forked from Archive/PX4-Autopilot
mtecs: rename variable
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@ -160,15 +160,15 @@ int mTecs::updateFlightPathAngleAcceleration(float flightPathAngle, float flight
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float airspeedDerivativeNorm = airspeedDerivative / CONSTANTS_ONE_G;
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float airspeedDerivativeNorm = airspeedDerivative / CONSTANTS_ONE_G;
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float airspeedDerivativeSp = accelerationLongitudinalSp;
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float airspeedDerivativeSp = accelerationLongitudinalSp;
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float airspeedDerivativeNormSp = airspeedDerivativeSp / CONSTANTS_ONE_G;
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float airspeedDerivativeNormSp = airspeedDerivativeSp / CONSTANTS_ONE_G;
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float airspeedDerivativeNormErrorSp = airspeedDerivativeNormSp - airspeedDerivativeNorm;
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float airspeedDerivativeNormError = airspeedDerivativeNormSp - airspeedDerivativeNorm;
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float totalEnergyRate = flightPathAngle + airspeedDerivativeNorm;
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float totalEnergyRate = flightPathAngle + airspeedDerivativeNorm;
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float totalEnergyRateError = flightPathAngleError + airspeedDerivativeNormErrorSp;
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float totalEnergyRateError = flightPathAngleError + airspeedDerivativeNormError;
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float totalEnergyRateSp = flightPathAngleSp + airspeedDerivativeNormSp;
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float totalEnergyRateSp = flightPathAngleSp + airspeedDerivativeNormSp;
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float totalEnergyRateError2 = totalEnergyRateSp - totalEnergyRate;
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float totalEnergyRateError2 = totalEnergyRateSp - totalEnergyRate;
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float energyDistributionRate = flightPathAngle - airspeedDerivativeNorm;
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float energyDistributionRate = flightPathAngle - airspeedDerivativeNorm;
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float energyDistributionRateError = flightPathAngleError - airspeedDerivativeNormErrorSp;
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float energyDistributionRateError = flightPathAngleError - airspeedDerivativeNormError;
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float energyDistributionRateSp = flightPathAngleSp - airspeedDerivativeNormSp;
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float energyDistributionRateSp = flightPathAngleSp - airspeedDerivativeNormSp;
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float energyDistributionRateError2 = energyDistributionRateSp - energyDistributionRate;
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float energyDistributionRateError2 = energyDistributionRateSp - energyDistributionRate;
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