• 한국항공우주학회지
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• 제46권7호
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• pp.592-601
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• 2018

군용항공기에 장착되는 전자 장비 중 하나인 항공장착물 GPS/INS 통합항법장치는 투하전에는 항공기 날개에 가려 GPS 위성 신호의 직접적인 수신이 불가능하므로 항공기로부터 GPS 항법 데이터를 전달 받아 필터 통합에 이용하고, 투하 후에는 안테나를 통해 직접 수신한 GPS 정보를 이용하여 통합 항법을 수행한다. 이때, 무선을 이용하여 GPS 항법데이터를 전송할 경우 항공기의 별다른 개조 없이 구형 항공기에서도 운용이 가능하다. 그러나 항공기의 항법데이터가 무선을 통해 장착물의 통합항법필터에 전달되기까지 지연이 발생하게 되며, 이는 GPS 측정치와 INS 정보의 시각동기에 영향을 미쳐 통합항법 성능에 영향을 미치게 된다. 이에 본 논문에서는 무선을 통하여 GPS 데이터를 수신하는 항공장착물의 GPS/INS 통합항법시스템을 구현할 때 발생할 수 있는 생성 및 전송지연의 영향을 분석하고 이를 보상하는 알고리즘을 제안하였다.

• Journal of Positioning, Navigation, and Timing
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• 제1권1호
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• pp.45-49
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• 2012

The flight performance evaluation of navigation system is very significant because the reliability of navigation data directly affect the safety of aircraft. Especially, the high-level navigation system such as DGPS/INS, need more precise flight performance evaluation method. The performance analysis is evaluated by comparing between the navigation system in aircraft and reference trajectory which is more precise than navigation system in aircraft. In order to verify DGPS/INS performance of m-level, the GPS receiver, which is capable post-processed Carrier-phase Differential GPS(CDGPS) method of cm-level, have to be used as reference system. The DGPS/INS is estimated the Center of Gravity (CG) point of aircraft to offer precise performance while the reference system is output the position of GPS antenna which is mounted on the outside of aircraft. Therefore, in order to more precise performance evaluation, it needs to compensate the lever arm and coordinates transformation. This paper use quaternion and Direct Cosine Matrix(DCM) methods as coordinate transformation matrix in lever arm compensation of CDGPS reference trajectory. And it compares NED errors of DCM and quaternion transformation in lever arm of reference trajectory via DGPS/INS result.

• Journal of Positioning, Navigation, and Timing
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• 제12권4호
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• pp.379-389
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• 2023

According to the Korea Urban Air Mobility (K-UAM) Concept of Operation (ConOps), the Global Navigation Satellite System (GNSS) is recommended as the primary navigation system and the performance specification will be implemented considering the standard of Performance Based Navigation (PBN). However, by taking into account the characteristics of an urban environment and the concurrent operations of multiple UAM aircraft, the current PBN standards for civil aviation seem difficult to be directly applied to an UAM aircraft. Therefore, by referring to technical documents published in the literature, this paper examines the feasibility of applying the proposed performance requirements to K-UAM, which follows the recommendation of navigation performance requirements for K-UAM. In accordance with the UAM ConOps, the UAM aircraft is anticipated to maintain low altitude during approach and landing phases. Subsequently, the navigation performance degradation could occur in the urban environment, and the primary degradation factor is identified as multipath error. For this reason, to ensure the safety and reliability of the K-UAM aircraft, it is necessary to analyze the degree of performance degradation related to the urban environment and then propose an alternative aid to enhance the navigation performance. To this end, the aim of this paper is to model the multipath effects of the GNSS in an urban environment and to carry out the simulation studies using the real GNSS datasets. Finally, the initial navigation performance requirement is proposed based on the results of the numerical simulation for the K-UAM.

• International Journal of Aeronautical and Space Sciences
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• 제1권1호
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• pp.81-91
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• 2000

The mechanization of navigation equation is depending on the designer according to the orientation vector relating the body frame to a chosen to inertial and navigation frames for its purposes. This paper considers the appropriate Earth Fixed frame for short range vehicle and develops a mechanization and algorithm for Strapdown Inertial Navigation System(SDINS). This mechanization consists of two parts : translational mechanization and rotational mechanization{attitude determination). The accuracy, availability and performance of this SDINS mechanization are verified on the simulation and the numerical method for integration attitude propagation is compared with a well-known method in a precession motion.

• 한국정보통신학회논문지
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• 제16권2호
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• pp.288-295
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• 2012

최근 소득수준이 올라감으로서 레저용 경량 항공기를 통한 여가활용 인구가 늘어나고 있다. 하지만 레저용 경량 항공기는 민항기나 군용 항공기에 비해 비교적 저가이기 때문에 탑재하고 있는 항공기기도 다른 항공기에 비해 잘 갖추고 있지 않는 경향이 있다. 본 논문에서는 최근 대중화되고 있는 스마트폰(iPhone, 안드로이드 폰, 윈도우 모바일 폰, 바다 폰 등) 및 스마트 패드(iPad, 갤럭시 Tab 등)를 활용하여 레저용 경량 항공기의 운항에 보조적인 기능을 제공할 수 있는 경량 항공기용 내비게이션을 설계하고 구현하고자 한다.

• 제어로봇시스템학회논문지
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• 제21권7호
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• pp.691-698
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• 2015

Inertial Navigation Systems (INS) are widely used as the main navigation device for aircraft. To get the initial attitude, the INS requires the initial alignment before navigation starts. An aircraft also needs an engine test procedure that causes some vibrations before flight. An INS can't be aligned in a vibration environment so the initial alignment is performed before the aircraft engine test. Therefore, the initial alignment time of an INS has been a major factor in limiting an aircraft's takeoff response time. In this paper, we designed an initial alignment algorithm that can be executed even in disturbances such as aircraft run-up. We demonstrated verification of the algorithm that is embedded on the real INS and testing methods to evaluate the alignment of the INS. We also analyzed the test results of the proposed initial alignment algorithm that is performed during a real aircraft run-up.

• Journal of Positioning, Navigation, and Timing
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• 제9권2호
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• pp.125-129
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• 2020

In this paper, Zero velocity UPdaTe (ZUPT) is implemented on the navigation system of Remotely Piloted Aircraft for GNSS denied environment. RPA's navigation system suffers from lack or loss of satellite signal while maintenance or ground test inside a hangar. Although some of the hangars install GPS repeaters for indoor tests, the anti-jamming equipment with array antenna blocks the repeater signal regarding them as hostile jamming signal. With ZUPT, an aircraft navigation system can be tested free from the divergence of navigation solution without line-of-sight satellites. The designed ZUPT aided centralized Kalman Filter is implemented on the Embedded GPS&INS and simulated with Captive Flight Test data. The simulation result shows stable navigation solution without GNSS updates.

• International journal of advanced smart convergence
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• 제9권3호
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• pp.207-214
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• 2020

Currently, the operation of unmanned aerial vehicle (UAV) is regulated to be able to fly only within the visible range, but in recent years, the needs for operation in the invisible area, in the urban area and at night have increased. In order to operate UAVs in the invisible area, at night, and in the urban area, a flight path for UAVs must be prepared like those operated by manned aircraft, and for this, it is necessary to establish an unmanned aircraft system traffic management (UTM). In order to establish the UTM, information on the minimum separation distance to prevent collisions with UAVs and buildings is required, and accordingly, information on the navigation performance of UAVs is required. In order to analyze the navigation performance of an UAV, total system error (TSE), which is the difference between the planned flight path and the actual location of the UAV, is required. If the collected data are insufficient and classification according to integrity, independence, and direction is not performed, accurate navigation performance is not derived. In this paper, propose a navigation performance analysis method of UAV that is derived TSE using flight data and modeled with normal distribution, analyze performance.

• 한국항행학회논문지
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• 제17권6호
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• pp.765-776
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• 2013

민수용 항공기 산업에서는 해당 제품의 성능이 우수 하더라도 항공기의 항행 안전성을 확보하기 위하여 필요한 안전성 요구사항에 대한 적합성을 인정을 받지 못하면 법적으로 항공기에 사용 될 수 없는 특성이 있다 [1]. 이와 같이 다양하게 적용되어 지고 있는 항공 전자장비의 항행 안전성을 위하여 민간용 항공기에는 기술표준품 인증 제도를 시행하고 있다. KTSO-C113은 항공기용 다목적 전자식 디스플레이의 기술표준품을 인증하는 최소성능표준을 포함하고 있다. 기술 표준품 형식승인은 설계 및 제조에 대한 승인을 의미하여 항공기 장착하여 사용하기 위해서는 별도의 승인이 필요하다. 본 논문을 통하여 항공기용 다목적 디스플레이의 기술 표준품 형식승인 제도 및 인증 요구조건을 소개하고 적합성 입증을 위한 인증 사례를 제시한다.

• 한국항행학회논문지
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• 제24권6호
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• pp.515-520
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• 2020

오늘날 항공기 항행에 있어서 자동조종장치와 FMS (flight management system)의 발전은 조종사들의 작업량감소와 항행 안전유지에 그 성과가 크다고 할 수 있다. 특히 공항의 교통량이 많거나 표준계기 출발 절차 (SID; standard instrument departure)가 복잡한 항행의 경우에 자동조종장치와 FMS 장비의 효과는 더욱 크다. 하지만 일부 공항의 특정한 출발 절차에서 FMS의 오류로 인한 uncommanded turn 이벤트가 발생하여, 항공기가 항로의 중심선에서 벗어나는 경우가 있다. 대부분의 출발 절차가 RNAV(area navigation) 운영이 요구됨으로, 조종사의 상황인식과 수정 조작이 항로 편차(deviation)를 최소화하여, RNAV의 안전을 유지하는 유일한 방법이다. 이와 관련하여 uncommanded turn 이벤트의 국내외 발생 현황을 기종별, 공항별, 비행 단계별로 조사하고 항공사의 uncommanded turn 이벤트 경감방안 분석을 통해 해당 이벤트의 더욱 근본적인 재발 방지대책 마련의 필요성 및 시사점을 도출하고자 한다.