コード例 #1
0
ファイル: altitudehold.c プロジェクト: Grisson/cleanflight
int32_t calculateAltHoldThrottleAdjustment(int32_t vel_tmp, float accZ_tmp, float accZ_old)
{
    int32_t result = 0;
    int32_t error;
    int32_t setVel;

    if (!isThrustFacingDownwards(&attitude)) {
        return result;
    }

    // Altitude P-Controller

    if (!velocityControl) {
        error = constrain(AltHold - EstAlt, -500, 500);
        error = applyDeadband(error, 10); // remove small P parameter to reduce noise near zero position
        setVel = constrain((pidProfile()->P8[PIDALT] * error / 128), -300, +300); // limit velocity to +/- 3 m/s
    } else {
        setVel = setVelocity;
    }
    // Velocity PID-Controller

    // P
    error = setVel - vel_tmp;
    result = constrain((pidProfile()->P8[PIDVEL] * error / 32), -300, +300);

    // I
    errorVelocityI += (pidProfile()->I8[PIDVEL] * error);
    errorVelocityI = constrain(errorVelocityI, -(8192 * 200), (8192 * 200));
    result += errorVelocityI / 8192;     // I in range +/-200

    // D
    result -= constrain(pidProfile()->D8[PIDVEL] * (accZ_tmp + accZ_old) / 512, -150, 150);

    return result;
}
コード例 #2
0
ファイル: cms_menu_imu.c プロジェクト: Carlitoscadiz/inav
static long cmsx_FilterPerProfileRead(void)
{
    cmsx_dterm_lpf_hz = pidProfile()->dterm_lpf_hz;
    cmsx_gyroSoftLpf  = gyroConfig()->gyro_soft_lpf_hz;
    cmsx_yaw_p_limit  = pidProfile()->yaw_p_limit;
    cmsx_yaw_lpf_hz   = pidProfile()->yaw_lpf_hz;

    return 0;
}
コード例 #3
0
ファイル: cms_menu_imu.c プロジェクト: Carlitoscadiz/inav
static long cmsx_profileOtherOnEnter(void)
{
    profileIndexString[1] = '0' + tmpProfileIndex;

    cmsx_dtermSetpointWeight = pidProfile()->dtermSetpointWeight;
    cmsx_setpointRelaxRatio  = pidProfile()->setpointRelaxRatio;

    cmsx_angleStrength       = pidProfile()[PIDLEVEL].P;
    cmsx_horizonStrength     = pidProfile()[PIDLEVEL].I;
    cmsx_horizonTransition   = pidProfile()[PIDLEVEL].D;

    return 0;
}
コード例 #4
0
ファイル: config.c プロジェクト: LupinIII/cleanflight
static void activateConfig(void)
{
    activateControlRateConfig();

    resetAdjustmentStates();

    useRcControlsConfig(modeActivationProfile()->modeActivationConditions);

    pidInitFilters(pidProfile());

#ifdef GPS
    gpsUsePIDs(pidProfile());
#endif

    useFailsafeConfig();
    setAccelerationTrims(&sensorTrims()->accZero);
    accelerationFilterInit(accelerometerConfig()->acc_cut_hz);

#ifdef USE_SERVOS
    mixerUseConfigs(servoProfile()->servoConf);
#endif

#ifdef GPS
    recalculateMagneticDeclination();
#endif

#ifdef VTX
    initVTXState();
#endif

    static imuRuntimeConfig_t imuRuntimeConfig;
    imuRuntimeConfig.dcm_kp = imuConfig()->dcm_kp / 10000.0f;
    imuRuntimeConfig.dcm_ki = imuConfig()->dcm_ki / 10000.0f;
    imuRuntimeConfig.acc_cut_hz = accelerometerConfig()->acc_cut_hz;
    imuRuntimeConfig.acc_unarmedcal = accelerometerConfig()->acc_unarmedcal;
    imuRuntimeConfig.small_angle = imuConfig()->small_angle;

    imuConfigure(
        &imuRuntimeConfig,
        &accelerometerConfig()->accDeadband,
        accelerometerConfig()->accz_lpf_cutoff,
        throttleCorrectionConfig()->throttle_correction_angle
    );
}
コード例 #5
0
ファイル: gtune.c プロジェクト: Bengt-M/Triflight
void init_Gtune(void)
{
    uint8_t i;
        if (pidProfile()->pidController == 2) {
	    floatPID = true;                                                        // LuxFloat is using float values for PID settings
	} else {
	    floatPID = false;
	}
	updateDelayCycles();
	for (i = 0; i < 3; i++) {
        if ((gtuneConfig()->gtune_hilimP[i] && gtuneConfig()->gtune_lolimP[i] > gtuneConfig()->gtune_hilimP[i]) || (motorCount < 4 && i == FD_YAW)) { // User config error disable axisis for tuning
            gtuneConfig()->gtune_hilimP[i] = 0;                                    // Disable YAW tuning for everything below a quadcopter
        }
        if(pidProfile()->P8[i] < gtuneConfig()->gtune_lolimP[i]) {
            pidProfile()->P8[i] = gtuneConfig()->gtune_lolimP[i];
        }
        result_P64[i] = (int16_t)pidProfile()->P8[i] << 6;                    // 6 bit extra resolution for P.
        OldError[i] = 0;
        time_skip[i] = delay_cycles;
    }
}
コード例 #6
0
ファイル: mw.c プロジェクト: JoachimF/cleanflight
void updateMagHold(void)
{
    if (ABS(rcCommand[YAW]) < 15 && FLIGHT_MODE(MAG_MODE)) {
        int16_t dif = DECIDEGREES_TO_DEGREES(attitude.values.yaw) - magHold;
        if (dif <= -180)
            dif += 360;
        if (dif >= +180)
            dif -= 360;
        dif *= -rcControlsConfig()->yaw_control_direction;
        if (STATE(SMALL_ANGLE))
            rcCommand[YAW] -= dif * pidProfile()->P8[PIDMAG] / 30;    // 18 deg
    } else
        magHold = DECIDEGREES_TO_DEGREES(attitude.values.yaw);
}
コード例 #7
0
ファイル: cleanflight_fc.c プロジェクト: LupinIII/cleanflight
void subTaskPidController(void)
{
    const uint32_t startTime = micros();

    // PID - note this is function pointer set by setPIDController()
    pidLuxFloat(
        pidProfile(),
        currentControlRateProfile,
        imuConfig()->max_angle_inclination,
        &accelerometerConfig()->accelerometerTrims,
        rxConfig()
    );

    if (debugMode == DEBUG_PIDLOOP) {debug[2] = micros() - startTime;}
}
コード例 #8
0
ファイル: mw.c プロジェクト: JoachimF/cleanflight
void annexCode(void)
{
    int32_t tmp, tmp2;
    int32_t axis, prop1 = 0, prop2;

    // PITCH & ROLL only dynamic PID adjustment,  depending on throttle value
    if (rcData[THROTTLE] < currentControlRateProfile->tpa_breakpoint) {
        prop2 = 100;
    } else {
        if (rcData[THROTTLE] < 2000) {
            prop2 = 100 - (uint16_t)currentControlRateProfile->dynThrPID * (rcData[THROTTLE] - currentControlRateProfile->tpa_breakpoint) / (2000 - currentControlRateProfile->tpa_breakpoint);
        } else {
            prop2 = 100 - currentControlRateProfile->dynThrPID;
        }
    }

    for (axis = 0; axis < 3; axis++) {
        tmp = MIN(ABS(rcData[axis] - rxConfig()->midrc), 500);
        if (axis == ROLL || axis == PITCH) {
            if (rcControlsConfig()->deadband) {
                if (tmp > rcControlsConfig()->deadband) {
                    tmp -= rcControlsConfig()->deadband;
                } else {
                    tmp = 0;
                }
            }

            tmp2 = tmp / 100;
            rcCommand[axis] = lookupPitchRollRC[tmp2] + (tmp - tmp2 * 100) * (lookupPitchRollRC[tmp2 + 1] - lookupPitchRollRC[tmp2]) / 100;
            prop1 = 100 - (uint16_t)currentControlRateProfile->rates[axis] * tmp / 500;
            prop1 = (uint16_t)prop1 * prop2 / 100;
        } else if (axis == YAW) {
            if (rcControlsConfig()->yaw_deadband) {
                if (tmp > rcControlsConfig()->yaw_deadband) {
                    tmp -= rcControlsConfig()->yaw_deadband;
                } else {
                    tmp = 0;
                }
            }
            tmp2 = tmp / 100;
            rcCommand[axis] = (lookupYawRC[tmp2] + (tmp - tmp2 * 100) * (lookupYawRC[tmp2 + 1] - lookupYawRC[tmp2]) / 100) * -rcControlsConfig()->yaw_control_direction;
            prop1 = 100 - (uint16_t)currentControlRateProfile->rates[axis] * ABS(tmp) / 500;
        }
        // FIXME axis indexes into pids.  use something like lookupPidIndex(rc_alias_e alias) to reduce coupling.
        dynP8[axis] = (uint16_t)pidProfile()->P8[axis] * prop1 / 100;
        dynI8[axis] = (uint16_t)pidProfile()->I8[axis] * prop1 / 100;
        dynD8[axis] = (uint16_t)pidProfile()->D8[axis] * prop1 / 100;

        // non coupled PID reduction scaler used in PID controller 1 and PID controller 2. YAW TPA disabled. 100 means 100% of the pids
        if (axis == YAW) {
            PIDweight[axis] = 100;
        }
        else {
            PIDweight[axis] = prop2;
        }

        if (rcData[axis] < rxConfig()->midrc)
            rcCommand[axis] = -rcCommand[axis];
    }

    tmp = constrain(rcData[THROTTLE], rxConfig()->mincheck, PWM_RANGE_MAX);
    tmp = (uint32_t)(tmp - rxConfig()->mincheck) * PWM_RANGE_MIN / (PWM_RANGE_MAX - rxConfig()->mincheck);       // [MINCHECK;2000] -> [0;1000]
    tmp2 = tmp / 100;
    rcCommand[THROTTLE] = lookupThrottleRC[tmp2] + (tmp - tmp2 * 100) * (lookupThrottleRC[tmp2 + 1] - lookupThrottleRC[tmp2]) / 100;    // [0;1000] -> expo -> [MINTHROTTLE;MAXTHROTTLE]

    if (FLIGHT_MODE(HEADFREE_MODE)) {
        float radDiff = degreesToRadians(DECIDEGREES_TO_DEGREES(attitude.values.yaw) - headFreeModeHold);
        float cosDiff = cos_approx(radDiff);
        float sinDiff = sin_approx(radDiff);
        int16_t rcCommand_PITCH = rcCommand[PITCH] * cosDiff + rcCommand[ROLL] * sinDiff;
        rcCommand[ROLL] = rcCommand[ROLL] * cosDiff - rcCommand[PITCH] * sinDiff;
        rcCommand[PITCH] = rcCommand_PITCH;
    }

    if (ARMING_FLAG(ARMED)) {
        LED0_ON;
    } else {
        if (IS_RC_MODE_ACTIVE(BOXARM) == 0) {
            ENABLE_ARMING_FLAG(OK_TO_ARM);
        }

        if (!imuIsAircraftArmable(armingConfig()->max_arm_angle)) {
            DISABLE_ARMING_FLAG(OK_TO_ARM);
            debug[3] = ARMING_FLAG(OK_TO_ARM);
        }

        if (isCalibrating() || isSystemOverloaded()) {
            warningLedFlash();
            DISABLE_ARMING_FLAG(OK_TO_ARM);
        } else {
            if (ARMING_FLAG(OK_TO_ARM)) {
                warningLedDisable();
            } else {
                warningLedFlash();
            }
        }

        debug[3] = ARMING_FLAG(OK_TO_ARM);

        warningLedUpdate();
    }

    // Read out gyro temperature. can use it for something somewhere. maybe get MCU temperature instead? lots of fun possibilities.
    if (gyro.temperature)
        gyro.temperature(&telemTemperature1);
}
コード例 #9
0
ファイル: boot.c プロジェクト: FenomPL/cleanflight
void init(void)
{
    drv_pwm_config_t pwm_params;

    printfSupportInit();

    initEEPROM();

    ensureEEPROMContainsValidData();
    readEEPROM();

    systemState |= SYSTEM_STATE_CONFIG_LOADED;

#ifdef STM32F303
    // start fpu
    SCB->CPACR = (0x3 << (10*2)) | (0x3 << (11*2));
#endif

#ifdef STM32F303xC
    SetSysClock();
#endif
#ifdef STM32F10X
    // Configure the System clock frequency, HCLK, PCLK2 and PCLK1 prescalers
    // Configure the Flash Latency cycles and enable prefetch buffer
    SetSysClock(systemConfig()->emf_avoidance);
#endif
    i2cSetOverclock(systemConfig()->i2c_highspeed);

    systemInit();

#ifdef USE_HARDWARE_REVISION_DETECTION
    detectHardwareRevision();
#endif

    // Latch active features to be used for feature() in the remainder of init().
    latchActiveFeatures();

    // initialize IO (needed for all IO operations)
    IOInitGlobal();

    debugMode = debugConfig()->debug_mode;

#ifdef USE_EXTI
    EXTIInit();
#endif

#ifdef ALIENFLIGHTF3
    if (hardwareRevision == AFF3_REV_1) {
        ledInit(false);
    } else {
        ledInit(true);
    }
#else
    ledInit(false);
#endif

#ifdef BEEPER
    beeperConfig_t beeperConfig = {
        .gpioPeripheral = BEEP_PERIPHERAL,
        .gpioPin = BEEP_PIN,
        .gpioPort = BEEP_GPIO,
#ifdef BEEPER_INVERTED
        .gpioMode = Mode_Out_PP,
        .isInverted = true
#else
        .gpioMode = Mode_Out_OD,
        .isInverted = false
#endif
    };
#ifdef NAZE
    if (hardwareRevision >= NAZE32_REV5) {
        // naze rev4 and below used opendrain to PNP for buzzer. Rev5 and above use PP to NPN.
        beeperConfig.gpioMode = Mode_Out_PP;
        beeperConfig.isInverted = true;
    }
#endif

    beeperInit(&beeperConfig);
#endif

#ifdef BUTTONS
    buttonsInit();

    if (!isMPUSoftReset()) {
        buttonsHandleColdBootButtonPresses();
    }
#endif

#ifdef SPEKTRUM_BIND
    if (feature(FEATURE_RX_SERIAL)) {
        switch (rxConfig()->serialrx_provider) {
            case SERIALRX_SPEKTRUM1024:
            case SERIALRX_SPEKTRUM2048:
                // Spektrum satellite binding if enabled on startup.
                // Must be called before that 100ms sleep so that we don't lose satellite's binding window after startup.
                // The rest of Spektrum initialization will happen later - via spektrumInit()
                spektrumBind(rxConfig());
                break;
        }
    }
#endif

    delay(100);

    timerInit();  // timer must be initialized before any channel is allocated

    dmaInit();


    serialInit(feature(FEATURE_SOFTSERIAL));

    mixerInit(customMotorMixer(0));
#ifdef USE_SERVOS
    mixerInitServos(customServoMixer(0));
#endif

    memset(&pwm_params, 0, sizeof(pwm_params));

#ifdef SONAR
    const sonarHardware_t *sonarHardware = NULL;
    sonarGPIOConfig_t sonarGPIOConfig;
    if (feature(FEATURE_SONAR)) {
        bool usingCurrentMeterIOPins = (feature(FEATURE_AMPERAGE_METER) && batteryConfig()->amperageMeterSource == AMPERAGE_METER_ADC);
        sonarHardware = sonarGetHardwareConfiguration(usingCurrentMeterIOPins);
        sonarGPIOConfig.triggerGPIO = sonarHardware->trigger_gpio;
        sonarGPIOConfig.triggerPin = sonarHardware->trigger_pin;
        sonarGPIOConfig.echoGPIO = sonarHardware->echo_gpio;
        sonarGPIOConfig.echoPin = sonarHardware->echo_pin;
        pwm_params.sonarGPIOConfig = &sonarGPIOConfig;
    }
#endif

    // when using airplane/wing mixer, servo/motor outputs are remapped
    if (mixerConfig()->mixerMode == MIXER_AIRPLANE || mixerConfig()->mixerMode == MIXER_FLYING_WING || mixerConfig()->mixerMode == MIXER_CUSTOM_AIRPLANE)
        pwm_params.airplane = true;
    else
        pwm_params.airplane = false;
#if defined(USE_UART2) && defined(STM32F10X)
    pwm_params.useUART2 = doesConfigurationUsePort(SERIAL_PORT_UART2);
#endif
#if defined(USE_UART3)
    pwm_params.useUART3 = doesConfigurationUsePort(SERIAL_PORT_UART3);
#endif
#if defined(USE_UART4)
    pwm_params.useUART4 = doesConfigurationUsePort(SERIAL_PORT_UART4);
#endif
#if defined(USE_UART5)
    pwm_params.useUART5 = doesConfigurationUsePort(SERIAL_PORT_UART5);
#endif
    pwm_params.useVbat = feature(FEATURE_VBAT);
    pwm_params.useSoftSerial = feature(FEATURE_SOFTSERIAL);
    pwm_params.useParallelPWM = feature(FEATURE_RX_PARALLEL_PWM);
    pwm_params.useRSSIADC = feature(FEATURE_RSSI_ADC);
    pwm_params.useCurrentMeterADC = (
        feature(FEATURE_AMPERAGE_METER)
        && batteryConfig()->amperageMeterSource == AMPERAGE_METER_ADC
    );
    pwm_params.useLEDStrip = feature(FEATURE_LED_STRIP);
    pwm_params.usePPM = feature(FEATURE_RX_PPM);
    pwm_params.useSerialRx = feature(FEATURE_RX_SERIAL);
#ifdef SONAR
    pwm_params.useSonar = feature(FEATURE_SONAR);
#endif

#ifdef USE_SERVOS
    pwm_params.useServos = isMixerUsingServos();
    pwm_params.useChannelForwarding = feature(FEATURE_CHANNEL_FORWARDING);
    pwm_params.servoCenterPulse = servoConfig()->servoCenterPulse;
    pwm_params.servoPwmRate = servoConfig()->servo_pwm_rate;
#endif

    pwm_params.useOneshot = feature(FEATURE_ONESHOT125);
    pwm_params.motorPwmRate = motorConfig()->motor_pwm_rate;
    pwm_params.idlePulse = calculateMotorOff();
    if (pwm_params.motorPwmRate > 500)
        pwm_params.idlePulse = 0; // brushed motors

    pwmRxInit();

    // pwmInit() needs to be called as soon as possible for ESC compatibility reasons
    pwmIOConfiguration_t *pwmIOConfiguration = pwmInit(&pwm_params);

    mixerUsePWMIOConfiguration(pwmIOConfiguration);

#ifdef DEBUG_PWM_CONFIGURATION
    debug[2] = pwmIOConfiguration->pwmInputCount;
    debug[3] = pwmIOConfiguration->ppmInputCount;
#endif

    if (!feature(FEATURE_ONESHOT125))
        motorControlEnable = true;

    systemState |= SYSTEM_STATE_MOTORS_READY;

#ifdef INVERTER
    initInverter();
#endif


#ifdef USE_SPI
    spiInit(SPI1);
    spiInit(SPI2);
#ifdef STM32F303xC
#ifdef ALIENFLIGHTF3
    if (hardwareRevision == AFF3_REV_2) {
        spiInit(SPI3);
    }
#else
    spiInit(SPI3);
#endif
#endif
#endif

#ifdef USE_HARDWARE_REVISION_DETECTION
    updateHardwareRevision();
#endif

#if defined(NAZE)
    if (hardwareRevision == NAZE32_SP) {
        serialRemovePort(SERIAL_PORT_SOFTSERIAL2);
    } else  {
        serialRemovePort(SERIAL_PORT_UART3);
    }
#endif

#if defined(SPRACINGF3) && defined(SONAR) && defined(USE_SOFTSERIAL2)
    if (feature(FEATURE_SONAR) && feature(FEATURE_SOFTSERIAL)) {
        serialRemovePort(SERIAL_PORT_SOFTSERIAL2);
    }
#endif

#if defined(SPRACINGF3MINI) && defined(SONAR) && defined(USE_SOFTSERIAL1)
    if (feature(FEATURE_SONAR) && feature(FEATURE_SOFTSERIAL)) {
        serialRemovePort(SERIAL_PORT_SOFTSERIAL1);
    }
#endif


#ifdef USE_I2C
#if defined(NAZE)
    if (hardwareRevision != NAZE32_SP) {
        i2cInit(I2C_DEVICE);
    } else {
        if (!doesConfigurationUsePort(SERIAL_PORT_UART3)) {
            i2cInit(I2C_DEVICE);
        }
    }
#elif defined(CC3D)
    if (!doesConfigurationUsePort(SERIAL_PORT_UART3)) {
        i2cInit(I2C_DEVICE);
    }
#else
    i2cInit(I2C_DEVICE);
#endif
#endif

#ifdef USE_ADC
    drv_adc_config_t adc_params;

    adc_params.channelMask = 0;

#ifdef ADC_BATTERY
    adc_params.channelMask = (feature(FEATURE_VBAT) ? ADC_CHANNEL_MASK(ADC_BATTERY) : 0);
#endif
#ifdef ADC_RSSI
    adc_params.channelMask |= (feature(FEATURE_RSSI_ADC) ? ADC_CHANNEL_MASK(ADC_RSSI) : 0);
#endif
#ifdef ADC_AMPERAGE
    adc_params.channelMask |=  (feature(FEATURE_AMPERAGE_METER) ? ADC_CHANNEL_MASK(ADC_AMPERAGE) : 0);
#endif

#ifdef ADC_POWER_12V
    adc_params.channelMask |= ADC_CHANNEL_MASK(ADC_POWER_12V);
#endif
#ifdef ADC_POWER_5V
    adc_params.channelMask |= ADC_CHANNEL_MASK(ADC_POWER_5V);
#endif
#ifdef ADC_POWER_3V
    adc_params.channelMask |= ADC_CHANNEL_MASK(ADC_POWER_3V);
#endif

#ifdef NAZE
    // optional ADC5 input on rev.5 hardware
    adc_params.channelMask |= (hardwareRevision >= NAZE32_REV5) ? ADC_CHANNEL_MASK(ADC_EXTERNAL) : 0;
#endif

    adcInit(&adc_params);
#endif

    initBoardAlignment();

#ifdef DISPLAY
    if (feature(FEATURE_DISPLAY)) {
        displayInit();
    }
#endif

#ifdef NAZE
    if (hardwareRevision < NAZE32_REV5) {
        gyroConfig()->gyro_sync = 0;
    }
#endif

    if (!sensorsAutodetect()) {
        // if gyro was not detected due to whatever reason, we give up now.
        failureMode(FAILURE_MISSING_ACC);
    }

    systemState |= SYSTEM_STATE_SENSORS_READY;

    flashLedsAndBeep();

    mspInit();
    mspSerialInit();

    const uint16_t pidPeriodUs = US_FROM_HZ(gyro.sampleFrequencyHz);
    pidSetTargetLooptime(pidPeriodUs * gyroConfig()->pid_process_denom);
    pidInitFilters(pidProfile());

#ifdef USE_SERVOS
    mixerInitialiseServoFiltering(targetPidLooptime);
#endif

    imuInit();


#ifdef USE_CLI
    cliInit();
#endif

    failsafeInit();

    rxInit(modeActivationProfile()->modeActivationConditions);

#ifdef GPS
    if (feature(FEATURE_GPS)) {
        gpsInit();
        navigationInit(pidProfile());
    }
#endif

#ifdef SONAR
    if (feature(FEATURE_SONAR)) {
        sonarInit(sonarHardware);
    }
#endif

#ifdef LED_STRIP
    ledStripInit();

    if (feature(FEATURE_LED_STRIP)) {
        ledStripEnable();
    }
#endif

#ifdef TELEMETRY
    if (feature(FEATURE_TELEMETRY)) {
        telemetryInit();
    }
#endif

#ifdef USB_CABLE_DETECTION
    usbCableDetectInit();
#endif

#ifdef TRANSPONDER
    if (feature(FEATURE_TRANSPONDER)) {
        transponderInit(transponderConfig()->data);
        transponderEnable();
        transponderStartRepeating();
        systemState |= SYSTEM_STATE_TRANSPONDER_ENABLED;
    }
#endif

#ifdef USE_FLASHFS
#ifdef NAZE
    if (hardwareRevision == NAZE32_REV5) {
        m25p16_init();
    }
#elif defined(USE_FLASH_M25P16)
    m25p16_init();
#endif

    flashfsInit();
#endif

#ifdef USE_SDCARD
    bool sdcardUseDMA = false;

    sdcardInsertionDetectInit();

#ifdef SDCARD_DMA_CHANNEL_TX

#if defined(LED_STRIP) && defined(WS2811_DMA_CHANNEL)
    // Ensure the SPI Tx DMA doesn't overlap with the led strip
    sdcardUseDMA = !feature(FEATURE_LED_STRIP) || SDCARD_DMA_CHANNEL_TX != WS2811_DMA_CHANNEL;
#else
    sdcardUseDMA = true;
#endif

#endif

    sdcard_init(sdcardUseDMA);

    afatfs_init();
#endif

#ifdef BLACKBOX
    initBlackbox();
#endif

    if (mixerConfig()->mixerMode == MIXER_GIMBAL) {
        accSetCalibrationCycles(CALIBRATING_ACC_CYCLES);
    }
    gyroSetCalibrationCycles(CALIBRATING_GYRO_CYCLES);
#ifdef BARO
    baroSetCalibrationCycles(CALIBRATING_BARO_CYCLES);
#endif

    // start all timers
    // TODO - not implemented yet
    timerStart();

    ENABLE_STATE(SMALL_ANGLE);
    DISABLE_ARMING_FLAG(PREVENT_ARMING);

#ifdef SOFTSERIAL_LOOPBACK
    // FIXME this is a hack, perhaps add a FUNCTION_LOOPBACK to support it properly
    loopbackPort = (serialPort_t*)&(softSerialPorts[0]);
    if (!loopbackPort->vTable) {
        loopbackPort = openSoftSerial(0, NULL, 19200, SERIAL_NOT_INVERTED);
    }
    serialPrint(loopbackPort, "LOOPBACK\r\n");
#endif


    if (feature(FEATURE_VBAT)) {
        // Now that everything has powered up the voltage and cell count be determined.

        voltageMeterInit();
        batteryInit();
    }

    if (feature(FEATURE_AMPERAGE_METER)) {
        amperageMeterInit();
    }

#ifdef DISPLAY
    if (feature(FEATURE_DISPLAY)) {
#ifdef USE_OLED_GPS_DEBUG_PAGE_ONLY
        displayShowFixedPage(PAGE_GPS);
#else
        displayResetPageCycling();
        displayEnablePageCycling();
#endif
    }
#endif

#ifdef CJMCU
    LED2_ON;
#endif

    // Latch active features AGAIN since some may be modified by init().
    latchActiveFeatures();
    motorControlEnable = true;

    systemState |= SYSTEM_STATE_READY;
}

#ifdef SOFTSERIAL_LOOPBACK
void processLoopback(void) {
    if (loopbackPort) {
        uint8_t bytesWaiting;
        while ((bytesWaiting = serialRxBytesWaiting(loopbackPort))) {
            uint8_t b = serialRead(loopbackPort);
            serialWrite(loopbackPort, b);
        };
    }
}
#else
#define processLoopback()
#endif

void configureScheduler(void)
{
    schedulerInit();
    setTaskEnabled(TASK_SYSTEM, true);

    uint16_t gyroPeriodUs = US_FROM_HZ(gyro.sampleFrequencyHz);
    rescheduleTask(TASK_GYRO, gyroPeriodUs);
    setTaskEnabled(TASK_GYRO, true);

    rescheduleTask(TASK_PID, gyroPeriodUs);
    setTaskEnabled(TASK_PID, true);

    if (sensors(SENSOR_ACC)) {
        setTaskEnabled(TASK_ACCEL, true);
    }

    setTaskEnabled(TASK_ATTITUDE, sensors(SENSOR_ACC));
    setTaskEnabled(TASK_SERIAL, true);
#ifdef BEEPER
    setTaskEnabled(TASK_BEEPER, true);
#endif
    setTaskEnabled(TASK_BATTERY, feature(FEATURE_VBAT) || feature(FEATURE_AMPERAGE_METER));
    setTaskEnabled(TASK_RX, true);
#ifdef GPS
    setTaskEnabled(TASK_GPS, feature(FEATURE_GPS));
#endif
#ifdef MAG
    setTaskEnabled(TASK_COMPASS, sensors(SENSOR_MAG));
#if defined(MPU6500_SPI_INSTANCE) && defined(USE_MAG_AK8963)
    // fixme temporary solution for AK6983 via slave I2C on MPU9250
    rescheduleTask(TASK_COMPASS, 1000000 / 40);
#endif
#endif
#ifdef BARO
    setTaskEnabled(TASK_BARO, sensors(SENSOR_BARO));
#endif
#ifdef SONAR
    setTaskEnabled(TASK_SONAR, sensors(SENSOR_SONAR));
#endif
#if defined(BARO) || defined(SONAR)
    setTaskEnabled(TASK_ALTITUDE, sensors(SENSOR_BARO) || sensors(SENSOR_SONAR));
#endif
#ifdef DISPLAY
    setTaskEnabled(TASK_DISPLAY, feature(FEATURE_DISPLAY));
#endif
#ifdef TELEMETRY
    setTaskEnabled(TASK_TELEMETRY, feature(FEATURE_TELEMETRY));
#endif
#ifdef LED_STRIP
    setTaskEnabled(TASK_LEDSTRIP, feature(FEATURE_LED_STRIP));
#endif
#ifdef TRANSPONDER
    setTaskEnabled(TASK_TRANSPONDER, feature(FEATURE_TRANSPONDER));
#endif
}
コード例 #10
0
ファイル: cleanflight_fc.c プロジェクト: LupinIII/cleanflight
/*
This function processes RX dependent coefficients when new RX commands are available
Those are: TPA, throttle expo
*/
static void updateRcCommands(void)
{
    int32_t prop2;

    // PITCH & ROLL only dynamic PID adjustment,  depending on throttle value
    if (rcData[THROTTLE] < currentControlRateProfile->tpa_breakpoint) {
        prop2 = 100;
    } else {
        if (rcData[THROTTLE] < 2000) {
            prop2 = 100 - (uint16_t)currentControlRateProfile->dynThrPID * (rcData[THROTTLE] - currentControlRateProfile->tpa_breakpoint) / (2000 - currentControlRateProfile->tpa_breakpoint);
        } else {
            prop2 = 100 - currentControlRateProfile->dynThrPID;
        }
    }

    for (int axis = 0; axis < 3; axis++) {
        int32_t prop1;
        int32_t tmp = MIN(ABS(rcData[axis] - rxConfig()->midrc), 500);
        if (axis == ROLL || axis == PITCH) {
            if (rcControlsConfig()->deadband) {
                if (tmp > rcControlsConfig()->deadband) {
                    tmp -= rcControlsConfig()->deadband;
                } else {
                    tmp = 0;
                }
            }

            rcCommand[axis] = rcLookupPitchRoll(tmp);
            prop1 = 100 - (uint16_t)currentControlRateProfile->rates[axis] * tmp / 500;
            prop1 = (uint16_t)prop1 * prop2 / 100;
            // non coupled PID reduction scaler used in PID controller 1 and PID controller 2. 100 means 100% of the pids
            PIDweight[axis] = prop2;
        } else {
            if (rcControlsConfig()->yaw_deadband) {
                if (tmp > rcControlsConfig()->yaw_deadband) {
                    tmp -= rcControlsConfig()->yaw_deadband;
                } else {
                    tmp = 0;
                }
            }
            rcCommand[axis] = rcLookupYaw(tmp) * -rcControlsConfig()->yaw_control_direction;
            prop1 = 100 - (uint16_t)currentControlRateProfile->rates[axis] * ABS(tmp) / 500;
            // YAW TPA disabled.
            PIDweight[axis] = 100;
        }
#ifdef USE_PID_MW23
        // FIXME axis indexes into pids.  use something like lookupPidIndex(rc_alias_e alias) to reduce coupling.
        dynP8[axis] = (uint16_t)pidProfile()->P8[axis] * prop1 / 100;
        dynI8[axis] = (uint16_t)pidProfile()->I8[axis] * prop1 / 100;
        dynD8[axis] = (uint16_t)pidProfile()->D8[axis] * prop1 / 100;
#endif

        if (rcData[axis] < rxConfig()->midrc) {
            rcCommand[axis] = -rcCommand[axis];
        }
    }

    int32_t tmp = constrain(rcData[THROTTLE], rxConfig()->mincheck, PWM_RANGE_MAX);
    tmp = (uint32_t)(tmp - rxConfig()->mincheck) * PWM_RANGE_MIN / (PWM_RANGE_MAX - rxConfig()->mincheck);       // [MINCHECK;2000] -> [0;1000]
    rcCommand[THROTTLE] = rcLookupThrottle(tmp);

    if (FLIGHT_MODE(HEADFREE_MODE)) {
        float radDiff = degreesToRadians(DECIDEGREES_TO_DEGREES(attitude.values.yaw) - headFreeModeHold);
        float cosDiff = cos_approx(radDiff);
        float sinDiff = sin_approx(radDiff);
        int16_t rcCommand_PITCH = rcCommand[PITCH] * cosDiff + rcCommand[ROLL] * sinDiff;
        rcCommand[ROLL] = rcCommand[ROLL] * cosDiff - rcCommand[PITCH] * sinDiff;
        rcCommand[PITCH] = rcCommand_PITCH;
    }
}
コード例 #11
0
ファイル: mw.c プロジェクト: SINTEF-9012/cleanflight
/*
This function processes RX dependent coefficients when new RX commands are available
Those are: TPA, throttle expo
*/
void processRxDependentCoefficients(void) {

    int32_t tmp, tmp2;
    int32_t axis, prop1 = 0, prop2;

    // TODO: SINTEF JAKOB - Add offsets somewhere in this code, so that it is not affected by deadbands,
    // and so that it does not affect command stick-positions
    int16_t tmpThrottle = rcData[THROTTLE] + rxMspReadOffsetRC(&rxRuntimeConfig, THROTTLE);

    // PITCH & ROLL only dynamic PID adjustment,  depending on throttle value
    if (rcData[THROTTLE] < currentControlRateProfile->tpa_breakpoint) {
        prop2 = 100;
    } else {
        if (rcData[THROTTLE] < 2000) {
            prop2 = 100 - (uint16_t)currentControlRateProfile->dynThrPID * (rcData[THROTTLE] - currentControlRateProfile->tpa_breakpoint) / (2000 - currentControlRateProfile->tpa_breakpoint);
        } else {
            prop2 = 100 - currentControlRateProfile->dynThrPID;
        }
    }

    for (axis = 0; axis < 3; axis++) {
        tmp = MIN(ABS(rcData[axis] - rxConfig()->midrc), 500);
        if (axis == ROLL || axis == PITCH) {
            if (rcControlsConfig()->deadband) {
                if (tmp > rcControlsConfig()->deadband) {
                    tmp -= rcControlsConfig()->deadband;
                } else {
                    tmp = 0;
                }
            }
            tmp += rxMspReadOffsetRC(&rxRuntimeConfig, axis);

            tmp2 = tmp / 100;
            rcCommand[axis] = lookupPitchRollRC[tmp2] + (tmp - tmp2 * 100) * (lookupPitchRollRC[tmp2 + 1] - lookupPitchRollRC[tmp2]) / 100;
            prop1 = 100 - (uint16_t)currentControlRateProfile->rates[axis] * tmp / 500;
            prop1 = (uint16_t)prop1 * prop2 / 100;
        } else if (axis == YAW) {
            if (rcControlsConfig()->yaw_deadband) {
                if (tmp > rcControlsConfig()->yaw_deadband) {
                    tmp -= rcControlsConfig()->yaw_deadband;
                } else {
                    tmp = 0;
                }
            }
            tmp += rxMspReadOffsetRC(&rxRuntimeConfig, axis);

            tmp2 = tmp / 100;
            rcCommand[axis] = (lookupYawRC[tmp2] + (tmp - tmp2 * 100) * (lookupYawRC[tmp2 + 1] - lookupYawRC[tmp2]) / 100) * -rcControlsConfig()->yaw_control_direction;
            prop1 = 100 - (uint16_t)currentControlRateProfile->rates[axis] * ABS(tmp) / 500;
        }
#ifndef SKIP_PID_MW23
        // FIXME axis indexes into pids.  use something like lookupPidIndex(rc_alias_e alias) to reduce coupling.
        dynP8[axis] = (uint16_t)pidProfile()->P8[axis] * prop1 / 100;
        dynI8[axis] = (uint16_t)pidProfile()->I8[axis] * prop1 / 100;
        dynD8[axis] = (uint16_t)pidProfile()->D8[axis] * prop1 / 100;
#endif
        // non coupled PID reduction scaler used in PID controller 1 and PID controller 2. YAW TPA disabled. 100 means 100% of the pids
        if (axis == YAW) {
            PIDweight[axis] = 100;
        }
        else {
            PIDweight[axis] = prop2;
        }

        if (rcData[axis] < rxConfig()->midrc)
            rcCommand[axis] = -rcCommand[axis];
    }

    tmp = constrain(rcData[THROTTLE], rxConfig()->mincheck, PWM_RANGE_MAX);
    tmp = (uint32_t)(tmp - rxConfig()->mincheck) * PWM_RANGE_MIN / (PWM_RANGE_MAX - rxConfig()->mincheck);       // [MINCHECK;2000] -> [0;1000]
    tmp2 = tmp / 100;
    rcCommand[THROTTLE] = lookupThrottleRC[tmp2] + (tmp - tmp2 * 100) * (lookupThrottleRC[tmp2 + 1] - lookupThrottleRC[tmp2]) / 100;    // [0;1000] -> expo -> [MINTHROTTLE;MAXTHROTTLE]

    // Throttle calculations done, reset rcData to value before offset
    rcData[THROTTLE] = tmpThrottle;
}
コード例 #12
0
ファイル: config.c プロジェクト: jeyong/cleanflight
// Default settings
STATIC_UNIT_TESTED void resetConf(void)
{
    pgResetAll(MAX_PROFILE_COUNT);

    setProfile(0);
    pgActivateProfile(0);

    setControlRateProfile(0);

    featureClearAll();

    featureSet(DEFAULT_RX_FEATURE);

#ifdef BOARD_HAS_VOLTAGE_DIVIDER
    // only enable the VBAT feature by default if the board has a voltage divider otherwise
    // the user may see incorrect readings and unexpected issues with pin mappings may occur.
    featureSet(FEATURE_VBAT);
#endif

    featureSet(FEATURE_FAILSAFE);

    parseRcChannels("AETR1234", rxConfig());

    featureSet(FEATURE_BLACKBOX);

#if defined(COLIBRI_RACE)
    // alternative defaults settings for COLIBRI RACE targets
    imuConfig()->looptime = 1000;
    featureSet(FEATURE_ONESHOT125);
    featureSet(FEATURE_LED_STRIP);
#endif

#ifdef SPRACINGF3EVO
    featureSet(FEATURE_TRANSPONDER);
    featureSet(FEATURE_RSSI_ADC);
    featureSet(FEATURE_CURRENT_METER);
    featureSet(FEATURE_TELEMETRY);
#endif

    // alternative defaults settings for ALIENWIIF1 and ALIENWIIF3 targets
#ifdef ALIENWII32
    featureSet(FEATURE_RX_SERIAL);
    featureSet(FEATURE_MOTOR_STOP);
# ifdef ALIENWIIF3
    serialConfig()->portConfigs[2].functionMask = FUNCTION_RX_SERIAL;
    batteryConfig()->vbatscale = 20;
# else
    serialConfig()->portConfigs[1].functionMask = FUNCTION_RX_SERIAL;
# endif
    rxConfig()->serialrx_provider = SERIALRX_SPEKTRUM2048;
    rxConfig()->spektrum_sat_bind = 5;
    motorAndServoConfig()->minthrottle = 1000;
    motorAndServoConfig()->maxthrottle = 2000;
    motorAndServoConfig()->motor_pwm_rate = 32000;
    imuConfig()->looptime = 2000;
    pidProfile()->pidController = 3;
    pidProfile()->P8[PIDROLL] = 36;
    pidProfile()->P8[PIDPITCH] = 36;
    failsafeConfig()->failsafe_delay = 2;
    failsafeConfig()->failsafe_off_delay = 0;
    currentControlRateProfile->rcRate8 = 130;
    currentControlRateProfile->rates[ROLL] = 20;
    currentControlRateProfile->rates[PITCH] = 20;
    currentControlRateProfile->rates[YAW] = 100;
    parseRcChannels("TAER1234", rxConfig());
    *customMotorMixer(0) = (motorMixer_t){ 1.0f, -0.414178f,  1.0f, -1.0f };    // REAR_R
    *customMotorMixer(1) = (motorMixer_t){ 1.0f, -0.414178f, -1.0f,  1.0f };    // FRONT_R
    *customMotorMixer(2) = (motorMixer_t){ 1.0f,  0.414178f,  1.0f,  1.0f };    // REAR_L
    *customMotorMixer(3) = (motorMixer_t){ 1.0f,  0.414178f, -1.0f, -1.0f };    // FRONT_L
    *customMotorMixer(4) = (motorMixer_t){ 1.0f, -1.0f, -0.414178f, -1.0f };    // MIDFRONT_R
    *customMotorMixer(5) = (motorMixer_t){ 1.0f,  1.0f, -0.414178f,  1.0f };    // MIDFRONT_L
    *customMotorMixer(6) = (motorMixer_t){ 1.0f, -1.0f,  0.414178f,  1.0f };    // MIDREAR_R
    *customMotorMixer(7) = (motorMixer_t){ 1.0f,  1.0f,  0.414178f, -1.0f };    // MIDREAR_L
#endif

    // copy first profile into remaining profile
    PG_FOREACH_PROFILE(reg) {
        for (int i = 1; i < MAX_PROFILE_COUNT; i++) {
            memcpy(reg->address + i * pgSize(reg), reg->address, pgSize(reg));
        }
    }
    for (int i = 1; i < MAX_PROFILE_COUNT; i++) {
        configureRateProfileSelection(i, i % MAX_CONTROL_RATE_PROFILE_COUNT);
    }
}
コード例 #13
0
ファイル: gtune.c プロジェクト: Bengt-M/Triflight
void calculate_Gtune(uint8_t axis)
{
    int16_t error, diff_G, threshP;

    if(rcCommand[axis] || (axis != FD_YAW && (FLIGHT_MODE(ANGLE_MODE) || FLIGHT_MODE(HORIZON_MODE)))) {  // Block tuning on stick input. Always allow G-Tune on YAW, Roll & Pitch only in acromode
        OldError[axis] = 0;
        time_skip[axis] = delay_cycles;                                         // Some settle time after stick center. default 450ms
    } else {
        if (!time_skip[axis]) AvgGyro[axis] = 0;
        time_skip[axis]++;
        if (time_skip[axis] > 0) {
            if (axis == FD_YAW) {
                AvgGyro[axis] += 32 * ((int16_t)gyroADC[axis] / 32);           // Chop some jitter and average
            } else {
                AvgGyro[axis] += 128 * ((int16_t)gyroADC[axis] / 128);         // Chop some jitter and average
            }
        }
        if (time_skip[axis] == gtuneConfig()->gtune_average_cycles) {              // Looptime cycles for gyro average calculation. default 16.
            AvgGyro[axis] /= time_skip[axis];                                   // AvgGyro[axis] has now very clean gyrodata
            time_skip[axis] = 0;
            if (axis == FD_YAW) {
                threshP = 20;
                error = -AvgGyro[axis];
            } else {
                threshP = 10;
                error = AvgGyro[axis];
            }
            if (gtuneConfig()->gtune_hilimP[axis] && error && OldError[axis] && error != OldError[axis]) {  // Don't run when not needed or pointless to do so
                diff_G = ABS(error) - ABS(OldError[axis]);
                if ((error > 0 && OldError[axis] > 0) || (error < 0 && OldError[axis] < 0)) {
                    if (diff_G > threshP) {
                        if (axis == FD_YAW) {
                            result_P64[axis] += 256 + gtuneConfig()->gtune_pwr;    // YAW ends up at low limit on float PID, give it some more to work with.
                        } else {
                            result_P64[axis] += 64 + gtuneConfig()->gtune_pwr;     // Shift balance a little on the plus side.
                        }
                    } else {
                        if (diff_G < -threshP) {
                            if (axis == FD_YAW) {
                                result_P64[axis] -= 64 + gtuneConfig()->gtune_pwr;
                            } else {
                                result_P64[axis] -= 32;
                            }
                        }
                    }
                } else {
                    if (ABS(diff_G) > threshP && axis != FD_YAW) {
                        result_P64[axis] -= 32;                                 // Don't use antiwobble for YAW
                    }
                }
                int16_t newP = constrain((result_P64[axis] >> 6), (int16_t)gtuneConfig()->gtune_lolimP[axis], (int16_t)gtuneConfig()->gtune_hilimP[axis]);

#ifdef BLACKBOX
                if (feature(FEATURE_BLACKBOX)) {
                    flightLogEvent_gtuneCycleResult_t eventData;

                    eventData.gtuneAxis = axis;
                    eventData.gtuneGyroAVG = AvgGyro[axis];
                    eventData.gtuneNewP = newP;                                 // for float PID the logged P value is still mutiplyed by 10
                    blackboxLogEvent(FLIGHT_LOG_EVENT_GTUNE_RESULT, (flightLogEventData_t*)&eventData);
                }
#endif

                pidProfile()->P8[axis] = newP;                                // new P value
            }
            OldError[axis] = error;
        }
コード例 #14
0
ファイル: mw.c プロジェクト: bimmal/cleanflight
/*
This function processes RX dependent coefficients when new RX commands are available
Those are: TPA, throttle expo
*/
void processRxDependentCoefficients(void) {

    int32_t tmp, tmp2;
    int32_t axis, prop1 = 0, prop2;

    // PITCH & ROLL only dynamic PID adjustment,  depending on throttle value
    if (rcData[THROTTLE] < currentControlRateProfile->tpa_breakpoint) {
        prop2 = 100;
    } else {
        if (rcData[THROTTLE] < 2000) {
            prop2 = 100 - (uint16_t)currentControlRateProfile->dynThrPID * (rcData[THROTTLE] - currentControlRateProfile->tpa_breakpoint) / (2000 - currentControlRateProfile->tpa_breakpoint);
        } else {
            prop2 = 100 - currentControlRateProfile->dynThrPID;
        }
    }

    for (axis = 0; axis < 3; axis++) {
        tmp = MIN(ABS(rcData[axis] - rxConfig()->midrc), 500);
        if (axis == ROLL || axis == PITCH) {
            if (rcControlsConfig()->deadband) {
                if (tmp > rcControlsConfig()->deadband) {
                    tmp -= rcControlsConfig()->deadband;
                } else {
                    tmp = 0;
                }
            }

            tmp2 = tmp / 100;
            rcCommand[axis] = lookupPitchRollRC[tmp2] + (tmp - tmp2 * 100) * (lookupPitchRollRC[tmp2 + 1] - lookupPitchRollRC[tmp2]) / 100;
            prop1 = 100 - (uint16_t)currentControlRateProfile->rates[axis] * tmp / 500;
            prop1 = (uint16_t)prop1 * prop2 / 100;
        } else if (axis == YAW) {
            if (rcControlsConfig()->yaw_deadband) {
                if (tmp > rcControlsConfig()->yaw_deadband) {
                    tmp -= rcControlsConfig()->yaw_deadband;
                } else {
                    tmp = 0;
                }
            }
            tmp2 = tmp / 100;
            rcCommand[axis] = (lookupYawRC[tmp2] + (tmp - tmp2 * 100) * (lookupYawRC[tmp2 + 1] - lookupYawRC[tmp2]) / 100) * -rcControlsConfig()->yaw_control_direction;
            prop1 = 100 - (uint16_t)currentControlRateProfile->rates[axis] * ABS(tmp) / 500;
        }
#ifndef SKIP_PID_MW23
        // FIXME axis indexes into pids.  use something like lookupPidIndex(rc_alias_e alias) to reduce coupling.
        dynP8[axis] = (uint16_t)pidProfile()->P8[axis] * prop1 / 100;
        dynI8[axis] = (uint16_t)pidProfile()->I8[axis] * prop1 / 100;
        dynD8[axis] = (uint16_t)pidProfile()->D8[axis] * prop1 / 100;
#endif
        // non coupled PID reduction scaler used in PID controller 1 and PID controller 2. YAW TPA disabled. 100 means 100% of the pids
        if (axis == YAW) {
            PIDweight[axis] = 100;
        }
        else {
            PIDweight[axis] = prop2;
        }

        if (rcData[axis] < rxConfig()->midrc)
            rcCommand[axis] = -rcCommand[axis];
    }
    if (FLIGHT_MODE(HEADFREE_MODE)) {
        float radDiff = degreesToRadians(DECIDEGREES_TO_DEGREES(attitude.values.yaw) - headFreeModeHold);
        float cosDiff = cos_approx(radDiff);
        float sinDiff = sin_approx(radDiff);
        int16_t rcCommand_PITCH = rcCommand[PITCH] * cosDiff + rcCommand[ROLL] * sinDiff;
        rcCommand[ROLL] = rcCommand[ROLL] * cosDiff - rcCommand[PITCH] * sinDiff;
        rcCommand[PITCH] = rcCommand_PITCH;
    }
}
コード例 #15
0
void applyFixedWingLaunchController(timeUs_t currentTimeUs)
{
    // Called at PID rate

    if (launchState.launchDetected) {
        bool applyLaunchIdleLogic = true;

        if (launchState.motorControlAllowed) {
            // If launch detected we are in launch procedure - control airplane
            const float timeElapsedSinceLaunchMs = US2MS(currentTimeUs - launchState.launchStartedTime);

            // If user moves the stick - finish the launch
            if ((ABS(rcCommand[ROLL]) > rcControlsConfig()->pos_hold_deadband) || (ABS(rcCommand[PITCH]) > rcControlsConfig()->pos_hold_deadband)) {
                launchState.launchFinished = true;
            }

            // Abort launch after a pre-set time
            if (timeElapsedSinceLaunchMs >= navConfig()->fw.launch_timeout) {
                launchState.launchFinished = true;
            }

            // Motor control enabled
            if (timeElapsedSinceLaunchMs >= navConfig()->fw.launch_motor_timer) {
                // Don't apply idle logic anymore
                applyLaunchIdleLogic = false;

                // Increase throttle gradually over `launch_motor_spinup_time` milliseconds
                if (navConfig()->fw.launch_motor_spinup_time > 0) {
                    const float timeSinceMotorStartMs = constrainf(timeElapsedSinceLaunchMs - navConfig()->fw.launch_motor_timer, 0.0f, navConfig()->fw.launch_motor_spinup_time);
                    const uint16_t minIdleThrottle = MAX(motorConfig()->minthrottle, navConfig()->fw.launch_idle_throttle);
                    rcCommand[THROTTLE] = scaleRangef(timeSinceMotorStartMs,
                                                      0.0f, navConfig()->fw.launch_motor_spinup_time,
                                                      minIdleThrottle, navConfig()->fw.launch_throttle);
                }
                else {
                    rcCommand[THROTTLE] = navConfig()->fw.launch_throttle;
                }
            }
        }

        if (applyLaunchIdleLogic) {
            // Launch idle logic - low throttle and zero out PIDs
            applyFixedWingLaunchIdleLogic();
        }
    }
    else {
        // We are waiting for launch - update launch detector
        updateFixedWingLaunchDetector(currentTimeUs);

        // Launch idle logic - low throttle and zero out PIDs
        applyFixedWingLaunchIdleLogic();
    }

    // Control beeper
    if (!launchState.launchFinished) {
        beeper(BEEPER_LAUNCH_MODE_ENABLED);
    }

    // Lock out controls
    rcCommand[ROLL] = 0;
    rcCommand[PITCH] = pidAngleToRcCommand(-DEGREES_TO_DECIDEGREES(navConfig()->fw.launch_climb_angle), pidProfile()->max_angle_inclination[FD_PITCH]);
    rcCommand[YAW] = 0;
}
コード例 #16
0
ファイル: mw.c プロジェクト: JoachimF/cleanflight
void taskMainPidLoop(void)
{
    cycleTime = getTaskDeltaTime(TASK_SELF);
    dT = (float)cycleTime * 0.000001f;

    // Calculate average cycle time and average jitter
    filteredCycleTime = filterApplyPt1(cycleTime, &filteredCycleTimeState, 1, dT);
    
    debug[0] = cycleTime;
    debug[1] = cycleTime - filteredCycleTime;

    imuUpdateGyroAndAttitude();

    annexCode();

    if (rxConfig()->rcSmoothing) {
        filterRc();
    }

#if defined(BARO) || defined(SONAR)
    haveProcessedAnnexCodeOnce = true;
#endif

#ifdef MAG
        if (sensors(SENSOR_MAG)) {
            updateMagHold();
        }
#endif

#if defined(BARO) || defined(SONAR)
        if (sensors(SENSOR_BARO) || sensors(SENSOR_SONAR)) {
            if (FLIGHT_MODE(BARO_MODE) || FLIGHT_MODE(SONAR_MODE)) {
                applyAltHold();
            }
        }
#endif

    // If we're armed, at minimum throttle, and we do arming via the
    // sticks, do not process yaw input from the rx.  We do this so the
    // motors do not spin up while we are trying to arm or disarm.
    // Allow yaw control for tricopters if the user wants the servo to move even when unarmed.
    if (isUsingSticksForArming() && rcData[THROTTLE] <= rxConfig()->mincheck
#ifndef USE_QUAD_MIXER_ONLY
#ifdef USE_SERVOS
                && !((mixerConfig()->mixerMode == MIXER_TRI || mixerConfig()->mixerMode == MIXER_CUSTOM_TRI) && mixerConfig()->tri_unarmed_servo)
#endif
                && mixerConfig()->mixerMode != MIXER_AIRPLANE
                && mixerConfig()->mixerMode != MIXER_FLYING_WING
#endif
    ) {
        rcCommand[YAW] = 0;
    }

    if (throttleCorrectionConfig()->throttle_correction_value && (FLIGHT_MODE(ANGLE_MODE) || FLIGHT_MODE(HORIZON_MODE))) {
        rcCommand[THROTTLE] += calculateThrottleAngleCorrection(throttleCorrectionConfig()->throttle_correction_value);
    }

#ifdef GPS
    if (sensors(SENSOR_GPS)) {
        if ((FLIGHT_MODE(GPS_HOME_MODE) || FLIGHT_MODE(GPS_HOLD_MODE)) && STATE(GPS_FIX_HOME)) {
            updateGpsStateForHomeAndHoldMode();
        }
    }
#endif

    // PID - note this is function pointer set by setPIDController()
    pid_controller(
        pidProfile(),
        currentControlRateProfile,
        imuConfig()->max_angle_inclination,
        &accelerometerConfig()->accelerometerTrims,
        rxConfig()
    );

    mixTable();

#ifdef USE_SERVOS
    filterServos();
    writeServos();
#endif

    if (motorControlEnable) {
        writeMotors();
    }

#ifdef USE_SDCARD
        afatfs_poll();
#endif

#ifdef BLACKBOX
    if (!cliMode && feature(FEATURE_BLACKBOX)) {
        handleBlackbox();
    }
#endif
}
コード例 #17
0
ファイル: pid_autotune.c プロジェクト: raul-ortega/iNav
void autotuneFixedWingUpdate(const flight_dynamics_index_t axis, float desiredRateDps, float reachedRateDps, float pidOutput)
{
    const timeMs_t currentTimeMs = millis();
    const float absDesiredRateDps = fabsf(desiredRateDps);
    float maxDesiredRate = currentControlRateProfile->stabilized.rates[axis] * 10.0f;
    pidAutotuneState_e newState;

    // Use different max desired rate in ANGLE for pitch and roll
    // Maximum reasonable error in ANGLE mode is 200% of angle inclination (control dublet), but we are conservative and tune for control singlet.
    if (FLIGHT_MODE(ANGLE_MODE) && (axis == FD_PITCH || axis == FD_ROLL)) {
        float maxDesiredRateInAngleMode = DECIDEGREES_TO_DEGREES(pidProfile()->max_angle_inclination[axis] * 1.0f) * pidBank()->pid[PID_LEVEL].P / FP_PID_LEVEL_P_MULTIPLIER;
        maxDesiredRate = MIN(maxDesiredRate, maxDesiredRateInAngleMode);
    }

    if (fabsf(pidOutput) >= pidProfile()->pidSumLimit) {
        // If we have saturated the pid output by P+FF don't increase the gain
        tuneCurrent[axis].pidSaturated = true;
    }

    if (absDesiredRateDps < (pidAutotuneConfig()->fw_max_rate_threshold / 100.0f) * maxDesiredRate) {
        // We can make decisions only when we are demanding at least 50% of max configured rate
        newState = DEMAND_TOO_LOW;
    }
    else if (fabsf(reachedRateDps) > absDesiredRateDps) {
        newState = DEMAND_OVERSHOOT;
    }
    else {
        newState = DEMAND_UNDERSHOOT;
    }

    if (newState != tuneCurrent[axis].state) {
        const timeDelta_t stateTimeMs = currentTimeMs - tuneCurrent[axis].stateEnterTime;
        bool gainsUpdated = false;

        switch (tuneCurrent[axis].state) {
            case DEMAND_TOO_LOW:
                break;
            case DEMAND_OVERSHOOT:
                if (stateTimeMs >= pidAutotuneConfig()->fw_overshoot_time) {
                    tuneCurrent[axis].gainD = tuneCurrent[axis].gainD * (100 - AUTOTUNE_FIXED_WING_DECREASE_STEP) / 100.0f;
                    if (tuneCurrent[axis].gainD < AUTOTUNE_FIXED_WING_MIN_FF) {
                        tuneCurrent[axis].gainD = AUTOTUNE_FIXED_WING_MIN_FF;
                    }
                    gainsUpdated = true;
                }
                break;
            case DEMAND_UNDERSHOOT:
                if (stateTimeMs >= pidAutotuneConfig()->fw_undershoot_time && !tuneCurrent[axis].pidSaturated) {
                    tuneCurrent[axis].gainD = tuneCurrent[axis].gainD * (100 + AUTOTUNE_FIXED_WING_INCREASE_STEP) / 100.0f;
                    if (tuneCurrent[axis].gainD > AUTOTUNE_FIXED_WING_MAX_FF) {
                        tuneCurrent[axis].gainD = AUTOTUNE_FIXED_WING_MAX_FF;
                    }
                    gainsUpdated = true;
                }
                break;
        }

        if (gainsUpdated) {
            // Set P-gain to 10% of FF gain (quite agressive - FIXME)
            tuneCurrent[axis].gainP = tuneCurrent[axis].gainD * (pidAutotuneConfig()->fw_ff_to_p_gain / 100.0f);

            // Set integrator gain to reach the same response as FF gain in 0.667 second
            tuneCurrent[axis].gainI = (tuneCurrent[axis].gainD / FP_PID_RATE_FF_MULTIPLIER) * (1000.0f / pidAutotuneConfig()->fw_ff_to_i_time_constant) * FP_PID_RATE_I_MULTIPLIER;
            tuneCurrent[axis].gainI = constrainf(tuneCurrent[axis].gainI, 2.0f, 50.0f);
            autotuneUpdateGains(tuneCurrent);

            switch (axis) {
            case FD_ROLL:
                blackboxLogAutotuneEvent(ADJUSTMENT_ROLL_D, tuneCurrent[axis].gainD);
                break;

            case FD_PITCH:
                blackboxLogAutotuneEvent(ADJUSTMENT_PITCH_D, tuneCurrent[axis].gainD);
                break;

            case FD_YAW:
                blackboxLogAutotuneEvent(ADJUSTMENT_YAW_D, tuneCurrent[axis].gainD);
                break;
            }
        }

        // Change state and reset saturation flag
        tuneCurrent[axis].state = newState;
        tuneCurrent[axis].stateEnterTime = currentTimeMs;
        tuneCurrent[axis].pidSaturated = false;
    }
}