선택한 단어 수는 입니다.
최소 단어 이상 선택하여야 합니다.
최소 단어 이상 선택하여야 합니다.
선택한 단어 수는 30입니다.
최대 10 단어까지만 선택 가능합니다.
최대 10 단어까지만 선택 가능합니다.
제안 방법
- The magnetic sensor is widely implemented for attitude determination of LEO small satellites because of its low mass, low power consumptions and small size. In this paper, to develop the fluxgate magnetometer, a core and coil materials are selected with optimal sizing analysis by considering several parameters such as permeability, demagnetization factors, coil diameter, and number of coil turns. Following the analysis, the magnetometer was developed and the linearity test was performed.
- The sensor size is also to be limited in the small satellite design. To estimate the magnetometer size, we surveyed the size of magnetic sensors for small satellites. Figure 3a and 3b show the magnetometer size and height in accordance with satellite mass, respectively.
대상 데이터
- In order to make a magnetometer smaller, the established magnetometer data was analysed. The data was used in deciding the mass and size of the magnetometer developed by SSRL. As shown in Figure 2, the magnetometer mass is linearly proportional to the satellite mass, except one magnetometer was used as a payload on a 20 kg class satellite.
- As shown in Figure 6, the cross point at 20 mm of core diameter is about 210 turns. The sensing coil of magnetic sensor is selected to be 210 turns and 250 turns for the driving coil. The number of driving coil turns is determined depending on number of sensing coil turns because mutual inductance must be zero.
이론/모형
- In this paper, to develop the fluxgate magnetometer, a core and coil materials are selected with optimal sizing analysis by considering several parameters such as permeability, demagnetization factors, coil diameter, and number of coil turns. Following the analysis, the magnetometer was developed and the linearity test was performed. The result of the error analysis satisfies the requirements.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.