• 항공우주시스템공학회지
• /
• 제14권6호
• /
• pp.74-78
• /
• 2020

The cooler driver electronics (CDE) for maintaining a low temperature of a satellite payload IR sensor has a compressor with a pulsation current load when in operation. This pulsation current creates a large voltage fluctuation and may negatively affect both the load and regulated bus stability. Thus, a CDE power conditioning system has a battery for use as a buffer that is connected in front of the CDE load line. In this system, a battery charger limiter circuit is required to protect from an over-charge of the battery and power to the load. In this study, an optimal design and parameter selection were developed and simulated.

• 항공우주시스템공학회지
• /
• 제14권6호
• /
• pp.79-84
• /
• 2020

Cooler driver electronics (CDE) for maintaining low temperature of the satellite payload IR sensor consists of a compressor that has a pulsation current load condition when it is operated. This pulsation current produces large voltage fluctuation, which affects both load and regulated bus stability. Thus, CDE power conditioning system consists of a primary bus, infrared power distribution unit for battery charging and protection, reverse current protection diode, and battery, which is used as a buffer. In this study, the operational mode analysis is performed by each part with equivalent impedance modeling verified through system level simulation. From this mode analysis, the safety margin for state of charge and open circuit voltage of the battery is determined for satisfying the minimum operational voltage of the CDE load.

• 항공우주시스템공학회지
• /
• 제17권1호
• /
• pp.88-96
• /
• 2023

우리나라에서 개발 중인 저궤도 위성은 아리랑 위성으로, 이제까지 꾸준한 성능향상이 있었다. 이때 탑재체의 성능향상에 따른 탑재체의 전력요구도는 늘어나게 되었고 이에 위성 내부 전력 공급장치의 설계 및 Solar Array의 구성 등 위성 설계가 달라진다. 이에 따라 위성에 전력을 공급하며 위성 통합시험을 진행하는 전력계 전기지상지원장비 설계 시 전력 증가에 따라 많은 고려사항이 필요로 한다. 본 논문은 탑재체에 따른 위성 전력요구도의 변화 및 전력요구도 증가에 따른 전력계 전기지상지원장비 설계 시 고려할 사항에 대해서 다룬다.