• 산업경영시스템학회지
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• 제39권3호
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• pp.1-9
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• 2016

NSS (Navigation satellite system) provides the information for determining the position, velocity and time of users in real time using satellite-networking, and is classified into GNSS (Global NSS) and RNSS (Regional NSS). Although GNSS services for global users, the exactitude of provided information is dissatisfied with the degree required in modern systems such as unmanned system, autonomous navigation system for aircraft, ship and others, air-traffic control system. Especially, due to concern about the monopoly status of the countries operating it, some other countries have already considered establishing RNSS. The RNSS services for users within a specific area, however, it not only gives more precise information than those from GNSS, but also can be operated independently from the NSS of other countries. Thus, for Korean RNSS, this paper suggests the methodology to design the satellite constellation considering the regional features of Korean Peninsula. It intends to determine the orbits and the arrangement of navigation satellites for minimizing PDOP (Position dilution of precision). PGA (Parallel Genetic Algorithm) geared to solve this nonlinear optimization problem is proposed and STK (System tool kit) software is used for simulating their space flight. The PGA is composed of several GAs and iterates the process that they search the solution for a problem during the pre-specified generations, and then mutually exchange the superior solutions investigated by each GA. Numerical experiments were performed with increasing from four to seven satellites for Korean RNSS. When the RNSS was established by seven satellites, the time ratio that PDOP was measured to less than 5 (i.e. better than 'Good' level on the meaning of the PDOP value) was found to 94.3% and PDOP was always kept at 10 or less (i.e. better than 'Moderate' level).

• Journal of Positioning, Navigation, and Timing
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• 제10권2호
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• pp.91-102
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• 2021

In this paper, a fully reconfigurable Software Defined Radio (SDR) for multi-constellation and multi-frequency Global Navigation Satellite System (GNSS) receivers is presented. The reconfigurability with respect to the data structure, variability of signal and receiver parameters, and receiver's internal functionality is presented. The configuration file, that is modified to lead to an entirely different operation of the SDR in response to specific target signal scenarios, directly determines the operating characteristics of the SDR. In this manner, receiver designers can effectively reduce the effort to develop many different combinations of multi-constellation and/or multi-frequency GNSS receivers. Finally, the implementation of the presented fully reconfigurable SDR is included with the experimental processing results such as acquisition, tracking, navigation for the received signals in the realistic fields.

• 한국항공우주학회지
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• 제37권11호
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• pp.1112-1120
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• 2009

본 논문에서는 현재 궤도상에서 운용중인 위성들을 특정 임무수행을 하도록 각 위성들 을 허용된 추진제량을 초과하지 않는 범위 내에서 궤도기동을 통해 재배치함으로써 일시적인 위성군집궤도를 형성하기 위한 목적궤도 설계기법을 소개하였다. 설계기법의 응용성을 확인하기 위해 본 연구에서는 두 가지 문제, 즉 각각 위성들에 대한 허용 추진제량이 모두 다른 경우 지상의 특정 지역을 정찰하는 문제와 지상을 지속적으로 이동하는 이동 물체를 동일한 허용 추진제량을 가진 위성들을 이용하여 정찰하는 문제를 다루었다. 유전 알고리즘을 이용한 접근방법의 유효성을 검증하기 위해 시뮬레이션을 수행하였으며, 결과적으로 현재 궤도배치 상에서 획득할 수 있는 평균재방문주기에 비해 재배치된 궤도상에서의 평균재방문주기가 각각 41%, 42% 감소함을 알 수 있었다. 제안된 방법에 의한 결과는 궤도조정 방법, 궤도상황, 센서 특성, 허용 추진제량, 그리고 추력기의 성능에 따라 다소 달라질 수 있다.

• 항공우주시스템공학회지
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• 제16권2호
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• pp.63-72
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• 2022

초소형위성에 대한 관심이 증가함에 따라 초소형위성군의 성능과 활용도뿐 아니라 위성군의 궤도설계, 궤도배치 기법에 대한 연구가 활발히 수행되고 있다. 본 연구에서는 초소형 위성을 활용한 워커-델타 위성군을 구축하기 위한 궤도배치 기법으로 추력을 이용한 기법과 차등 대기항력 제어 (DADC)를 연구하였다. 추력을 이용할 시, 발사체에 대한 위성의 분리속도와 각도에 따라 궤도배치에 소요되는 시간과 추력량이 달라진다. 초소형위성의 추력시스템 성능을 참고하여 제한된 성능으로 궤도배치를 완료하기 위한 제어전략을 제시하였다. 결과적으로 궤도배치 기간과 총 추력량의 관계를 도출하였다. 차등 대기항력을 이용하면 추력을 소모하지 않는 대신 상대적으로 긴 배치기간을 소요한다. 소프트웨어 시뮬레이션을 통해 일반적인 초소형위성군의 궤도에서 차등 대기항력으로 궤도배치를 완료할 수 있음을 검증하였다. 본 연구 결과를 활용하면 초소형위성군의 궤도배치에 전략을 수립하고 활용할 수 있을 것이다.

• Journal of Positioning, Navigation, and Timing
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• 제12권3호
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• pp.295-306
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• 2023

This paper presents a multi-frequency and multi-constellation Global Navigation Satellite System (GNSS) signal generator that simulates intermediate frequency level digital signal samples for testing GNSS receivers. GNSS signal generators are ideally suited for testing the performance of GNSS receivers and algorithms under development in the laboratory for specific user locations and environments. The proposed GNSS signal generator features a fully-reconfigurable structure with the ability to adjust signal parameters, which is beneficial to generate desired signal characteristics for multiple scenarios including multi-constellation and frequencies. Successful signal acquisition, tracking, and navigation are demonstrated on a verified Software Defined Radio (SDR) in this study. This work has implications for future studies and advances the research and development of new GNSS signals.

• 한국정보기술학회논문지
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• 제17권3호
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• pp.31-41
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• 2019

본 논문에서는 CCSDS에서 권고하고 있는 대역폭 효율적인 변조 방식 중 채널당 2.0, 2.25, 2.5, 2.75 bits/symbol의 전송효율을 가지는 4D-8PSK TCM 시스템의 송신부와 수신부를 설계하고 시뮬레이터를 구현하여 AWGN 환경에서 모의시험을 통하여 BER 성능을 분석한다. 송신부는 CCSDS 표준을 준용하여 설계하고, 수신부는 차동 부호화 및 복호화를 일반화하여 차동 복호기를 설계하며, 트렐리스 복호 알고리즘은 보조격자의 정보와 비터비 알고리즘을 적용하여 설계하고, CCSDS 표준에서 주어진 8차원 성상도 맵퍼의 방정식을 가감법으로 풀어 성상도 디맵퍼를 설계한다. 특히, 컴퓨터 모의실험을 통해 비터비 복호기 설계 시 역추적 깊이에 따른 오류 성능을 제시하여 4D-8PSK TCM 시스템의 최적화된 송/수신부를 구현하고 성능을 분석한다.

• International Journal of Aeronautical and Space Sciences
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• 제18권2호
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• pp.327-333
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• 2017

This study presents the orbit determination (OD) of a candidate Korea Regional Navigation Satellite System (KRNSS) using both inter-satellite links (ISLs) and ground observations. The candidate constellation of KRNSS is first introduced. The OD algorithm based on both ISL and ground observation is developed, and consists of three main components: dynamic model for Korean navigation satellites, measurement model for ISLs and ground observations, and the batch least-square filter for estimating OD parameters. As numerical simulations are performed to analyze the OD performances, the present study focuses on investigating the effects of ISL measurements on the OD accuracy of KRNSS. Simulation results show that the use of ISLs can considerably enhance the OD accuracy to one meter (design preference) under certain distributions of ground stations.

• Journal of Positioning, Navigation, and Timing
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• 제12권4호
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• pp.335-342
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• 2023

Lunar Navigation Satellite System refers to a constellation of satellite providing PNT services on the moon. LNSS consists of main satellite and navigation satellites. Navigation satellites orbiting around the moon and a main satellite moves the area between the moon and the L2 point. The navigation satellite performs the same role as the Earth's GNSS satellite, and the main satellite communicates with the Earth for time synchronization. Due to the effect of the non-uniform shape of the moon, it is necessary to focus on the influence of the lunar gravitational field when designing the orbit simulation for navigation satellite. Since the main satellite is farther away from the moon than the navigation satellite, both the earth's gravity and the moon's gravity must be considered simultaneously when designing the orbit simulation for main satellite. Therefore, the main satellite orbit simulation must be designed through the three-body problem between the Earth, the moon, and the main satellite. In this paper, the orbit simulation tool for main satellite and navigation satellite required for LNSS was designed. The orbit simulation considers the environment characteristics of the moon. As a result of comparing long-term data (180 days) with the commercial program GMAT, it was confirmed that there was an error of about 1 m.

• Journal of Positioning, Navigation, and Timing
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• 제8권4호
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• pp.215-223
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• 2019

This paper analyzes navigation performances of the Korean Positioning System (KPS) constellation with respect to the orbit parameters which fulfills the specification requirements. Specifically, the satellite configuration and navigation requirements of KPS are explained, and the daily mean horizontal dilution of precision (HDOP) and satellite visibility on KPS coverage are analyzed to confirm the adequate orbit parameters. However, due to orbital slot saturation, geostationary-orbit (GEO) satellites may not be allocated in the original orbit as specified in the KPS requirements. Therefore, in a spanned window of 4 degrees from the reference longitude the navigation performance of each GEO satellite orbit is investigated.