본 논문에서는 항공기 자세 변화를 고려한 항공기 보조연료탱크 연료량측정시스템을 제시하였다. 개발된 연료량측정시스템은 연료센서, 데이터 처리장치, 계기 및 센서 데이터로부터 연료량을 추정하는 소프트웨어로 구성되었다. 지상에서의 롤 및 피치 자세 변화를 모사하기 위해 모사시험 장치가 개발되었다. 모사시험장치를 이용하여 다양한 연료량, 롤 및 피치 각도의 센서 데이터를 자동으로 측정하여 트레이닝 데이터 세트를 획득하였다. 연료량을 추정하는 연료량 측정 소프트웨어를 트레이닝 데이터 세트와 함께 삼선형보간법을 사용하여 개발하였다. 개발된 연료량측정시스템은 참값을 알고 있는 테스트 데이터 세트의 연료 추정 오차를 측정하여 검증하였다. 테스트를 통해 개발된 연료량측정시스템의 오차가 TSO-C55 문서의 기준을 충족하는 것을 확인하였다.
본 논문에서는 항공기 자세 변화를 고려한 항공기 보조연료탱크 연료량측정시스템을 제시하였다. 개발된 연료량측정시스템은 연료센서, 데이터 처리장치, 계기 및 센서 데이터로부터 연료량을 추정하는 소프트웨어로 구성되었다. 지상에서의 롤 및 피치 자세 변화를 모사하기 위해 모사시험 장치가 개발되었다. 모사시험장치를 이용하여 다양한 연료량, 롤 및 피치 각도의 센서 데이터를 자동으로 측정하여 트레이닝 데이터 세트를 획득하였다. 연료량을 추정하는 연료량 측정 소프트웨어를 트레이닝 데이터 세트와 함께 삼선형보간법을 사용하여 개발하였다. 개발된 연료량측정시스템은 참값을 알고 있는 테스트 데이터 세트의 연료 추정 오차를 측정하여 검증하였다. 테스트를 통해 개발된 연료량측정시스템의 오차가 TSO-C55 문서의 기준을 충족하는 것을 확인하였다.
This paper presents a fuel quantity measurement system (FQMS) for an aircraft supplementary fuel tank considering the change of aircraft attitude. The developed FQMS consists of fuel sensors, a signal process unit, an indicator and a software to estimate the fuel quantity from the sensor data. To re...
This paper presents a fuel quantity measurement system (FQMS) for an aircraft supplementary fuel tank considering the change of aircraft attitude. The developed FQMS consists of fuel sensors, a signal process unit, an indicator and a software to estimate the fuel quantity from the sensor data. To replicate the change of the roll and pitch attitude on the ground, the test simulator is developed in this work. Using the test simulator, the sensor data at various fuel quantities, roll and pitch angles are automatically measured to build a training data set. The data-driven software to estimate the fuel quantity is then developed using a trilinear interpolation method with the training data set. The developed FQMS is verified by investigating the fuel estimation error of the test data set that we know the true values. Through the test, it is confirmed that the error of the developed FQMS system satisfies the criteria of TSO-C55 document.
This paper presents a fuel quantity measurement system (FQMS) for an aircraft supplementary fuel tank considering the change of aircraft attitude. The developed FQMS consists of fuel sensors, a signal process unit, an indicator and a software to estimate the fuel quantity from the sensor data. To replicate the change of the roll and pitch attitude on the ground, the test simulator is developed in this work. Using the test simulator, the sensor data at various fuel quantities, roll and pitch angles are automatically measured to build a training data set. The data-driven software to estimate the fuel quantity is then developed using a trilinear interpolation method with the training data set. The developed FQMS is verified by investigating the fuel estimation error of the test data set that we know the true values. Through the test, it is confirmed that the error of the developed FQMS system satisfies the criteria of TSO-C55 document.
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문제 정의
This paper presents the FQMS developed for an aircraft supplementary fuel tank. The developed FQMS uses a capacitance type fuel sensor with the signal processing device composed of the data acquisition (DAQ) and computer.
This paper presents the development of the FQMS for a supplementary fuel tank. The developed FQMS consists of P-300C capacitance-type fuel sensor, a signal processor, and an indicator implemented using a LabVIEW software.
가설 설정
8. The frequency f measured at the fuel sensor is little varied following the roll Φ motion.
9. If the fuel quantity is between 9L and 72L, the relation between the frequency f and the pitch angle θ is linearly proportional.
제안 방법
The FQMS consists of fuel sensors, a signal process unit, an indicator, and software. As shown in Fig. 1, a passive DC capacitance type fuel sensor, P-300C, is used in this work to measure the capacitance that is determined by the height of the fuel in the tank. The output data of the P-300C fuel sensor is the form of the frequency and processed through a data acquisition (DAQ) system.
Through tank studies, the location of the sensor is optimized to minimize the quantity of fuel that cannot be measured. The optimized sensor location is obtained using parametric study. Fig.
The quantity of fuel was estimated using the trilinear interpolation method with the training data set. The training data set was prepared using the test simulator. Using the test simulator, the sensor frequency data at various fuel quantity and roll/pitch angles were automatically acquired.
The test simulator hardware consists of attitude simulation equipment, fueling equipment, and data acquisition equipment. To obtain the training data set composed of a sensor information at various fuel quantities and roll/pitch angles, the system for the automatic control of the fuel quantity and roll/ pitch angles is developed in this work. A data-driven software using the trilinear interpolation[12] is developed using the obtained training data set to estimate the fuel quantity.
The test system[10] consists of a drive unit, a servo system, and an upper control. Using the developed device, the FQMS for MUAV was developed and its accuracy was verified through the test.
대상 데이터
To treat the change of aircraft attitude, a test simulator is developed. The test simulator hardware consists of attitude simulation equipment, fueling equipment, and data acquisition equipment. To obtain the training data set composed of a sensor information at various fuel quantities and roll/pitch angles, the system for the automatic control of the fuel quantity and roll/ pitch angles is developed in this work.
이론/모형
The fuel quantity is estimated using the trilinear interpolation method. The trilinear interpolation is the extension of linear interpolation to deal with three-dimensional data.
The developed FQMS consists of P-300C capacitance-type fuel sensor, a signal processor, and an indicator implemented using a LabVIEW software. The quantity of fuel was estimated using the trilinear interpolation method with the training data set. The training data set was prepared using the test simulator.
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