• 한국항공우주학회지
• /
• 제37권6호
• /
• pp.580-585
• /
• 2009

본 논문은 항우연에서 개발 중인 위성 탑재카메라 FPA-CU(Focal Plane Assembly Cooling Unit) 의 개념설계 및 열설계에 대한 개략적인 내용을 기술하고 있다. FPA-CU은 국내 기술로 설계/제작되는 최초의 우주용 냉각유닛이다. FPA-CU에는 일반적인 히트파이프와 방열판을 이용한 냉각유닛과는 다르게 TBM(Thermal Buffer Mass)이 부착되어 있으므로 열적거동이 기존의 냉각유닛과 다르며, 설계에 있어 천이열전달 해석이 반드시 필요하다. 본 논문에서는 TBM의 용량산출 및 형상적 영향을 포함한 전체 냉각유닛 설계방법을 제시하고 전체 냉각유닛에 대한 열해석 결과를 기술하고 있다. 열해석 결과 냉각유닛의 요구조건을 잘 만족시킴을 알 수 있었으며, 최상단부 히트파이프가 비정상 작동하는 경우 FPA의 온도가 $3{\sim}4^{\circ}C$ 정도 상승함을 알 수 있었다. 본 연구를 통해 위성용 열제어 유닛 설계에 대한 국내 기술적 자립 가능성을 확인할 수 있었다.

• Journal of Astronomy and Space Sciences
• /
• 제17권2호
• /
• pp.233-240
• /
• 2000

Five scientific instruments are planned on KAISTSAT-4 that is scheduled to be launched in 2002. A far ultra-violet imaging spectrograph and a set of space plasma instruments are currently being designed. The imaging spectrograph will make observations of astronomical objects and Earth's upper atmosphere. The plasma instrumentation is capable of fast measuring the thermal magnetosphere plasmas, cold ionospheric plasmas and the Earth's magnetic fields. Major system drivers and constraints on the payloads as well as the spacecraft are identified. A preliminary analysis of the K-4 mission has been undertaken with the system requirements that are derived from the system drivers. Detailed investigation shows that Sun-synchronous orbits with approximate altitudes of 800km are optimal to satisfy the identified requirements. Comparisons with other orbits of different inclinations are also shown. Four operation modes and a daily schedule of spacecraft maneuver are found from the Sun-synchronous orbital model. It is shown that the scientific objectives of K-4 can be achieved with moderate levels of design and operation risks.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 1999년도 제12회 학술강연회논문집
• /
• pp.24-24
• /
• 1999

This study addresses the effectiveness of TEC(Thermoelectric cooler) application for spacecraft thermal control. The required radiator area and power consumption characteristics of active thermal control using TEC are compared with the passive control at BOL and EOL through unsteady thermal analyses by calculating external heat fluxes. When the component operating temperature is low enough in TEC active control, the required radiator area can be smaller than the passive thermal control. TEC also needs less power consumption than the passive control under the condition that the temperature of cooling pars is low enough and/or the design temperature margin of the components is narrow enough.

• 한국항공우주학회지
• /
• 제39권5호
• /
• pp.466-473
• /
• 2011

인공위성의 열제어는 인공위성이 운용궤도상에서 겪는 고진공, 극한의 온도변화 환경에서 위성 구성품의 온도변화를 허용한계 온도 범위 내에서 유지하는데 목적이 있다. 본 연구에서는 저궤도 관측위성(LEO)의 광학탑재체에 대한 열해석 과정으로 열진공 시험 조건, 열진공 챔버의 형상, 위성 탑재체 내부의 열적 환경을 고려하여 열해석 모델을 구성하고 궤도 조건에 따른 열해석을 수행하였다. 또한 광학탑재체의 지상 열진공 시험 조건에 따른 열해석 수행하여 열진공 시험을 위한 시험조건을 정립하였다.

• 대한원격탐사학회:학술대회논문집
• /
• 대한원격탐사학회 2002년도 Proceedings of International Symposium on Remote Sensing
• /
• pp.815-820
• /
• 2002

MSC as a payload of KOMPSAT-2 is an optical telescope for earth imaging on a sun-synchronous orbit. The MSC is a Ritchey-Chretien type telescope composed of hyperbolic primary and secondary mirrors with focal correcting lenses. Their relative positions should be kept aligned during imaging operation. However, the MSC is exposed to adverse thermal environment on orbit which can have some impacts on optical performance as well as structural endurance. Solar incidence can cause non-uniform temperature rise on the tube which entails unfavorable thermal distortion. Three options were proposed, which were internal shield, external mechanical shield and spacecraft maneuvering. After the trade-off studies, internal sun shield was selected as a realistic and optimal solution to minimize the effect of the solar radiation. In this paper, pros and cons are explained for the three possible choices and a design of the internal shield is discussed.

• 한국항공우주학회지
• /
• 제40권2호
• /
• pp.178-183
• /
• 2012

위성체의 열진공 시험에는 우주 열환경을 모사하기 위하여 직접 방열판 표면에 열을 공급하는 접촉식 히터와 일정 거리를 두고 간접적으로 복사에 의해 열을 공급하는 비접촉식 히터가 사용된다. 이는 태양 복사 뿐 아니라 지구의 적외선 및 알베도(Albedo)를 모사하며, 열환경 시험 요구에 따라 정의된 온도 조건에 필요한 열을 공급하기도 한다. 일반적으로 접촉식 히터 사용이 불가할 경우 비접촉식 히터를 사용하게 되는데, 이때 복사에 의한 열전달량을 고려하여 적절한 히터파워를 산정하고 히터 미작동시 방열판과 챔버 슈라우드와 열교환에 있어 간섭이 없도록 히터의 위치를 설정하는 것이 필요하다. 본 논문은 열해석상용 프로그램인 SINDA를 이용하여 비접촉식 히터의 최적화 열설계를 수행하였으며, 이를 통해 시험시 유효한 설계값을 도출하였다.

• 한국항공우주학회지
• /
• 제33권8호
• /
• pp.99-104
• /
• 2005

인공위성에서 구조체의 역할은 발사환경 및 궤도상의 모든 발생 가능한 환경에서 위성체를 안전하게 지지하는 것이다. 인공위성의 개발단계에서 구조 및 열 개발모델은 유한요소모델 보정 및 구조강도/특성 확인 등의 구조적인 특징과 열평형시험을 통한 열적 안정성의 확인을 그 목적으로 한다. 이때 얻어진 결과는 실제 비행모델의 개발 시 구조 및 열적 안정성 검증 등의 중요한 자료로써 활용된다. 본 논문에서는 고정밀 지구관측위성의 구조 및 열 개발모델에 대해 구조 관점에서의 설계/해석에 대해 기술하고 또한 모달 시험을 통한 시험결과와 유한요소해석과의 비교에 대해 기술한다.

• 한국소음진동공학회:학술대회논문집
• /
• 한국소음진동공학회 2005년도 춘계학술대회논문집
• /
• pp.949-952
• /
• 2005

According to the national space program in Korea, is satellites will be launch into space up to 2015. Especially, KARI is going to develope of its own a high resolution camera of less than 1m to be mounted on next Multipurpose Satellite. When performing testing of large spacecraft or hardware that will be launched into orbit, it is necessary to conduct a testing with space-simulated environment. To achieve this requirement, thermal vacuum chamber is generally used. KARI has been developed a very Large Thermal Vacuum Chamber(LTVC) from 2003 to accomodate future space program, such as KOMPSAT, COMS, and Launch vehicles. This new facility will be used to qualify the first self developed High Resolution Camera, which will be loaded on KOMPSAT-3. To perform an optical test for space camera, it is necessary to provide vibration free environment. Thus the vibration responses on the optical table due to external vibration should be minimized by using a special isolation system. In this paper, we propose the concept design of vibration isolation system for the development of the high resolution camera.

• 대한원격탐사학회:학술대회논문집
• /
• 대한원격탐사학회 2002년도 Proceedings of International Symposium on Remote Sensing
• /
• pp.229-234
• /
• 2002

Under the hostile influence of the extreme space environmental conditions due to the deep space and direct solar flux, the thermal control in space applications is especially of major importance. There are tight temperature range restrictions for electro-optical elements while on the other hand there are low power consumption requirements due to the limited energy sources on the spacecraft. So, we usually have strong requirement of thermal and power control module in space applications. In this paper, the design concept of a thermal and power control module in the MSC(Multi-Spectral Camera) system which will be a payload on KOMPSATII is described in terms of H/W & S/W. This thermal and power control module, called THTM(Thermal and Telemetry Module) in MSC, resides inside the PMU(Payload Management Unit) which is responsible for the proper management of the MSC payload for controlling and monitoring the temperature insides the EOS(Electro-Optic System) and gathering all the analog telemetry from all the MSC sub-units, etc. Particularly, the designed heater controller has the special mode of "duty cycle" in addition to normal closed loop control mode as usual. THTM controls heaters in open loop according to on/off set time designed through analysis in duty cycle mode in case of all thermistor failure whereas it controls heaters by comparing the thermistor value to temperature based on closed loop in normal mode. And a designed THTM provides a checking and protection method against the failure in thermal control command using the test pulse in command itself.

• Advances in aircraft and spacecraft science
• /
• 제2권2호
• /
• pp.109-124
• /
• 2015

This paper deals with the aerodynamic and aerothermodynamic trade-off analysis of a hypersonic flying test bed. Such vehicle will have to be launched with an expendable launcher and shall re-enter the Earth atmosphere allowing to perform several experiments on critical re-entry phenomena. The demonstrator under study is a re-entry space glider characterized by a relatively simple vehicle architecture able to validate hypersonic aerothermodynamic design database and passenger experiments, including thermal shield and hot structures. A summary review of the aerodynamic characteristics of two flying test bed concepts, compliant with a phase-A design level, has been provided hereinafter. Several design results, based both on engineering approach and computational fluid dynamics, are reported and discussed in the paper.