• Aerospace Engineering and Technology
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• v.10 no.1
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• pp.45-53
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• 2011

This paper is technical review about Direct Sequence Spread Spectrum(DSSS) to apply in launch vehicle system. First, we introduce communication protocol(carrier frequency, code length, process gain, data rate, chip rate etc) about several application system using DSSS. And then, we survey and summarize the effect of doppler shift to the DSSS. The doppler shift is important error factor for PN code tracking in the fast moving system like launch vehicle. So, spread spectrum code acquisition technique for a direct sequence system in the presence of doppler effect must be investigated.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.9
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• pp.60-66
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• 2006

Now, on developing COMS(Communication, Ocean and Meteorological Satellite) has solar panel on the south panel only. Therefore, the wheel off-loading has to be performed periodically to reduce a induced momentum energy by a asymmetric solar panel. One of two East/West station keeping maneuver to correct simultaneously longitude and eccentricity, orbit corrections may be performed during one of the two wheel off-loading manoeuvres per day to get enough observation time for meteorological and ocean sensor. In this paper, we applied a linearized orbit maneuver equation to acquire maneuver time and delta-V. Nonlinear simulation for the station keeping is performed and compared with general station keeping strategy for fuel reduction.

• Aerospace Engineering and Technology
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• v.1 no.1
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• pp.135-140
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• 2002

The position and trajectory of in-flight rocket are important informations to determine the flight safety of rocket. In general tracking system, radar and transponder are used to acquire position information. Rocket position and trajectory can be determined by using RF communication between ground station and in-flight rocket and antenna position data. Onboard transponder system is composed of RF receiving part, RF transmitting one, decoder and single TX/ RX antenna. Therefore circulator is necessary for minimizing RF signal interference. In this paper, the radar transponder system was developed to track the trajectory and position of KSR-Ⅲ by using radar.

• Current Industrial and Technological Trends in Aerospace
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• v.5 no.1
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• pp.39-55
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• 2007

인류는 달을 보며 우주개발에 대한 꿈을 꾸어왔다. 60년대에서 70년대 중반까지 미 소간의 우주경쟁으로 달 탐사에 큰 예산을 들여 마침내 인류를 달에 착륙시켜 달 탐사를 실현할 수 있었다. 이젠 화성에 인류를 보내기 위한 전초기지를 달에 구축하려고 다시금 미국이 달 탐사를 가동시켰다. 이에 따라 세계 여러 나라가 달에 대해 다시 관심을 고조 시키고 있다. 그래서 이 논문에서는 90년대와 최근에 재 시작된 달 탐사위성의 개발동향을 조사하여 기술하였다. 대상 위성 프로젝트는 미국의 클레멘타인과 루나 프로스펙터, 유럽연합의 스마트-1호, 일본의 셀레네, 중국의 창어-1호, 인도의 찬드라얀-1호, 미국의 LRO 달 탐사 궤도선, 러시아의 루나-글로브 위성들의 주요특성과 탑재체, 지상국, 임무궤적 및 달 임무 궤도에 대해 개괄적으로 기술하였다. 기술 특징으로는 위성 제작기술 발전에 따라 경량화에 중점을 두어 위성을 소형화 하였으며, 통신방식에 있어서는 X 및 Ka대역을 사용하여 데이터 전송속도를 현저히 증가 시켰으며, 위성 및 지상의 안테나의 크기를 줄일 수 있었으며, 전기추력기를 사용하여 소형위성으로도 달 탐사를 실현시켰다. 그리고 다른 나라에서 개발되는 달 탐사위성의 개발 예산을 살펴보면 약 1억불 정도이면 소형 급의 위성을 개발하여 달 궤도에 진입시켜 달 과학탐사 임무를 수행할 수 있다고 할 수 있겠다. 따라서 우리나라도 지난 15년 이상 지구궤도 위성을 성공적으로 개발하며 구축한 기술을 바탕으로 달 탐사 위성의 개발에 대한 가능성을 가지고 있다고 본다. 이제 우리나라도 인류의 미래우주개발의 일익을 담당하고자 달 탐사위성 프로젝트를 준비해야한다

• Aerospace Engineering and Technology
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• v.10 no.2
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• pp.82-86
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• 2011

This paper presents an RF Electric field assessment at 2.290 [GHz] inside launcher PROTON M/Breeze M long fairings, produced by COMS TM. COMS intentional RE due to TM ON under fairing has been assessed considering PROTON M / BREEZE M fairing characteristics. As fairings of all launchers present similar sizes, a similar E-field level under fairing is expected for the other launchers. As a result, the RE level under faring is compliant with COMS RS limits, but is not compliant with RS requirements of the launcher PROTON M/Breeze M.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.5
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• pp.104-108
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• 2004

The most of the CDMA mobile communication depends on the GPS for the time synchronization. Then, we must prepare alternative system against the unusable GPS like a unexpectable accident or strategic purpose by the USA government. In this study, we have constructed ground test segment for the time synchronization system using the geostationary satellite. In addition. we have designed, manufactured and tested the transmitting and receiving board to receive 1 PPS signal from atomic clock for transmitting stored data in buffer to satellite modem and to produce 1 PPS signal from satellite modem for measuring time delay.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.2
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• pp.170-177
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• 2011

This paper proposes a telemetering method that transmits the real-time data together with the time-delayed data and that merges both data after flight test. The method can minimize the error data which occur in the communication environment affected by the multipath fading and transmit antenna pattern when telemetry data are received during the flight test. This method was applied to the design of the telemetry unit and the development of data merging program. By merging the resulting data of flight test and analyzing synchronization errors, its efficiency for the telemetry link is verified.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.6
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• pp.565-573
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• 2008

The behavior-based decentralized approach is considered for multi-UAV formation flight. It is assumed that each UAV has its own mission of flying to a specified region, while the distances between UAVs should be maintained. These two requirements may conflict with each other. To design the controller, coupled dynamics approach is applied to multi-UAVs with an assumption that each UAV can communicate with each other to share the state-information. Control gain matrices are optimized to acquire better performances of formation flying. To validate the proposed control approach, numerical simulation is performed for the waypoint-passing mission of multi-UAVs.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.5
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• pp.429-436
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• 2017

Since the telemetry performance using the time-delayed data dissipates the wireless channel resources, we propose the spectral efficient retransmission scheme in this paper. In the proposed scheme, the telemetry data is retransmitted based on triggered memory to improve the spectral efficiency. The proposed scheme minimizes the error caused by multipath fading, antenna pattern as well as the error caused by the flight events. In the flight simulation data, we show the proposed scheme improves the telemetry performance based on spectral efficient retransmission.

• Aerospace Engineering and Technology
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• v.7 no.1
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• pp.142-150
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• 2008

In order to ensure the individual and mutual performances among the telemetry system, tracking system, flight termination system, GPS, and inertial navigation & guidance system which are installed in the KSLV-I 2nd stage and ground equipment of the Naro space center, flight test using a light airplane is required. Since the high degree of test efficiency is fulfilled through the minute plan and analysis about selection of the equipment which are applicable to the test, harness, operation strategy, and antenna installation. KSLV-I communication environment and flight profile should be precisely taken into account during the flight test. In this document, overall aspect of the KSLV-I 2nd stage equipment specification, a rack for the installation, harness, the airplane specification, and flight route which are required for the effective flight test are presented.