• Aerospace Engineering and Technology
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• v.12 no.2
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• pp.7-13
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• 2013

Power system in satellite shall produce stable outputs for successful mission accomplishment. However, unstability in overall electrical system is caused in a case where a load having a power profile with high-powered and micro-cycled pulse shape is connected to a satellite power system. In order to resolve this anomaly, "power system stabilization method using a battery" featured with simplicity can be applied, but there is a constraint to operate a battery in its normal operational conditions. In this paper, an effective interface structure for "power system stabilization method using a battery" is suggested and a battery protection algorithm for preventing over-charging and over-discharging is discussed.

• Proceedings of the KIPE Conference
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• 2017.11a
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• pp.163-164
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• 2017

본 논문에서는 KMSL(Korea Microgravity Science Laboratory) 큐브 위성에 대해 설명하고 전력시스템 설계 연구 방법을 제시한다. 1~3리터 사이즈인 초소형 인공위성(큐브위성)의 전력시스템은 태양 전지 패널로부터 큐브 위성의 부하장치 운용을 위한 전력을 공급받고, 남은 잉여 전력은 배터리에 저장하여 식(eclipse) 구간 동안 전력이 공급될 수 있도록 전력계가 구성된다. 본 논문에서는 조선대학교 KMSL팀의 큐브 위성에 대한 전력시스템을 설계하기 위해서 위성 궤도 및 자세에 따른 생산 전력, 소비 전력을 인공위성의 자세 및 궤도에 따라 분석하고, 부하 장치의 전원 및 소모전력을 통해 전력 및 에너지 마진(margin)이 충분하도록 전력계시스템의 구성품 용량을 설계하였다.

• Aerospace Engineering and Technology
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• v.11 no.1
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• pp.1-6
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• 2012

Power system in satellite is protected by installing fuses, LCLs (Latching Current Limiters), etc. between satellite power supply and loads. In this paper, the fuse sizing technique for satellite power system protection is addressed. Detailed fuse sizing method is explained and it is shown that the single fuse connection method is mathematically subordinated to the parallel fuse connection method. In addition, appropriate fuse selection method is newly suggested under a situation where exact current characteristics of a load connected to a fuse is unknown.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.12
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• pp.1207-1215
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• 2008

Satellite generates a complex electromagnetic noise by conducted and radiated coupling effect of the various electrical instruments. This noise may cause serious problems on the satellite system. To minimize the electromagnetic coupling effects and maintain the system safety margin, system noise reduction technique should be applied from the beginning of the system design. The COMS system is evaluated by measuring the conducted noise on system electrical power leads at PSR(Power Supply Regulator) and verifying a 6 dB system safety margin under the complex noise environment with current injection. The radiated noise due to the complex transmit antenna configuration is evaluated by integrating all unit-level RE measurement results, and the RF compatibility between spacecraft and launch vehicle is analyzed with the above estimations. This paper describes the COMS EMC compatibility analysis with respect to each unit level EMC test results, and RF compatibility analysis between spacecraft and launch vehicle. The analyzed results will be reflected on FM(Flight Model) EMC test.

• Journal of Satellite, Information and Communications
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• v.11 no.3
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• pp.114-118
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• 2016

In this paper, we present the advanced open collector circuit, interface circuit between aerospace electronics. Satellite is composed of a number of electronics, which were provided from various manufacturers. Each company manufactured its own electronics for satellite using its heritage and requirements for their electronics. Therefore each electronics may use different internal supplies. It make a problem between electronics because the supply is different from other electronics, such as the increasing of power dissipation because of the static current and the mismatch of interface voltage, the offset. Proposed circuit can reduce the static current and rising time, and also decrease the useless power dissipation caused by the static current for open collector circuit

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.4
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• pp.351-359
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• 2014

This paper introduces the lithium ion battery system for LEO(Low Earth Orbit) small satellites. This study proves the reliability of lithium ion batteries applying to the space application. The specifications for lithium ion battery unit are proposed to supply power to the satellite and the overall mechanical design including structural simulation to confirm the reliability of the lithium ion BMS(Battery Management System) under the space environment and launching conditions. The results of structural simulation, functional tests, and space environmental tests show the lithium ion battery system is space qualified. Space qualification of the small satellite battery system to secure reliability of BMS and lithium ion batteries lend credibility for using lithium ion batteries in space application.

• 전기의세계
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• v.45 no.7
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• pp.39-44
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• 1996

전력변환 시스템의 고성능화를 위해서는 스윗칭 주파수를 고주파수로 하는 것이 필요하다. 그러나 PWM방식에서는 반도체 소자를 강제적으로 스윗칭시키기 때문에 고주파 스윗칭을 행하면 EMI, EMC 문제를 무시할 수 없게 되고 스윗칭 손실은 스윗칭 주파수와 함께 증가한다. 이 문제를 해결하기 위해 1986년에 미국 위스콘신대학에서 당초 인공위성 등에 탑재하는 직류전원으로서 직류/직류 컨버터의 공진 스위치였던 회로구성을 3상 직류링크 전압형 인버터에 전개하여 소프트 스윗칭이 가능하게 되는 교류전원용의 전압형 인버터를 발표하였다. 또한 그 당시에 또 다른 공진형 회로구성인 교류링크 인버터도 발표되었다[3-5]. 이러한 배경으로 이하에서는 PWM 전력변환기의 소개를 시작으로 고주파수화의 필요성 및 그로 인해 파생되는 문제점을 고찰하고, 공진형 전력변환 시스템의 필요성에 대하여 논한 뒤 각종의 공진형 변환기에 대하여 간략하게 설명하고자 한다.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.21 no.5
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• pp.885-892
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• 2017

In this paper, we proposed a novel crowbar circuit for high-speed discharge charge switching to solve discharge charge-time delay of supply voltage in the conventional crowbar circuit. The proposed circuit is designed to increase the charge-speed after high-speed discharge of supply voltage, thereby reducing the time exposed to radiation damage and, the normal operation time of electronic system after passing the pulse radiation. The simulation of the discharge charge-times before the implement of the hardware is conducted using Cadence's pspice tool, and DUT (Device Under Test) board is fabricated in the device level. The comparison measurement of the crowbar circuits is performed on the satellite-electronic device for 24V. As the result, we confirmed the high-speed function of the proposed circuit by improvement of the discharge-speed 96.8% and the charge-speed 27.3% as compared with the conventional circuit.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.23 no.5
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• pp.487-494
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• 2019

A Small-Sat Power System Design and Development should be depend on space environment such as solar wind with Electromagnetic field by hurdle of techniques. It is surmount solution of trend that will unitize and converge with power module in these days. The level of modularize means that applying Universal Middleware for payload power module requirements. The scope of target system is a main power provider module and operational subunit that can be implemented with the final power module distribution loads to consume for continuous process. A Universal Middleware strengthen to build power module from satellite power system should be accuracy and consuming data. A Power Service Module and dynamic system drive interactive management between power distribution and consumer module by Range Control. Consequently, suggesting evaluation, unexpecting payload system power consumer that makes fine variable resources in the development design process and efficiency.

• Korean Journal of Optics and Photonics
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• v.32 no.1
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• pp.9-14
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• 2021

In this paper we have studied an optical system according to the aperture position of an off-axis TMA telescope for satellites. An off-axis TMA telescope should have high resolution and wide field of view (FOV). In addition, the optical system should have a wide tolerance range, because it is structurally located off-axis and is difficult to assemble. However, there are differences in performance and sensitivity according to the aperture-stop position, so it is important to select a suitable aperture-stop position. Therefore, in this paper we have designed each off-axis TMA telescope according to the aperture-stop position, and have analyzed the performance and sensitivity to suggest a suitable aperture-stop position.