void init_imu(void){ init_magnetometer(); init_gyro(); init_accelerometer(); }
// usetup is called during the calibration period. It must return before the // period ends. int usetup (void) { printf("\nPlace robot, press go."); goClick(); printf("\nStabilizing..."); pause(500); /* Wait for robot to stabilize mechanically */ printf("\nCalibrating offset..."); init_gyro(GYRO_PORT, 638, 10000); printf("\nDone calibration"); rf_set_team(60); return 0; }
// It all starts here: int main(void) { // start with default user settings in case there's nothing in eeprom default_user_settings(); // try to load settings from eeprom read_user_settings_from_eeprom(); // set our LED as a digital output lib_digitalio_initpin(LED1_OUTPUT,DIGITALOUTPUT); //initialize the libraries that require initialization lib_timers_init(); lib_i2c_init(); // pause a moment before initializing everything. To make sure everything is powered up lib_timers_delaymilliseconds(100); // initialize all other modules init_rx(); init_outputs(); serial_init(); init_gyro(); init_acc(); init_baro(); init_compass(); init_gps(); init_imu(); // set the default i2c speed to 400 KHz. If a device needs to slow it down, it can, but it should set it back. lib_i2c_setclockspeed(I2C_400_KHZ); // initialize state global.state.armed=0; global.state.calibratingCompass=0; global.state.calibratingAccAndGyro=0; global.state.navigationMode=NAVIGATION_MODE_OFF; global.failsafeTimer=lib_timers_starttimer(); // run loop for(;;) { // check to see what switches are activated check_checkbox_items(); // check for config program activity serial_check_for_action(); calculate_timesliver(); // run the imu to estimate the current attitude of the aircraft imu_calculate_estimated_attitude(); // arm and disarm via rx aux switches if (global.rxValues[THROTTLE_INDEX]<FPSTICKLOW) { // see if we want to change armed modes if (!global.state.armed) { if (global.activeCheckboxItems & CHECKBOX_MASK_ARM) { global.state.armed=1; #if (GPS_TYPE!=NO_GPS) navigation_set_home_to_current_location(); #endif global.home.heading=global.currentEstimatedEulerAttitude[YAW_INDEX]; global.home.location.altitude=global.baroRawAltitude; } } else if (!(global.activeCheckboxItems & CHECKBOX_MASK_ARM)) global.state.armed=0; } #if (GPS_TYPE!=NO_GPS) // turn on or off navigation when appropriate if (global.state.navigationMode==NAVIGATION_MODE_OFF) { if (global.activeCheckboxItems & CHECKBOX_MASK_RETURNTOHOME) { // return to home switch turned on navigation_set_destination(global.home.location.latitude,global.home.location.longitude); global.state.navigationMode=NAVIGATION_MODE_RETURN_TO_HOME; } else if (global.activeCheckboxItems & CHECKBOX_MASK_POSITIONHOLD) { // position hold turned on navigation_set_destination(global.gps.currentLatitude,global.gps.currentLongitude); global.state.navigationMode=NAVIGATION_MODE_POSITION_HOLD; } } else { // we are currently navigating // turn off navigation if desired if ((global.state.navigationMode==NAVIGATION_MODE_RETURN_TO_HOME && !(global.activeCheckboxItems & CHECKBOX_MASK_RETURNTOHOME)) || (global.state.navigationMode==NAVIGATION_MODE_POSITION_HOLD && !(global.activeCheckboxItems & CHECKBOX_MASK_POSITIONHOLD))) { global.state.navigationMode=NAVIGATION_MODE_OFF; // we will be turning control back over to the pilot. reset_pilot_control(); } } #endif // read the receiver read_rx(); // turn on the LED when we are stable and the gps has 5 satelites or more #if (GPS_TYPE==NO_GPS) lib_digitalio_setoutput(LED1_OUTPUT, (global.state.stable==0)==LED1_ON); #else lib_digitalio_setoutput(LED1_OUTPUT, (!(global.state.stable && global.gps.numSatelites>=5))==LED1_ON); #endif // get the angle error. Angle error is the difference between our current attitude and our desired attitude. // It can be set by navigation, or by the pilot, etc. fixedpointnum angleError[3]; // let the pilot control the aircraft. get_angle_error_from_pilot_input(angleError); #if (GPS_TYPE!=NO_GPS) // read the gps unsigned char gotNewGpsReading=read_gps(); // if we are navigating, use navigation to determine our desired attitude (tilt angles) if (global.state.navigationMode!=NAVIGATION_MODE_OFF) { // we are navigating navigation_set_angle_error(gotNewGpsReading,angleError); } #endif if (global.rxValues[THROTTLE_INDEX]<FPSTICKLOW) { // We are probably on the ground. Don't accumnulate error when we can't correct it reset_pilot_control(); // bleed off integrated error by averaging in a value of zero lib_fp_lowpassfilter(&global.integratedAngleError[ROLL_INDEX],0L,global.timesliver>>TIMESLIVEREXTRASHIFT,FIXEDPOINTONEOVERONEFOURTH,0); lib_fp_lowpassfilter(&global.integratedAngleError[PITCH_INDEX],0L,global.timesliver>>TIMESLIVEREXTRASHIFT,FIXEDPOINTONEOVERONEFOURTH,0); lib_fp_lowpassfilter(&global.integratedAngleError[YAW_INDEX],0L,global.timesliver>>TIMESLIVEREXTRASHIFT,FIXEDPOINTONEOVERONEFOURTH,0); } #ifndef NO_AUTOTUNE // let autotune adjust the angle error if the pilot has autotune turned on if (global.activeCheckboxItems & CHECKBOX_MASK_AUTOTUNE) { if (!(global.previousActiveCheckboxItems & CHECKBOX_MASK_AUTOTUNE)) { autotune(angleError,AUTOTUNE_STARTING); // tell autotune that we just started autotuning } else { autotune(angleError,AUTOTUNE_TUNING); // tell autotune that we are in the middle of autotuning } } else if (global.previousActiveCheckboxItems & CHECKBOX_MASK_AUTOTUNE) { autotune(angleError,AUTOTUNE_STOPPING); // tell autotune that we just stopped autotuning } #endif // This gets reset every loop cycle // keep a flag to indicate whether we shoud apply altitude hold. The pilot can turn it on or // uncrashability/autopilot mode can turn it on. global.state.altitudeHold=0; if (global.activeCheckboxItems & CHECKBOX_MASK_ALTHOLD) { global.state.altitudeHold=1; if (!(global.previousActiveCheckboxItems & CHECKBOX_MASK_ALTHOLD)) { // we just turned on alt hold. Remember our current alt. as our target global.altitudeHoldDesiredAltitude=global.altitude; global.integratedAltitudeError=0; } } fixedpointnum throttleOutput; #ifndef NO_AUTOPILOT // autopilot is available if (global.activeCheckboxItems & CHECKBOX_MASK_AUTOPILOT) { if (!(global.previousActiveCheckboxItems & CHECKBOX_MASK_AUTOPILOT)) { // let autopilot know to transition to the starting state autopilot(AUTOPILOT_STARTING); } else { // autopilot normal run state autopilot(AUTOPILOT_RUNNING); } } else if (global.previousActiveCheckboxItems & CHECKBOX_MASK_AUTOPILOT) { // tell autopilot that we just stopped autotuning autopilot(AUTOPILOT_STOPPING); } else { // get the pilot's throttle component // convert from fixedpoint -1 to 1 to fixedpoint 0 to 1 throttleOutput=(global.rxValues[THROTTLE_INDEX]>>1)+FIXEDPOINTCONSTANT(.5)+FPTHROTTLETOMOTOROFFSET; } #else // get the pilot's throttle component // convert from fixedpoint -1 to 1 to fixedpoint 0 to 1 throttleOutput=(global.rxValues[THROTTLE_INDEX]>>1)+FIXEDPOINTCONSTANT(.5)+FPTHROTTLETOMOTOROFFSET; #endif #ifndef NO_UNCRASHABLE uncrashable(gotNewGpsReading,angleError,&throttleOutput); #endif #if (BAROMETER_TYPE!=NO_BAROMETER) // check for altitude hold and adjust the throttle output accordingly if (global.state.altitudeHold) { global.integratedAltitudeError+=lib_fp_multiply(global.altitudeHoldDesiredAltitude-global.altitude,global.timesliver); lib_fp_constrain(&global.integratedAltitudeError,-INTEGRATED_ANGLE_ERROR_LIMIT,INTEGRATED_ANGLE_ERROR_LIMIT); // don't let the integrated error get too high // do pid for the altitude hold and add it to the throttle output throttleOutput+=lib_fp_multiply(global.altitudeHoldDesiredAltitude-global.altitude,settings.pid_pgain[ALTITUDE_INDEX])-lib_fp_multiply(global.altitudeVelocity,settings.pid_dgain[ALTITUDE_INDEX])+lib_fp_multiply(global.integratedAltitudeError,settings.pid_igain[ALTITUDE_INDEX]); } #endif #ifndef NO_AUTOTHROTTLE if ((global.activeCheckboxItems & CHECKBOX_MASK_AUTOTHROTTLE) || global.state.altitudeHold) { if (global.estimatedDownVector[Z_INDEX]>FIXEDPOINTCONSTANT(.3)) { // Divide the throttle by the throttleOutput by the z component of the down vector // This is probaly the slow way, but it's a way to do fixed point division fixedpointnum recriprocal=lib_fp_invsqrt(global.estimatedDownVector[Z_INDEX]); recriprocal=lib_fp_multiply(recriprocal,recriprocal); throttleOutput=lib_fp_multiply(throttleOutput-AUTOTHROTTLE_DEAD_AREA,recriprocal)+AUTOTHROTTLE_DEAD_AREA; } } #endif #ifndef NO_FAILSAFE // if we don't hear from the receiver for over a second, try to land safely if (lib_timers_gettimermicroseconds(global.failsafeTimer)>1000000L) { throttleOutput=FPFAILSAFEMOTOROUTPUT; // make sure we are level! angleError[ROLL_INDEX]=-global.currentEstimatedEulerAttitude[ROLL_INDEX]; angleError[PITCH_INDEX]=-global.currentEstimatedEulerAttitude[PITCH_INDEX]; } #endif // calculate output values. Output values will range from 0 to 1.0 // calculate pid outputs based on our angleErrors as inputs fixedpointnum pidOutput[3]; // Gain Scheduling essentialy modifies the gains depending on // throttle level. If GAIN_SCHEDULING_FACTOR is 1.0, it multiplies PID outputs by 1.5 when at full throttle, // 1.0 when at mid throttle, and .5 when at zero throttle. This helps // eliminate the wobbles when decending at low throttle. fixedpointnum gainSchedulingMultiplier=lib_fp_multiply(throttleOutput-FIXEDPOINTCONSTANT(.5),FIXEDPOINTCONSTANT(GAIN_SCHEDULING_FACTOR))+FIXEDPOINTONE; for (int x=0;x<3;++x) { global.integratedAngleError[x]+=lib_fp_multiply(angleError[x],global.timesliver); // don't let the integrated error get too high (windup) lib_fp_constrain(&global.integratedAngleError[x],-INTEGRATED_ANGLE_ERROR_LIMIT,INTEGRATED_ANGLE_ERROR_LIMIT); // do the attitude pid pidOutput[x]=lib_fp_multiply(angleError[x],settings.pid_pgain[x])-lib_fp_multiply(global.gyrorate[x],settings.pid_dgain[x])+(lib_fp_multiply(global.integratedAngleError[x],settings.pid_igain[x])>>4); // add gain scheduling. pidOutput[x]=lib_fp_multiply(gainSchedulingMultiplier,pidOutput[x]); } lib_fp_constrain(&throttleOutput,0,FIXEDPOINTONE); // Keep throttle output between 0 and 1 compute_mix(throttleOutput, pidOutput); // aircraft type dependent mixes #if (NUM_SERVOS>0) // do not update servos during unarmed calibration of sensors which are sensitive to vibration if (global.state.armed || (!global.state.calibratingAccAndGyro)) write_servo_outputs(); #endif write_motor_outputs(); }
int main (int argc, char **argv) { int file; int16_t temp; uint8_t data[2] = {0}; Triplet a_bias = {0}, g_bias = {0}, m_bias = {0}; FTriplet m_scale; int opt, option_index, help = 0, option_dump = 0; OptionMode option_mode = OPTION_MODE_ANGLES; float declination = 0.0; while ((opt = getopt_long(argc, argv, "d:hm:u", long_options, &option_index )) != -1) { switch (opt) { case 'd' : declination = atof (optarg); break; case 'm' : if (strcmp (optarg, "sensor") == 0) option_mode = OPTION_MODE_SENSOR; else if (strcmp (optarg, "angles") == 0) option_mode = OPTION_MODE_ANGLES; else help = 1; break; case 'u' : option_dump = 1; break; default: help = 1; break; } } if (help || argv[optind] != NULL) { printf ("%s [--mode <sensor|angles>] [--dump]\n", argv[0]); return 0; } if (!read_bias_files (&a_bias, &g_bias, &m_bias, &m_scale)) return 1; file = init_device (I2C_DEV_NAME); if (file == 0) return 1; if (option_dump) { dump_config_registers(file); printf ("\n"); } init_gyro(file, GYRO_SCALE_245DPS); init_mag(file, MAG_SCALE_2GS); init_acc(file, ACCEL_SCALE_2G); // temperature is a 12-bit value: cut out 4 highest bits read_bytes (file, XM_ADDRESS, OUT_TEMP_L_XM, &data[0], 2); temp = (((data[1] & 0x0f) << 8) | data[0]); printf ("Temperature: %d\n", temp); printf ("Temperature: %d\n", temp); if (option_mode == OPTION_MODE_SENSOR) printf (" Gyroscope (deg/s) | Magnetometer (mGs) | Accelerometer (mG)\n"); else printf (" Rotations (mag + acc):\n"); while (1) { FTriplet gyro, mag, acc, angles1; usleep (500000); read_gyro (file, g_bias, GYRO_SCALE_245DPS, &gyro); read_mag (file, m_bias, m_scale, MAG_SCALE_2GS, &mag); read_acc (file, a_bias, ACCEL_SCALE_2G, &acc); if (option_mode == OPTION_MODE_SENSOR) { printf ("gyro: %4.0f %4.0f %4.0f | ", gyro.x, gyro.y, gyro.z); printf ("mag: %4.0f %4.0f %4.0f | ", mag.x*1000, mag.y*1000, mag.z*1000); printf ("acc: %4.0f %4.0f %5.0f\n", acc.x*1000, acc.y*1000, acc.z*1000); } else { calculate_simple_angles (mag, acc, declination, &angles1); printf ("pitch: %4.0f, roll: %4.0f, yaw: %4.0f\n", angles1.x, angles1.y, angles1.z); } } return 0; }
int main(void) //Main program starts from here { double acc_Angle; int gyro_Angle; int filt_Angle; unsigned int pwm_value; init_adxl(); //Initialise accelerometer init_gyro(); //Initialise gyroscope init_devices1(); uart0_init(); //Initailize UART1 for serial communiaction start_timer4(); //Timer for timing calculations SetTunings(8.1,8,5); lcd_print(1,1,kp*10,4); lcd_print(1,6,ki*10,4); lcd_print(1,11,kd*10,4); while(1) { acc_Angle=0.1*acc_angle(); //Accelerometer angle gyro_Angle=gyro_Rate(); //Anugular rate from Gyroscope filt_Angle=comp_filter(acc_Angle,gyro_Angle); //Filtered angle after passing through Complementary filter Input=filt_Angle; //Input for error calculation of PID Compute(); //Calling PID if (Output>0) //Mapping PID output to velocity of motors { pwm_value = (Output+THRESHOLD); if(pwm_value>=255) { pwm_value=255; } set_PWM_value(pwm_value); forward(); } else if(Output<0) { pwm_value = (-Output)+THRESHOLD; if(pwm_value>=255) { pwm_value=255; } set_PWM_value(pwm_value); back(); } else if(Input==0) { stop(); } //_delay_ms(20); UDR0=0xFF; _delay_ms(1); UDR0=(uint8_t)(filt_Angle+100); _delay_ms(1); uint8_t op=(Output/2)+127; UDR0=op; } }