• Journal of Astronomy and Space Sciences
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• 제39권4호
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• pp.181-194
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• 2022

Korea Pathfinder Lunar Orbiter (KPLO), also known as Danuri, was successfully launched on 4 Aug. from Cape Canaveral Space Force Station using a Space-X Falcon-9 rocket. Flight dynamics (FD) operational readiness was one of the critical parts to be checked before the flight. To demonstrate FD software's readiness and enhance the operator's contingency response capabilities, KPLO FD specialists planned, organized, and conducted four simulations and two rehearsals before the KPLO launch. For the efficiency and integrity of FD simulation and rehearsal, different sets of blind test data were prepared, including the simulated tracking measurements that incorporated dynamical model errors, maneuver execution errors, and other errors associated with a tracking system. This paper presents the simulation and rehearsal results with lessons learned for the KPLO FD operational readiness checkout. As a result, every functionality of FD operation systems is firmly secured based on the operation procedure with an enhancement of contingency operational response capability. After conducting several simulations and rehearsals, KPLO FD specialists were much more confident in the flight teams' ability to overcome the challenges in a realistic flight and FD software's reliability in flying the KPLO. Moreover, the results of this work will provide numerous insights to the FD experts willing to prepare deep space flight operations.

• 대한임베디드공학회논문지
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• 제11권1호
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• pp.21-27
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• 2016

An integrated display software platform for small UAV is developed based on parallel processing technique in this paper. When the small UAV with high-performance camera and avionic modules is employed to various surveillance-related missions, it is important to reduce the operator's workload and increase the monitoring efficiency. For this purpose, it is needed to develop an efficient monitoring software enable to manipulate the image and flight data obtained during flight within the given processing time and display them simultaneously. In this paper, we set up requirements and suggest the architecture for the software platform. The integrated software platform is implemented with parallel processing scheme. Based on AR drone, we verified that the various data are concurrently displayed by the suggest software platform.

• 한국정보처리학회:학술대회논문집
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• 한국정보처리학회 2012년도 춘계학술발표대회
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• pp.492-494
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• 2012

저궤도 위성은 위성과 지상과의 통신시간이 제한되어 있으므로 제한된 시간에 위성의 대용량메모리(Mass Memory)에 저장된 데이터를 전송받아야 하는데, 이를 위해 저장되는 데이터 량을 정확히 예측할 수 있어야 하고, 저장된 데이터 량에 따라 지상으로 전송하는데 소요되는 시간을 예측할 수 있어야 한다. 본 논문은 위성에 저장되고 있는 Telemetry 종류에 따라 대용량메모리에 저장되는 데이터 량을 예측하고, 저장된 데이터 량에 따라 지상으로 전송하는데 소요되는 시간을 계산하기 위해 개발된 플레이백 시간 예측 프로그램에 대해 서술한 것이다.

• 한국정보처리학회:학술대회논문집
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• 한국정보처리학회 2011년도 추계학술발표대회
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• pp.520-522
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• 2011

위성으로부터 전송받은 Telemetry 플레이백 데이터 파일들을 적절한 크기로 또는 저장된 시간에 따라 병합하거나 분할할 수 있는 플레이백 파일 병합/분할 프로그램을 구현하였다. 기존에 플레이백 데이터가 정상적으로 수신되었는지를 점검하기 위한 플레이백 데이터 자동 분석 프로그램이 있는데, 기존의 프로그램을 윈도우 기반으로 보다 편리하게 사용할 수 있도록 전체적으로 보완하였고, 여기에 플레이백 파일 병합/분할 기능을 추가하여 전체적으로 하나로 통합하였다. 본 논문은 차세대 저궤도 위성에서 수행되는 데이터 저장 및 전송에 대한 내용과 새롭게 개선된 플레이백 데이터 자동분석 프로그램 및 플레이백 파일 병합/분할 프로그램에 대해 기술한 것이다.

• 제어로봇시스템학회논문지
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• 제14권8호
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• pp.824-836
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• 2008

Relaxed static stability(RSS) concept has been applied to improve aerodynamic performance of modern version supersonic jet fighter aircraft. Therefore, flight control systems are necessary to stabilize an unstable aircraft, and provides adequate handling qualities and achieve performance enhancements. Standard FCSDVP (Flight Control System Design and Verification Process) is provided to reduce development period of the flight control system. In addition, if this process is employed in developing flight control system, it reduces the trial and error for development and verification of flight control system. This paper addresses the flight control system design and verification process for the RSS aircraft utilizing design goal based on military specifications, linear and nonlinear system design and verification based on universal software, handling quality test based on HILS(Hardware In-the-Loop Simulator) environment, and ground and flight test results to verify aircraft dynamic flight responses.

• 한국항공우주학회지
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• 제49권6호
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• pp.473-480
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• 2021

소형 무인비행체 드론의 비행제어기(Flight Controller) 소프트웨어로 널리 사용되고 있는 오픈소스(Open Source)에 대한 정적분석(Static Analysis)을 통해 소프트웨어 품질의 문제점을 분석하고 개선 방안을 제시한다. 소프트웨어 품질 기준으로는 국제적으로 널리 적용되고 있는 MISRA 코딩 규칙을 선정하였으며, 정적분석 도구는 국제 도구인증(Tool Certification)을 받아 항공분야 뿐만 아니라 안전성(Safety)이 요구되는 자동차, 철도, 원자력, 의료 등 모든 산업에서 활용되고 있는 LDRA Tool을 사용하였다. 오픈소스 모듈의 구조, 사용 데이터 분석, 코딩 규칙 준수, 품질 지표(복잡도 및 시험성) 등 소프트웨어의 품질 전반에서 안전성을 위협하는 문제점들을 발견하였으며, 이에 대한 개선 방안을 제시하였다.

• Journal of Astronomy and Space Sciences
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• 제28권3호
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• pp.241-252
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• 2011

A simulated network protocol provides the capability of distributed simulation to a generic simulator. Through this, full coverage of management of data and service handling among separated simulators is achieved. The distributed simulation environment is much more conducive to handling simulation load balancing and hazard treatment than a standalone computer. According to the simulated network protocol, one simulator takes on the role of server and the other simulators take on the role of client, and client is controlled by server. The purpose of the simulated network protocol is to seamlessly connect multiple simulator instances into a single simulation environment. This paper presents the development of a simulated network (simNetwork) that provides the capability of distributed simulation to a generic simulator (GenSim), which is a software simulator of satellites that has been developed by the Korea Aerospace Research Institute since 2010, to use as a flight software validation bench for future satellite development.

• Journal of Astronomy and Space Sciences
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• 제27권4호
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• pp.407-412
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• 2010

Software reusability is one of key factors which impacts cost and schedule on a software development project. It is very crucial also in satellite simulator development since there are many commercial simulator models related to satellite and dynamics. If these models can be used in another simulator platform, great deal of confidence and cost/schedule reduction would be achieved. Simulation model portability (SMP) is maintained by European Space Agency and many models compatible with SMP/simulation model interface (SMI) are available. Korea Aerospace Research Institute (KARI) is developing hardware abstraction layer (HAL) supported satellite simulator to verify on-board software of satellite. From above reasons, KARI wants to port these SMI compatible models to the HAL supported satellite simulator. To port these SMI compatible models to the HAL supported satellite simulator, simulation scheduler is preliminary designed according to the SMI standard.

• 제어로봇시스템학회논문지
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• 제13권7호
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• pp.694-702
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• 2007

The SSWM(Software Switching Mechanism) of I-processor concept using non-real time in-house software simulation program is an effective method in order to develop the flight control law in desktop or HQS environment. And, this system has some advantages compare to HSWM(Hardware Switching Mechanism) such as remove the time delay effectiveness and reduce the costs of development. But, if this system loading to the OFP(Operational Flight Program), the OFP guarantee the enough throughput in order to calculate the two control law at once. Therefore, the HSWM(Hardware Switching Mechanism) of 2-processor concept is necessary. This paper addresses the concept of HSWM of the HQS-PC interface using TCP/IP(Transmission Control Protocol/Internet Protocol) communication based on flight control law of advanced supersonic trainer. And, the fader logic of TFS(Transient Free Switch) and stand-by mode of reset '0' type are designed in order to reduce the abrupt transient response and minimize the integrator effect in pitch axis. The result of the analysis based on HQS pilot simulation using HSWM reveals that the flight control systems are switching between two computers without any problem.

• 한국항공우주학회지
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• 제48권1호
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• pp.55-62
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• 2020

회전익 헬리콥터의 안정성, 조종성 향상 및 증대를 보장하기 위해서는 디지털 제어기술에 의한 디지털 비행제어시스템의 개발이 필요하다. 헬리콥터 비행제어시스템 설계 및 개발 기술은 해외 선진 항공 개발사의 기술이전 기피 및 불가에 해당하는 핵심기술로써 헬리콥터 비행제어 시스템 운용소프트웨어인 OFP의 기능 요구조건 충족과 더불어 비행안전에 직결되는 시스템 신뢰도의 검증이 필요하며 비행제어 시스템 운용 소프트웨어의 검증 방안 연구는 무엇보다 중요하다. 본 논문에서는 회전익 자동비행제어시스템 소프트웨어의 FMET 수행 및 검증 방안에 관한 연구를 수행하였다.