#endif
#ifdef INFLIGHT_ACC_CALIBRATION
"CALIB;"
#endif
#ifdef GOVERNOR_P
"GOVERNOR;"
#endif
#ifdef OSD_SWITCH
"OSD SW;"
#endif
;
const uint8_t boxids[] PROGMEM = {// permanent IDs associated to boxes. This way, you can rely on an ID number to identify a BOX function.
0, //"ARM;"
#if ACC
1, //"ANGLE;"
2, //"HORIZON;"
#endif
#if BARO && (!defined(SUPPRESS_BARO_ALTHOLD))
3, //"BARO;"
#endif
#ifdef VARIOMETER
4, //"VARIO;"
#endif
#if MAG
5, //"MAG;"
6, //"HEADFREE;"
7, //"HEADADJ;"
#endif
#if defined(SERVO_TILT) || defined(GIMBAL)|| defined(SERVO_MIX_TILT)
8, //"CAMSTAB;"
#endif
#if defined(CAMTRIG)
9, //"CAMTRIG;"
#endif
#if GPS
10, //"GPS HOME;"
11, //"GPS HOLD;"
#endif
#if defined(FIXEDWING) || defined(HELICOPTER)
12, //"PASSTHRU;"
#endif
#if defined(BUZZER)
13, //"BEEPER;"
#endif
#if defined(LED_FLASHER)
14, //"LEDMAX;"
15, //"LEDLOW;"
#endif
#if defined(LANDING_LIGHTS_DDR)
16, //"LLIGHTS;"
#endif
#ifdef INFLIGHT_ACC_CALIBRATION
17, //"CALIB;"
#endif
#ifdef GOVERNOR_P
18, //"GOVERNOR;"
#endif
#ifdef OSD_SWITCH
19, //"OSD_SWITCH;"
#endif
};
static uint32_t currentTime = 0;
static uint16_t previousTime = 0;
static uint16_t cycleTime = 0; // this is the number in micro second to achieve a full loop, it can differ a little and is taken into account in the PID loop
static uint16_t calibratingA = 0; // the calibration is done in the main loop. Calibrating decreases at each cycle down to 0, then we enter in a normal mode.
static uint16_t calibratingB = 0; // baro calibration = get new ground pressure value
static uint16_t calibratingG;
static uint16_t acc_1G; // this is the 1G measured acceleration
static uint16_t acc_25deg;
static int16_t gyroADC[3],accADC[3],accSmooth[3],magADC[3];
static int16_t heading,magHold,headFreeModeHold; // [-180;+180]
static uint8_t vbat; // battery voltage in 0.1V steps
static uint8_t vbatMin = VBATNOMINAL; // lowest battery voltage in 0.1V steps
static uint8_t rcOptions[CHECKBOXITEMS];
static int32_t BaroAlt,EstAlt,AltHold; // in cm
static int16_t BaroPID = 0;
static int16_t errorAltitudeI = 0;
static int16_t vario = 0; // variometer in cm/s
#if defined(ARMEDTIMEWARNING)
static uint32_t ArmedTimeWarningMicroSeconds = 0;
#endif
static int16_t debug[4];
static int16_t sonarAlt; //to think about the unit
//-------------------------------------------------------------------------
// Calibration flag value
uint8_t calibration_flag;
//-------------------------------------------------------------------------
struct flags_struct {
uint8_t OK_TO_ARM :1 ;
uint8_t ARMED :1 ;
uint8_t I2C_INIT_DONE :1 ; // For i2c gps we have to now when i2c init is done, so we can update parameters to the i2cgps from eeprom (at startup it is done in setup())
uint8_t ACC_CALIBRATED :1 ;
uint8_t NUNCHUKDATA :1 ;
uint8_t ANGLE_MODE :1 ;
uint8_t HORIZON_MODE :1 ;
uint8_t MAG_MODE :1 ;
uint8_t BARO_MODE :1 ;
uint8_t GPS_HOME_MODE :1 ;
uint8_t GPS_HOLD_MODE :1 ;
uint8_t HEADFREE_MODE :1 ;
uint8_t PASSTHRU_MODE :1 ;
uint8_t GPS_FIX :1 ;
uint8_t GPS_FIX_HOME :1 ;
uint8_t SMALL_ANGLES_25 :1 ;
uint8_t CALIBRATE_MAG :1 ;
uint8_t VARIO_MODE :1;
} f;
//for log
#if defined(LOG_VALUES) || defined(LCD_TELEMETRY)
static uint16_t cycleTimeMax = 0; // highest ever cycle timen
static uint16_t cycleTimeMin = 65535; // lowest ever cycle timen
static uint16_t powerMax = 0; // highest ever current;
static int32_t BAROaltMax; // maximum value
#endif
#if defined(LOG_VALUES) || defined(LCD_TELEMETRY) || defined(ARMEDTIMEWARNING) || defined(LOG_PERMANENT)
static uint32_t armedTime = 0;
#endif
static int16_t i2c_errors_count = 0;
static int16_t annex650_overrun_count = 0;
// **********************
//Automatic ACC Offset Calibration
// **********************
#if defined(INFLIGHT_ACC_CALIBRATION)
static uint16_t InflightcalibratingA = 0;
static int16_t AccInflightCalibrationArmed;
static uint16_t AccInflightCalibrationMeasurementDone = 0;
static uint16_t AccInflightCalibrationSavetoEEProm = 0;
static uint16_t AccInflightCalibrationActive = 0;
#endif
// **********************
// power meter
// **********************
#if defined(POWERMETER)
#define PMOTOR_SUM 8 // index into pMeter[] for sum
static uint32_t pMeter[PMOTOR_SUM + 1]; // we use [0:7] for eight motors,one extra for sum
static uint8_t pMeterV; // dummy to satisfy the paramStruct logic in ConfigurationLoop()
static uint32_t pAlarm; // we scale the eeprom value from [0:255] to this value we can directly compare to the sum in pMeter[6]
static uint16_t powerValue = 0; // last known current
#endif
static uint16_t intPowerMeterSum, intPowerTrigger1;
// **********************
// telemetry
// **********************
#if defined(LCD_TELEMETRY)
static uint8_t telemetry = 0;
static uint8_t telemetry_auto = 0;
#endif
#ifdef LCD_TELEMETRY_STEP
static char telemetryStepSequence [] = LCD_TELEMETRY_STEP;
static uint8_t telemetryStepIndex = 0;
#endif
// ******************
// rc functions
// ******************
#define MINCHECK 1100
#define MAXCHECK 1900
#define ROL_LO (1<<(2*ROLL))
#define ROL_CE (3<<(2*ROLL))
#define ROL_HI (2<<(2*ROLL))
#define PIT_LO (1<<(2*PITCH))
#define PIT_CE (3<<(2*PITCH))
#define PIT_HI (2<<(2*PITCH))
#define YAW_LO (1<<(2*YAW))
#define YAW_CE (3<<(2*YAW))
#define YAW_HI (2<<(2*YAW))
#define THR_LO (1<<(2*THROTTLE))
#define THR_CE (3<<(2*THROTTLE))
#define THR_HI (2<<(2*THROTTLE))
static int16_t failsafeEvents = 0;
volatile int16_t failsafeCnt = 0;
static int16_t rcData[RC_CHANS]; // interval [1000;2000]
static int16_t rcCommand[4]; // interval [1000;2000] for THROTTLE and [-500;+500] for ROLL/PITCH/YAW
static int16_t lookupPitchRollRC[6];// lookup table for expo & RC rate PITCH+ROLL
static int16_t lookupThrottleRC[11];// lookup table for expo & mid THROTTLE
static uint16_t rssi; // range: [0;1023]
#if defined(SPEKTRUM)
volatile uint8_t spekFrameFlags;
volatile uint32_t spekTimeLast;
#endif
#if defined(OPENLRSv2MULTI)
static uint8_t pot_P,pot_I; // OpenLRS onboard potentiometers for P and I trim or other usages
#endif
// **************
// gyro+acc IMU
// **************
static int16_t gyroData[3] = {0,0,0};
static int16_t gyroZero[3] = {0,0,0};
static int16_t angle[2] = {0,0}; // absolute angle inclination in multiple of 0.1 degree 180 deg = 1800
// *************************
// motor and servo functions
// *************************
static int16_t axisPID[3];
static int16_t motor[NUMBER_MOTOR];
#if defined(SERVO)
static int16_t servo[8] = {1500,1500,1500,1500,1500,1500,1500,1500};
#endif
// ************************
// EEPROM Layout definition
// ************************
static uint8_t dynP8[3], dynD8[3];
static struct {
uint8_t currentSet;
int16_t accZero[3];
int16_t magZero[3];
uint8_t checksum; // MUST BE ON LAST POSITION OF STRUCTURE !
} global_conf;
static struct {
uint8_t checkNewConf;
uint8_t P8[PIDITEMS], I8[PIDITEMS], D8[PIDITEMS];
uint8_t rcRate8;
uint8_t rcExpo8;
uint8_t rollPitchRate;
uint8_t yawRate;
uint8_t dynThrPID;
uint8_t thrMid8;
uint8_t thrExpo8;
int16_t angleTrim[2];
uint16_t activate[CHECKBOXITEMS];
uint8_t powerTrigger1;
#ifdef FLYING_WING
uint16_t wing_left_mid;
uint16_t wing_right_mid;
#endif
#ifdef TRI
uint16_t tri_yaw_middle;
#endif
#if defined HELICOPTER || defined(AIRPLANE)|| defined(SINGLECOPTER)|| defined(DUALCOPTER)
int16_t servoTrim[8];
#endif
#if defined(GYRO_SMOOTHING)
uint8_t Smoothing[3];
#endif
#if defined (FAILSAFE)
int16_t failsafe_throttle;
#endif
#ifdef VBAT
uint8_t vbatscale;
uint8_t vbatlevel_warn1;
uint8_t vbatlevel_warn2;
uint8_t vbatlevel_crit;
uint8_t no_vbat;
#endif
#ifdef POWERMETER
uint16_t psensornull;
uint16_t pleveldivsoft;
uint16_t pleveldiv;
uint8_t pint2ma;
#endif
#ifdef CYCLETIME_FIXATED
uint16_t cycletime_fixated;
#endif
#ifdef MMGYRO
uint8_t mmgyro;
#endif
#ifdef ARMEDTIMEWARNING
uint16_t armedtimewarning;
#endif
int16_t minthrottle;
#ifdef GOVERNOR_P
int16_t governorP;
int16_t governorD;
int8_t governorR;
#endif
uint8_t checksum; // MUST BE ON LAST POSITION OF CONF STRUCTURE !
} conf;
#ifdef LOG_PERMANENT
static struct
{
uint16_t arm; // #arm events
uint16_t disarm; // #disarm events
uint16_t start; // #powercycle/reset/initialize events
uint32_t armed_time ; // copy of armedTime @ disarm
uint32_t lifetime; // sum (armed) lifetime in seconds
uint16_t failsafe; // #failsafe state @ disarm
uint16_t i2c; // #i2c errs state @ disarm
uint8_t running; // toggle on arm & disarm to monitor for clean shutdown vs. powercut
uint8_t checksum; // MUST BE ON LAST POSITION OF CONF STRUCTURE !
} plog;
#endif
// **********************
// GPS common variables
// **********************
static int32_t GPS_coord[2];
static int32_t GPS_home[2];
static int32_t GPS_hold[2];
static uint8_t GPS_numSat;
static uint16_t GPS_distanceToHome; // distance to home - unit: meter
static int16_t GPS_directionToHome; // direction to home - unit: degree
static uint16_t GPS_altitude; // GPS altitude - unit: meter
static uint16_t GPS_speed; // GPS speed - unit: cm/s
static uint8_t GPS_update = 0; // a binary toogle to distinct a GPS position update
static int16_t GPS_angle[2] = { 0, 0}; // the angles that must be applied for GPS correction
static uint16_t GPS_ground_course = 0; // - unit: degree*10
static uint8_t GPS_Present = 0; // Checksum from Gps serial
static uint8_t GPS_Enable = 0;
#define LAT 0
#define LON 1
// The desired bank towards North (Positive) or South (Negative) : latitude
// The desired bank towards East (Positive) or West (Negative) : longitude
static int16_t nav[2];
static int16_t nav_rated[2]; //Adding a rate controller to the navigation to make it smoother
// default POSHOLD control gains
#define POSHOLD_P .11
#define POSHOLD_I 0.0
#define POSHOLD_IMAX 20 // degrees
#define POSHOLD_RATE_P 2.0
#define POSHOLD_RATE_I 0.08 // Wind control
#define POSHOLD_RATE_D 0.045 // try 2 or 3 for POSHOLD_RATE 1
#define POSHOLD_RATE_IMAX 20 // degrees
// default Navigation PID gains
#define NAV_P 1.4
#define NAV_I 0.20 // Wind control
#define NAV_D 0.08 //
#define NAV_IMAX 20 // degrees
/////////////////////////////////////////////////////////////////////////////////////////////////////////////
// Serial GPS only variables
//navigation mode
#define NAV_MODE_NONE 0
#define NAV_MODE_POSHOLD 1
#define NAV_MODE_WP 2
static uint8_t nav_mode = NAV_MODE_NONE; // Navigation mode
static uint8_t alarmArray[16]; // array
#if BARO
static int32_t baroPressure;
static int32_t baroTemperature;
static int32_t baroPressureSum;
#endif
void annexCode() { // this code is excetuted at each loop and won't interfere with control loop if it lasts less than 650 microseconds
static uint32_t calibratedAccTime;
uint16_t tmp,tmp2;
uint8_t axis,prop1,prop2;
#define BREAKPOINT 1500
// PITCH & ROLL only dynamic PID adjustemnt, depending on throttle value
if (rcData[THROTTLE]<BREAKPOINT) {
prop2 = 100;
} else {
if (rcData[THROTTLE]<2000) {
prop2 = 100 - (uint16_t)conf.dynThrPID*(rcData[THROTTLE]-BREAKPOINT)/(2000-BREAKPOINT);
} else {
prop2 = 100 - conf.dynThrPID;
}
}
for(axis=0;axis<3;axis++) {
tmp = min(abs(rcData[axis]-MIDRC),500);
#if defined(DEADBAND)
if (tmp>DEADBAND) { tmp -= DEADBAND; }
else { tmp=0; }
#endif
if(axis!=2) { //ROLL & PITCH
tmp2 = tmp/100;
rcCommand[axis] = lookupPitchRollRC[tmp2] + (tmp-tmp2*100) * (lookupPitchRollRC[tmp2+1]-lookupPitchRollRC[tmp2]) / 100;
prop1 = 100-(uint16_t)conf.rollPitchRate*tmp/500;
prop1 = (uint16_t)prop1*prop2/100;
} else { // YAW
rcCommand[axis] = tmp;
prop1 = 100-(uint16_t)conf.yawRate*tmp/500;
}
dynP8[axis] = (uint16_t)conf.P8[axis]*prop1/100;
dynD8[axis] = (uint16_t)conf.D8[axis]*prop1/100;
if (rcData[axis]<MIDRC) rcCommand[axis] = -rcCommand[axis];
}
tmp = constrain(rcData[THROTTLE],MINCHECK,2000);
tmp = (uint32_t)(tmp-MINCHECK)*1000/(2000-MINCHECK); // [MINCHECK;2000] -> [0;1000]
tmp2 = tmp/100;
rcCommand[THROTTLE] = lookupThrottleRC[tmp2] + (tmp-tmp2*100) * (lookupThrottleRC[tmp2+1]-lookupThrottleRC[tmp2]) / 100; // [0;1000] -> expo -> [conf.minthrottle;MAXTHROTTLE]
if(f.HEADFREE_MODE) { //to optimize
float radDiff = (heading - headFreeModeHold) * 0.0174533f; // where PI/180 ~= 0.0174533
float cosDiff = cos(radDiff);
float sinDiff = sin(radDiff);
int16_t rcCommand_PITCH = rcCommand[PITCH]*cosDiff + rcCommand[ROLL]*sinDiff;
rcCommand[ROLL] = rcCommand[ROLL]*cosDiff - rcCommand[PITCH]*sinDiff;
rcCommand[PITCH] = rcCommand_PITCH;
}
#if defined(POWERMETER_HARD)
uint16_t pMeterRaw; // used for current reading
static uint16_t psensorTimer = 0;
if (! (++psensorTimer % PSENSORFREQ)) {
pMeterRaw = analogRead(PSENSORPIN);
//lcdprint_int16(pMeterRaw); LCDcrlf();
powerValue = ( conf.psensornull > pMeterRaw ? conf.psensornull - pMeterRaw : pMeterRaw - conf.psensornull); // do not use abs(), it would induce implicit cast to uint and overrun
if ( powerValue < 333) { // only accept reasonable values. 333 is empirical
#ifdef LCD_TELEMETRY
if (powerValue > powerMax) powerMax = powerValue;
#endif
} else {
powerValue = 333;
}
pMeter[PMOTOR_SUM] += (uint32_t) powerValue;
}
#endif
#if defined(BUZZER)
#if defined(VBAT)
static uint8_t vbatTimer = 0;
static uint8_t ind = 0;
uint16_t vbatRaw = 0;
static uint16_t vbatRawArray[8];
if (! (++vbatTimer % VBATFREQ)) {
vbatRawArray[(ind++)%8] = analogRead(V_BATPIN);
for (uint8_t i=0;i<8;i++) vbatRaw += vbatRawArray[i];
vbat = (vbatRaw*2) / conf.vbatscale; // result is Vbatt in 0.1V steps
}
#endif
alarmHandler(); // external buzzer routine that handles buzzer events globally now
#endif
#if defined(RX_RSSI)
static uint8_t sig = 0;
uint16_t rssiRaw = 0;
static uint16_t rssiRawArray[8];
rssiRawArray[(sig++)%8] = analogRead(RX_RSSI_PIN);
for (uint8_t i=0;i<8;i++) rssiRaw += rssiRawArray[i];
rssi = rssiRaw / 8;
#endif
if ( (calibratingA>0 && ACC ) || (calibratingG>0) ) { // Calibration phasis
LEDPIN_TOGGLE;
} else {
if (f.ACC_CALIBRATED) {LEDPIN_OFF;}
if (f.ARMED) {LEDPIN_ON;}
}
#if defined(LED_RING)
static uint32_t LEDTime;
if ( currentTime > LEDTime ) {
LEDTime = currentTime + 50000;
i2CLedRingState();
}
#endif
#if defined(LED_FLASHER)
auto_switch_led_flasher();
#endif
if ( currentTime > calibratedAccTime ) {
if (! f.SMALL_ANGLES_25) {
// the multi uses ACC and is not calibrated or is too much inclinated
f.ACC_CALIBRATED = 0;
LEDPIN_TOGGLE;
calibratedAccTime = currentTime + 100000;
} else {
f.ACC_CALIBRATED = 1;
}
}
#if !(defined(SPEKTRUM) && defined(PROMINI)) //Only one serial port on ProMini. Skip serial com if Spektrum Sat in use. Note: Spek code will auto-call serialCom if GUI data detected on serial0.
#if defined(GPS_PROMINI)
if(GPS_Enable == 0) {serialCom();}
#else
serialCom();
#endif
#endif
#if defined(POWERMETER)
intPowerMeterSum = (pMeter[PMOTOR_SUM]/conf.pleveldiv);
intPowerTrigger1 = conf.powerTrigger1 * PLEVELSCALE;
#endif
#ifdef LCD_TELEMETRY_AUTO
static char telemetryAutoSequence [] = LCD_TELEMETRY_AUTO;
static uint8_t telemetryAutoIndex = 0;
static uint16_t telemetryAutoTimer = 0;
if ( (telemetry_auto) && (! (++telemetryAutoTimer % LCD_TELEMETRY_AUTO_FREQ) ) ){
telemetry = telemetryAutoSequence[++telemetryAutoIndex % strlen(telemetryAutoSequence)];
LCDclear(); // make sure to clear away remnants
}
#endif
#ifdef LCD_TELEMETRY
static uint16_t telemetryTimer = 0;
if (! (++telemetryTimer % LCD_TELEMETRY_FREQ)) {
#if (LCD_TELEMETRY_DEBUG+0 > 0)
telemetry = LCD_TELEMETRY_DEBUG;
#endif
if (telemetry) lcd_telemetry();
}
#endif
#if GPS & defined(GPS_LED_INDICATOR) // modified by MIS to use STABLEPIN LED for number of sattelites indication
static uint32_t GPSLEDTime; // - No GPS FIX -> LED blink at speed of incoming GPS frames
static uint8_t blcnt; // - Fix and sat no. bellow 5 -> LED off
if(currentTime > GPSLEDTime) { // - Fix and sat no. >= 5 -> LED blinks, one blink for 5 sat, two blinks for 6 sat, three for 7 ...
if(f.GPS_FIX && GPS_numSat >= 5) {
if(++blcnt > 2*GPS_numSat) blcnt = 0;
GPSLEDTime = currentTime + 150000;
if(blcnt >= 10 && ((blcnt%2) == 0)) {STABLEPIN_ON;} else {STABLEPIN_OFF;}
}else{
if((GPS_update == 1) && !f.GPS_FIX) {STABLEPIN_ON;} else {STABLEPIN_OFF;}
blcnt = 0;
}
}
#endif
#if defined(LOG_VALUES) && (LOG_VALUES >= 2)
if (cycleTime > cycleTimeMax) cycleTimeMax = cycleTime; // remember highscore
if (cycleTime < cycleTimeMin) cycleTimeMin = cycleTime; // remember lowscore
#endif
if (f.ARMED) {
#if defined(LCD_TELEMETRY) || defined(ARMEDTIMEWARNING) || defined(LOG_PERMANENT)
armedTime += (uint32_t)cycleTime;
#endif
#if defined(VBAT)
if ( (vbat > conf.no_vbat) && (vbat < vbatMin) ) vbatMin = vbat;
#endif
#ifdef LCD_TELEMETRY
#if BARO
if ( (BaroAlt > BAROaltMax) ) BAROaltMax = BaroAlt;
#endif
#endif
}
}
void setup()
{
#if !defined(GPS_PROMINI)
SerialOpen(0,SERIAL0_COM_SPEED);
#if defined(PROMICRO)
SerialOpen(1,SERIAL1_COM_SPEED);
#endif
#if defined(MEGA)
SerialOpen(1,SERIAL1_COM_SPEED);
SerialOpen(2,SERIAL2_COM_SPEED);
SerialOpen(3,SERIAL3_COM_SPEED);
#endif
#endif
LEDPIN_PINMODE;
POWERPIN_PINMODE;
BUZZERPIN_PINMODE;
STABLEPIN_PINMODE;
POWERPIN_OFF;
initOutput();
#ifdef MULTIPLE_CONFIGURATION_PROFILES
for(global_conf.currentSet=0; global_conf.currentSet<3; global_conf.currentSet++) { // check all settings integrity
readEEPROM();
}
#else
global_conf.currentSet=0;
readEEPROM();
#endif
readGlobalSet();
readEEPROM(); // load current setting data
blinkLED(2,40,global_conf.currentSet+1);
configureReceiver();
#if defined (PILOTLAMP)
PL_INIT;
#endif
#if defined(OPENLRSv2MULTI)
initOpenLRS();
#endif
initSensors();
#if defined(I2C_GPS) || defined(GPS_SERIAL) || defined(GPS_FROM_OSD)
GPS_set_pids();
#endif
previousTime = micros();
#if defined(GIMBAL)
calibratingA = 512;
#endif
calibratingG = 512;
calibratingB = 200; // 10 seconds init_delay + 200 * 25 ms = 15 seconds before ground pressure settles
#if defined(POWERMETER)
for(uint8_t i=0;i<=PMOTOR_SUM;i++)
pMeter[i]=0;
#endif
/************************************/
#if defined(GPS_SERIAL)
GPS_SerialInit();
for(uint8_t i=0;i<=5;i++){
GPS_NewData();
LEDPIN_ON
delay(20);
LEDPIN_OFF
delay(80);
}
if(!GPS_Present){
SerialEnd(GPS_SERIAL);
SerialOpen(0,SERIAL0_COM_SPEED);
}
#if !defined(GPS_PROMINI)
GPS_Present = 1;
#endif
GPS_Enable = GPS_Present;
#endif
/************************************/
#if defined(I2C_GPS) || defined(TINY_GPS) || defined(GPS_FROM_OSD)
GPS_Enable = 1;
#endif
#if defined(LCD_ETPP) || defined(LCD_LCD03) || defined(OLED_I2C_128x64) || defined(LCD_TELEMETRY_STEP)
initLCD();
#endif
#ifdef LCD_TELEMETRY_DEBUG
telemetry_auto = 1;
#endif
#ifdef LCD_CONF_DEBUG
configurationLoop();
#endif
#ifdef LANDING_LIGHTS_DDR
init_landing_lights();
#endif
ADCSRA |= _BV(ADPS2) ; ADCSRA &= ~_BV(ADPS1); ADCSRA &= ~_BV(ADPS0); // this speeds up analogRead without loosing too much resolution: http://www.arduino.cc/cgi-bin/yabb2/YaBB.pl?num=1208715493/11
#if defined(LED_FLASHER)
init_led_flasher();
led_flasher_set_sequence(LED_FLASHER_SEQUENCE);
#endif
f.SMALL_ANGLES_25=1; // important for gyro only conf
#ifdef LOG_PERMANENT
// read last stored set
readPLog();
plog.lifetime += plog.armed_time / 1000000;
plog.start++; // #powercycle/reset/initialize events
// dump plog data to terminal
#ifdef LOG_PERMANENT_SHOW_AT_STARTUP
dumpPLog(0);
#endif
plog.armed_time = 0; // lifetime in seconds
//plog.running = 0; // toggle on arm & disarm to monitor for clean shutdown vs. powercut
#endif
pinMode(7,OUTPUT);
digitalWrite(7,LOW);
debugmsg_append_str("initialization completed\n");
}
//------------------------------------------------------------------
void calibration_fun(void)
{
calibratingG = 512;
#if GPS
GPS_reset_home_position();
#endif
#if BARO
calibratingB = 10; // calibrate baro to new ground level (10 * 25 ms = ~250 ms non blocking)
#endif
}
//------------------------------------------------------------------
// Unlock function
void go_arm() {
if(calibratingG == 0 && f.ACC_CALIBRATED
#if defined(FAILSAFE)
// && failsafeCnt < 2
#endif
) {
if(!f.ARMED) { // arm now!
digitalWrite(7,HIGH);
delay(200);
digitalWrite(7,LOW);
f.ARMED = 1;
flightState = flightState | 0x80;
headFreeModeHold = heading;
#if defined(VBAT)
if (vbat > conf.no_vbat) vbatMin = vbat;
#endif
#ifdef LCD_TELEMETRY // reset some values when arming
#if BARO
BAROaltMax = BaroAlt;
#endif
#endif
#ifdef LOG_PERMANENT
plog.arm++; // #arm events
plog.running = 1; // toggle on arm & disarm to monitor for clean shutdown vs. powercut
// write now.
writePLog();
#endif
}
} else if(!f.ARMED) {
blinkLED(2,255,1);
alarmArray[8] = 1;
}
if (calibration_flag == 0) {
calibration_flag = 1;
calibration_fun();
}
}
// Unlock function
void go_disarm() {
if (f.ARMED) {
digitalWrite(7,HIGH);
delay(200);
digitalWrite(7,LOW);
f.ARMED = 0;
flightState = flightState & 0x7f;
#ifdef LOG_PERMANENT
plog.disarm++; // #disarm events
plog.armed_time = armedTime ; // lifetime in seconds
if (failsafeEvents) plog.failsafe++; // #acitve failsafe @ disarm
if (i2c_errors_count > 10) plog.i2c++; // #i2c errs @ disarm
plog.running = 0; // toggle @ arm & disarm to monitor for clean shutdown vs. powercut
// write now.
writePLog();
#endif
}
}
void servos2Neutral() {
#ifdef TRI
servo[5] = 1500; // we center the yaw servo in conf mode
writeServos();
#endif
#ifdef FLYING_WING
servo[0] = conf.wing_left_mid;
servo[1] = conf.wing_right_mid;
writeServos();
#endif
#ifdef AIRPLANE
for(uint8_t i = 4; i<7 ;i++) servo[i] = 1500;
writeServos();
#endif
#ifdef HELICOPTER
servo[5] = YAW_CENTER;
servo[3] = servo[4] = servo[6] = 1500;
writeServos();
#endif
}
// ******** Main Loop *********
void loop () {
static uint8_t rcDelayCommand; // this indicates the number of time (multiple of RC measurement at 50Hz) the sticks must be maintained to run or switch off motors
static uint8_t rcSticks; // this hold sticks position for command combos
uint8_t axis,i;
int16_t error,errorAngle;
int16_t delta,deltaSum;
int16_t PTerm,ITerm,DTerm;
int16_t PTermACC = 0 , ITermACC = 0 , PTermGYRO = 0 , ITermGYRO = 0;
static int16_t lastGyro[3] = {0,0,0};
static int16_t delta1[3],delta2[3];
static int16_t errorGyroI[3] = {0,0,0};
static int16_t errorAngleI[2] = {0,0};
static uint32_t rcTime = 0;
static int16_t initialThrottleHold;
static uint32_t timestamp_fixated = 0;
#if defined(SPEKTRUM)
if (spekFrameFlags == 0x01) readSpektrum();
#endif
#if defined(OPENLRSv2MULTI)
Read_OpenLRS_RC();
#endif
#if defined(AIR)
serialCom();
#endif
if (currentTime > rcTime ) { // 50Hz
rcTime = currentTime + 20000;
computeRC();
// Failsafe routine - added by MIS
#if defined(AIR)
rcData[0] = serialRcValue[0];
rcData[1] = serialRcValue[1];
rcData[2] = serialRcValue[2];
rcData[3] = serialRcValue[3];
rcData[4] = serialRcValue[4];
rcData[5] = serialRcValue[5];
rcData[6] = serialRcValue[6];
rcData[7] = serialRcValue[7];
#endif
#if defined(FAILSAFE)
if ( failsafeCnt > (5*FAILSAFE_DELAY) && f.ARMED) { // Stabilize, and set Throttle to specified level
for(i=0; i<3; i++) rcData[i] = MIDRC; // after specified guard time after RC signal is lost (in 0.1sec)
if(rcData[THROTTLE] < conf.failsafe_throttle){
rcData[THROTTLE] = MINTHROTTLE;
}
else{
rcData[THROTTLE] = conf.failsafe_throttle;
}
if (failsafeCnt > 5*(FAILSAFE_DELAY+FAILSAFE_OFF_DELAY)) { // Turn OFF motors after specified Time (in 0.1sec)
go_disarm(); // This will prevent the copter to automatically rearm if failsafe shuts it down and prevents
f.OK_TO_ARM = 0; // to restart accidentely by just reconnect to the tx - you will have to switch off first to rearm
}
failsafeEvents++;
}
if ( failsafeCnt > (5*FAILSAFE_DELAY) && !f.ARMED) { //Turn of "Ok To arm to prevent the motors from spinning after repowering the RX with low throttle and aux to arm
go_disarm(); // This will prevent the copter to automatically rearm if failsafe shuts it down and prevents
f.OK_TO_ARM = 0; // to restart accidentely by just reconnect to the tx - you will have to switch off first to rearm
}
failsafeCnt++;
#endif
// end of failsafe routine - next change is made with RcOptions setting
// ------------------ STICKS COMMAND HANDLER --------------------
// checking sticks positions
uint8_t stTmp = 0;
for(i=0;i<4;i++) {
stTmp >>= 2;
if(rcData[i] > MINCHECK) stTmp |= 0x80; // check for MIN
if(rcData[i] < MAXCHECK) stTmp |= 0x40; // check for MAX
}
if(stTmp == rcSticks) {
if(rcDelayCommand<250) rcDelayCommand++;
} else rcDelayCommand = 0;
rcSticks = stTmp;
// perform actions
if (rcData[THROTTLE] <= MINCHECK) { // THROTTLE at minimum
errorGyroI[ROLL] = 0; errorGyroI[PITCH] = 0; errorGyroI[YAW] = 0;
errorAngleI[ROLL] = 0; errorAngleI[PITCH] = 0;
if (conf.activate[BOXARM] > 0) { // Arming/Disarming via ARM BOX
if ( rcOptions[BOXARM] && f.OK_TO_ARM )
go_arm();
else if (f.ARMED)
go_disarm();
}
}
if(rcDelayCommand == 20) {
if(f.ARMED) { // actions during armed
#ifdef ALLOW_ARM_DISARM_VIA_TX_YAW
if (conf.activate[BOXARM] == 0 && rcSticks == THR_LO + YAW_LO + PIT_CE + ROL_CE) go_disarm(); // Disarm via YAW
#endif
#ifdef ALLOW_ARM_DISARM_VIA_TX_ROLL
if (conf.activate[BOXARM] == 0 && rcSticks == THR_LO + YAW_CE + PIT_CE + ROL_LO) go_disarm(); // Disarm via ROLL
#endif
} else { // actions during not armed
i=0;
if (rcSticks == THR_LO + YAW_LO + PIT_LO + ROL_CE) { // GYRO calibration
//------------------------------------------------------------
calibration_fun();
//------------------------------------------------------------
}
#if defined(INFLIGHT_ACC_CALIBRATION)
else if (rcSticks == THR_LO + YAW_LO + PIT_HI + ROL_HI) { // Inflight ACC calibration START/STOP
if (AccInflightCalibrationMeasurementDone){ // trigger saving into eeprom after landing
AccInflightCalibrationMeasurementDone = 0;
AccInflightCalibrationSavetoEEProm = 1;
}else{
AccInflightCalibrationArmed = !AccInflightCalibrationArmed;
#if defined(BUZZER)
if (AccInflightCalibrationArmed) alarmArray[0]=2; else alarmArray[0]=3;
#endif
}
}
#endif
#ifdef MULTIPLE_CONFIGURATION_PROFILES
if (rcSticks == THR_LO + YAW_LO + PIT_CE + ROL_LO) i=1; // ROLL left -> Profile 1
else if (rcSticks == THR_LO + YAW_LO + PIT_HI + ROL_CE) i=2; // PITCH up -> Profile 2
else if (rcSticks == THR_LO + YAW_LO + PIT_CE + ROL_HI) i=3; // ROLL right -> Profile 3
if(i) {
global_conf.currentSet = i-1;
writeGlobalSet(0);
readEEPROM();
blinkLED(2,40,i);
alarmArray[0] = i;
}
#endif
if (rcSticks == THR_LO + YAW_HI + PIT_HI + ROL_CE) { // Enter LCD config
#if defined(LCD_CONF)
configurationLoop(); // beginning LCD configuration
#endif
previousTime = micros();
}
#ifdef ALLOW_ARM_DISARM_VIA_TX_YAW
else if (conf.activate[BOXARM] == 0 && rcSticks == THR_LO + YAW_HI + PIT_CE + ROL_CE) go_arm(); // Arm via YAW
#endif
#ifdef ALLOW_ARM_DISARM_VIA_TX_ROLL
else if (conf.activate[BOXARM] == 0 && rcSticks == THR_LO + YAW_CE + PIT_CE + ROL_HI) go_arm(); // Arm via ROLL
#endif
#ifdef LCD_TELEMETRY_AUTO
else if (rcSticks == THR_LO + YAW_CE + PIT_HI + ROL_LO) { // Auto telemetry ON/OFF
if (telemetry_auto) {
telemetry_auto = 0;
telemetry = 0;
} else
telemetry_auto = 1;
}
#endif
#ifdef LCD_TELEMETRY_STEP
else if (rcSticks == THR_LO + YAW_CE + PIT_HI + ROL_HI) { // Telemetry next step
telemetry = telemetryStepSequence[++telemetryStepIndex % strlen(telemetryStepSequence)];
#ifdef OLED_I2C_128x64
if (telemetry != 0) i2c_OLED_init();
#endif
LCDclear();
}
#endif
else if (rcSticks == THR_HI + YAW_LO + PIT_LO + ROL_CE) calibratingA=512; // throttle=max, yaw=left, pitch=min
else if (rcSticks == THR_HI + YAW_HI + PIT_LO + ROL_CE) f.CALIBRATE_MAG = 1; // throttle=max, yaw=right, pitch=min
i=0;
if (rcSticks == THR_HI + YAW_CE + PIT_HI + ROL_CE) {conf.angleTrim[PITCH]+=2; i=1;}
else if (rcSticks == THR_HI + YAW_CE + PIT_LO + ROL_CE) {conf.angleTrim[PITCH]-=2; i=1;}
else if (rcSticks == THR_HI + YAW_CE + PIT_CE + ROL_HI) {conf.angleTrim[ROLL] +=2; i=1;}
else if (rcSticks == THR_HI + YAW_CE + PIT_CE + ROL_LO) {conf.angleTrim[ROLL] -=2; i=1;}
if (i) {
writeParams(1);
rcDelayCommand = 0; // allow autorepetition
#if defined(LED_RING)
blinkLedRing();
#endif
}
}
}
#if defined(LED_FLASHER)
led_flasher_autoselect_sequence();
#endif
#if defined(INFLIGHT_ACC_CALIBRATION)
if (AccInflightCalibrationArmed && f.ARMED && rcData[THROTTLE] > MINCHECK && !rcOptions[BOXARM] ){ // Copter is airborne and you are turning it off via boxarm : start measurement
InflightcalibratingA = 50;
AccInflightCalibrationArmed = 0;
}
if (rcOptions[BOXCALIB]) { // Use the Calib Option to activate : Calib = TRUE Meausrement started, Land and Calib = 0 measurement stored
if (!AccInflightCalibrationActive && !AccInflightCalibrationMeasurementDone){
InflightcalibratingA = 50;
}
}else if(AccInflightCalibrationMeasurementDone && !f.ARMED){
AccInflightCalibrationMeasurementDone = 0;
AccInflightCalibrationSavetoEEProm = 1;
}
#endif
uint16_t auxState = 0;
for(i=0;i<4;i++)
auxState |= (rcData[AUX1+i]<1300)<<(3*i) | (1300<rcData[AUX1+i] && rcData[AUX1+i]<1700)<<(3*i+1) | (rcData[AUX1+i]>1700)<<(3*i+2);
for(i=0;i<CHECKBOXITEMS;i++)
rcOptions[i] = (auxState & conf.activate[i])>0;
// note: if FAILSAFE is disable, failsafeCnt > 5*FAILSAFE_DELAY is always false
#if ACC
if ( rcOptions[BOXANGLE] || (failsafeCnt > 5*FAILSAFE_DELAY) ) {
// bumpless transfer to Level mode
if (!f.ANGLE_MODE) {
errorAngleI[ROLL] = 0; errorAngleI[PITCH] = 0;
f.ANGLE_MODE = 1;
}
} else {
// failsafe support
f.ANGLE_MODE = 0;
}
if ( rcOptions[BOXHORIZON] ) {
f.ANGLE_MODE = 0;
if (!f.HORIZON_MODE) {
errorAngleI[ROLL] = 0; errorAngleI[PITCH] = 0;
f.HORIZON_MODE = 1;
}
} else {
f.HORIZON_MODE = 0;
}
#endif
if (rcOptions[BOXARM] == 0) f.OK_TO_ARM = 1;
#if !defined(GPS_LED_INDICATOR)
if (f.ANGLE_MODE || f.HORIZON_MODE) {STABLEPIN_ON;} else {STABLEPIN_OFF;}
#endif
#if BARO
#if (!defined(SUPPRESS_BARO_ALTHOLD))
if (rcOptions[BOXBARO]) {
if (!f.BARO_MODE) {
f.BARO_MODE = 1;
AltHold = EstAlt;
initialThrottleHold = rcCommand[THROTTLE];
errorAltitudeI = 0;
BaroPID=0;
}
} else {
f.BARO_MODE = 0;
}
#endif
#ifdef VARIOMETER
if (rcOptions[BOXVARIO]) {
if (!f.VARIO_MODE) {
f.VARIO_MODE = 1;
}
} else {
f.VARIO_MODE = 0;
}
#endif
#endif
#if MAG
if (rcOptions[BOXMAG]) {
if (!f.MAG_MODE) {
f.MAG_MODE = 1;
magHold = heading;
}
} else {
f.MAG_MODE = 0;
}
if (rcOptions[BOXHEADFREE]) {
if (!f.HEADFREE_MODE) {
f.HEADFREE_MODE = 1;
}
} else {
f.HEADFREE_MODE = 0;
}
if (rcOptions[BOXHEADADJ]) {
headFreeModeHold = heading; // acquire new heading
}
#endif
#if GPS
static uint8_t GPSNavReset = 1;
if (f.GPS_FIX && GPS_numSat >= 5 ) {
if (rcOptions[BOXGPSHOME]) { // if both GPS_HOME & GPS_HOLD are checked => GPS_HOME is the priority
if (!f.GPS_HOME_MODE) {
f.GPS_HOME_MODE = 1;
f.GPS_HOLD_MODE = 0;
GPSNavReset = 0;
#if defined(I2C_GPS)
GPS_I2C_command(I2C_GPS_COMMAND_START_NAV,0); //waypoint zero
#else // SERIAL
GPS_set_next_wp(&GPS_home[LAT],&GPS_home[LON]);
nav_mode = NAV_MODE_WP;
#endif
}
} else {
f.GPS_HOME_MODE = 0;
if (rcOptions[BOXGPSHOLD] && abs(rcCommand[ROLL])< AP_MODE && abs(rcCommand[PITCH]) < AP_MODE) {
if (!f.GPS_HOLD_MODE) {
f.GPS_HOLD_MODE = 1;
GPSNavReset = 0;
#if defined(I2C_GPS)
GPS_I2C_command(I2C_GPS_COMMAND_POSHOLD,0);
#else
GPS_hold[LAT] = GPS_coord[LAT];
GPS_hold[LON] = GPS_coord[LON];
GPS_set_next_wp(&GPS_hold[LAT],&GPS_hold[LON]);
nav_mode = NAV_MODE_POSHOLD;
#endif
}
} else {
f.GPS_HOLD_MODE = 0;
// both boxes are unselected here, nav is reset if not already done
if (GPSNavReset == 0 ) {
GPSNavReset = 1;
GPS_reset_nav();
}
}
}
} else {
f.GPS_HOME_MODE = 0;
f.GPS_HOLD_MODE = 0;
#if !defined(I2C_GPS)
nav_mode = NAV_MODE_NONE;
#endif
}
#endif
#if defined(FIXEDWING) || defined(HELICOPTER)
if (rcOptions[BOXPASSTHRU]) {f.PASSTHRU_MODE = 1;}
else {f.PASSTHRU_MODE = 0;}
#endif
} else { // not in rc loop
static uint8_t taskOrder=0; // never call all functions in the same loop, to avoid high delay spikes
if(taskOrder>4) taskOrder-=5;
switch (taskOrder) {
case 0:
taskOrder++;
#if MAG
if (Mag_getADC()) break; // max 350 µs (HMC5883) // only break when we actually did something
#endif
case 1:
taskOrder++;
#if BARO
if (Baro_update() != 0 ) break;
#endif
case 2:
taskOrder++;
break;
#if BARO
if (getEstimatedAltitude() !=0) break;
#endif
case 3:
taskOrder++;
#if GPS
if(GPS_Enable) GPS_NewData();
break;
#endif
case 4:
taskOrder++;
#if SONAR
Sonar_update();
#endif
#ifdef LANDING_LIGHTS_DDR
auto_switch_landing_lights();
#endif
#ifdef VARIOMETER
if (f.VARIO_MODE) vario_signaling();
#endif
break;
}
}
computeIMU();
// Measure loop rate just afer reading the sensors
currentTime = micros();
cycleTime = currentTime - previousTime;
previousTime = currentTime;
#ifdef CYCLETIME_FIXATED
if (conf.cycletime_fixated) {
if ((micros()-timestamp_fixated)>conf.cycletime_fixated) {
} else {
while((micros()-timestamp_fixated)<conf.cycletime_fixated) ; // waste away
}
timestamp_fixated=micros();
}
#endif
//***********************************
//**** Experimental FlightModes *****
//***********************************
#if defined(ACROTRAINER_MODE)
if(f.ANGLE_MODE){
if (abs(rcCommand[ROLL]) + abs(rcCommand[PITCH]) >= ACROTRAINER_MODE ) {
f.ANGLE_MODE=0;
f.HORIZON_MODE=0;
f.MAG_MODE=0;
f.BARO_MODE=0;
f.GPS_HOME_MODE=0;
f.GPS_HOLD_MODE=0;
}
}
#endif
//***********************************
#if MAG
if (abs(rcCommand[YAW]) <70 && f.MAG_MODE) {
int16_t dif = heading - magHold;
if (dif <= - 180) dif += 360;
if (dif >= + 180) dif -= 360;
if ( f.SMALL_ANGLES_25 ) rcCommand[YAW] -= dif*conf.P8[PIDMAG]>>5;
} else magHold = heading;
#endif
#if BARO && (!defined(SUPPRESS_BARO_ALTHOLD))
if (f.BARO_MODE) {
static uint8_t isAltHoldChanged = 0;
#if defined(ALTHOLD_FAST_THROTTLE_CHANGE)
if (abs(rcCommand[THROTTLE]-initialThrottleHold) > ALT_HOLD_THROTTLE_NEUTRAL_ZONE) {
//errorAltitudeI = 0;
isAltHoldChanged = 1;
rcCommand[THROTTLE] += (rcCommand[THROTTLE] > initialThrottleHold) ? -ALT_HOLD_THROTTLE_NEUTRAL_ZONE : ALT_HOLD_THROTTLE_NEUTRAL_ZONE;
// initialThrottleHold += (rcCommand[THROTTLE] > initialThrottleHold) ? -ALT_HOLD_THROTTLE_NEUTRAL_ZONE : ALT_HOLD_THROTTLE_NEUTRAL_ZONE;; //++hex nano
} else {
if (isAltHoldChanged) {
AltHold = EstAlt;
isAltHoldChanged = 0;
}
rcCommand[THROTTLE] = initialThrottleHold + BaroPID;
}
#else
static int16_t AltHoldCorr = 0;
if (abs(rcCommand[THROTTLE]-initialThrottleHold)>ALT_HOLD_THROTTLE_NEUTRAL_ZONE) {
// Slowly increase/decrease AltHold proportional to stick movement ( +100 throttle gives ~ +50 cm in 1 second with cycle time about 3-4ms)
AltHoldCorr+= rcCommand[THROTTLE] - initialThrottleHold;
if(abs(AltHoldCorr) > 500) {
AltHold += AltHoldCorr/500;
AltHoldCorr %= 500;
}
//errorAltitudeI = 0;
isAltHoldChanged = 1;
} else if (isAltHoldChanged) {
AltHold = EstAlt;
isAltHoldChanged = 0;
}
rcCommand[THROTTLE] = initialThrottleHold + BaroPID;
#endif
}
#endif
#if GPS
if ( (f.GPS_HOME_MODE || f.GPS_HOLD_MODE) && f.GPS_FIX_HOME ) {
float sin_yaw_y = sin(heading*0.0174532925f);
float cos_yaw_x = cos(heading*0.0174532925f);
#if defined(NAV_SLEW_RATE)
nav_rated[LON] += constrain(wrap_18000(nav[LON]-nav_rated[LON]),-NAV_SLEW_RATE,NAV_SLEW_RATE);
nav_rated[LAT] += constrain(wrap_18000(nav[LAT]-nav_rated[LAT]),-NAV_SLEW_RATE,NAV_SLEW_RATE);
GPS_angle[ROLL] = (nav_rated[LON]*cos_yaw_x - nav_rated[LAT]*sin_yaw_y) /10;
GPS_angle[PITCH] = (nav_rated[LON]*sin_yaw_y + nav_rated[LAT]*cos_yaw_x) /10;
#else
GPS_angle[ROLL] = (nav[LON]*cos_yaw_x - nav[LAT]*sin_yaw_y) /10;
GPS_angle[PITCH] = (nav[LON]*sin_yaw_y + nav[LAT]*cos_yaw_x) /10;
#endif
} else {
GPS_angle[ROLL] = 0;
GPS_angle[PITCH] = 0;
}
#endif
//**** PITCH & ROLL & YAW PID ****
int16_t prop;
prop = min(max(abs(rcCommand[PITCH]),abs(rcCommand[ROLL])),500); // range [0;500]
for(axis=0;axis<3;axis++) {
if ((f.ANGLE_MODE || f.HORIZON_MODE) && axis<2 ) { // MODE relying on ACC
// 50 degrees max inclination
errorAngle = constrain((rcCommand[axis]<<1) + GPS_angle[axis],-500,+500) - angle[axis] + conf.angleTrim[axis]; //16 bits is ok here
PTermACC = ((int32_t)errorAngle*conf.P8[PIDLEVEL])>>7; // 32 bits is needed for calculation: errorAngle*P8[PIDLEVEL] could exceed 32768 16 bits is ok for result
PTermACC = constrain(PTermACC,-conf.D8[PIDLEVEL]*5,+conf.D8[PIDLEVEL]*5);
errorAngleI[axis] = constrain(errorAngleI[axis]+errorAngle,-10000,+10000); // WindUp //16 bits is ok here
ITermACC = ((int32_t)errorAngleI[axis]*conf.I8[PIDLEVEL])>>12; // 32 bits is needed for calculation:10000*I8 could exceed 32768 16 bits is ok for result
}
if ( !f.ANGLE_MODE || f.HORIZON_MODE || axis == 2 ) { // MODE relying on GYRO or YAW axis
if (abs(rcCommand[axis])<500) error = (rcCommand[axis]<<6)/conf.P8[axis] ; // 16 bits is needed for calculation: 500*64 = 32000 16 bits is ok for result if P8>5 (P>0.5)
else error = ((int32_t)rcCommand[axis]<<6)/conf.P8[axis] ; // 32 bits is needed for calculation
error -= gyroData[axis];
PTermGYRO = rcCommand[axis];
errorGyroI[axis] = constrain(errorGyroI[axis]+error,-16000,+16000); // WindUp 16 bits is ok here
if (abs(gyroData[axis])>640) errorGyroI[axis] = 0;
ITermGYRO = ((errorGyroI[axis]>>7)*conf.I8[axis])>>6; // 16 bits is ok here 16000/125 = 128 ; 128*250 = 32000
}
if ( f.HORIZON_MODE && axis<2) {
PTerm = ((int32_t)PTermACC*(512-prop) + (int32_t)PTermGYRO*prop)>>9; // the real factor should be 500, but 512 is ok
ITerm = ((int32_t)ITermACC*(512-prop) + (int32_t)ITermGYRO*prop)>>9;
} else {
if ( f.ANGLE_MODE && axis<2) {
PTerm = PTermACC;
ITerm = ITermACC;
} else {
PTerm = PTermGYRO;
ITerm = ITermGYRO;
}
}
PTerm -= ((int32_t)gyroData[axis]*dynP8[axis])>>6; // 32 bits is needed for calculation
delta = gyroData[axis] - lastGyro[axis]; // 16 bits is ok here, the dif between 2 consecutive gyro reads is limited to 800
lastGyro[axis] = gyroData[axis];
deltaSum = delta1[axis]+delta2[axis]+delta;
delta2[axis] = delta1[axis];
delta1[axis] = delta;
DTerm = ((int32_t)deltaSum*dynD8[axis])>>5; // 32 bits is needed for calculation
axisPID[axis] = PTerm + ITerm - DTerm;
}
mixTable();
writeServos();
writeMotors();
}
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