• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.35 no.11
• /
• pp.1052-1057
• /
• 2007

A highly reliable Video Transmission System (VTS) was developed in order to obtain both video and digital data simultaneously in the real time flight test situation of a flying vehicle. The VTS integrates GPS data, digital telemetry data and video signals into a compact digital data package which is compressed and processed by an MPEG-2 Encoder and a DVB-S modulator respectively. The DVB-S modulator is composed of a specially devised Forward Error Correction processor and base band QPSK modulator. The designed VTS was verified and proved for its required functioning and performance through separate flight tests using an airplane and missiles.

• Aerospace Engineering and Technology
• /
• v.8 no.2
• /
• pp.41-53
• /
• 2009

This study describes to design the interface between VDL (VHF Digital Link) Mode 2 system and AOA (ACARS Over AVLC) network. KARI-Wrapper using aircraft and ground station design requirements should be designed to the system configuration of the in-out interface of the components and analyzed with the ARINC 618, 620, 622 documentations. According to the system interface test, we are verified the satisfactions of uplink and downlink VDL Mode 2 requirements.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.33 no.9
• /
• pp.104-112
• /
• 2005

This paper presents the technique to develop an operational flight program(OFP) of avionic system computer(ASC) which integrates the avionics control, navigation and fire control and provides informations for flight, navigation and weapon aiming missions. For the development of the OFP of ASC, two i960KB chips are used as central processing units board and standard computer interface library(SCIL) which is built in house is used. The Irvine compiler corporation(ICC) integrated development environment(IDE) and the programming language Ada95 are used for the OFP development. We designed the OFP to a computer software configuration item(CSCI) which consists of to three parts for independency of software modules. The OFP has been verified through a series of flight tests. The relevant tests also have been rigorously conducted on the OFP such as software integrated test, and ground functional test.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.39 no.7
• /
• pp.666-673
• /
• 2011

To perform effective integration test of avionics equipments, the importance of a setup for integration test environment has been increasing in recently developed aircraft. Especially, the development of integration test equipment is necessary for minimizing the development period and reliability of integration test. This paper treats the model development for optimal working of integration test after analyzing the characteristics of each MEP equipments for Surion(KUH). Models, whose main role is troubleshooting of equipment and simulation for missing equipments, consists of dynamic, behavior, and ICD models depending on the dynamic characteristics. Software test for both unit level and system level are performed to verify the model reliability. By conducting integration test using SIL, it is confirmed that the developed models are suitable for integration function test of the MEP system.

• 한국항공운항학회:학술대회논문집
• /
• 2015.11a
• /
• pp.252-256
• /
• 2015

항공기 운항과 밀접하게 관련되는 장비중에 하나가 CNS&ATM관련 탑재 항공전자 장비이다. 임베디드 소프트웨어가 들어간 항전장비 개발에 에러 유입이 주로 요구도 분석 및 아키텍쳐 설계에서 일어난다. 항공전자 장비 개발에 운영자가 적극적으로 참여함으로써 에러 발생 요인 감소, 고장 영향성 분석, 요구도 기반 시험 등을 효율적으로 수행할 수가 있어, 장비의 개발기간 및 비용을 줄일 수가 있다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.32 no.4
• /
• pp.101-110
• /
• 2004

Flight and Qualification Models of Single Board Computer (SBC), called On-Board Computer (OBC), for HAUSAT-l picosatellite, which is scheduled to launch on September, 2004 by Russian "Dnepr" launch vehicle, have been developed. The OBC of HAUSAT-1 has been designed with some improved features compared to other picosatellites. A multifunctional controller and up-to-date SPI (Serial Peripheral Interface) and 1-Wire interface are implemented to simplify the harness routing and to minimize the mass and size of OBC. The improved fault-tolerant architecture design methodology is incorporated in the HAUSAT-1 OBC to protect against space radiation environment. The functions of the OBC were fully tested and verified by the Electrical Test Bed (ETB) model. This paper is also addressing the environmental test results, such as random vibration and thermal vacuum tests.

• Proceedings of the Korean Vacuum Society Conference
• /
• 2013.02a
• /
• pp.147-147
• /
• 2013

인공위성이 임무를 수행하는 우주공간은 고진공 환경과 태양 복사열에 의한 고온 환경 및 극저온이 반복되는 가혹한 환경으로, 위성체는 이러한 가혹한 우주환경의 영향으로 인해 주요부품의 기능장애가 초래되기도 하며 이는 결국 임무의 실패로 이어지도 한다. 따라서 10E-06 torr 이하의 고진공과 $-180^{\circ}C$의 극저온 환경으로 일컬어지는 우주환경을 지상에서 모사하여 위성체의 안정성 및 신뢰성을 시험하기 위해서 열진공 시험장비를 이용한 열진공시험을 수행한다. 한국항공우주연구원에서는 인공위성의 탑재체인 광학카메라의 국산화 개발을 위하여 우주공간의 고진공과 극저온 상태를 모사할 수 있는 ${\varphi}4m{\times}L10m$ 규모의 광학탑재체 전용 열진 공챔버를 국산화 개발하여 사용하고 있다. 탑재체 진공시험은 진공환경의 조성과 함께 외부진동을 완벽하게 차단하는 것이 매우 중요하다. 본 논문에서는 한국항공우주연구원에서 보유한 광학탐재체용 진공챔버에서 진공 유지와 진동 차단을 동시에 수행하고 있는 방법에 대해 살펴보고자 한다.

• 한국항공운항학회:학술대회논문집
• /
• 2004.11a
• /
• pp.266-269
• /
• 2004

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.35 no.3
• /
• pp.253-259
• /
• 2007

Standard design and suitable environmental test method should be applied to increase the reliability of UAV flight control systems. UAV flight control systems under development domestically have enough capabilities for complicated missions. However, most low cost systems are not designed with concepts of compatibility, adaptability, and environmental compliance. This paper explains ATR(Air Transport Rack) standard that is widely used on aircraft. The paper presents a design uses commercial off-the-shelf parts. The paper also presents various environmental standards for airborne equipments, including U.S. military specifications. The developed FCS was tested under these specifications. The paper shows the test procedures and results.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.44 no.2
• /
• pp.156-164
• /
• 2016

Qualification model(QM) of main payloads including concentrating photovoltaic system using fresnel lens, heating wire cutting type shockless holding and release mechanism, and MEMS-based solid propellant thruster have been developed for the STEP Cube Lab.(Cube Laboratory for Space Technology Experimental Project), which is a pico-class satellite for verification of core space technologies. In this study, we have verified structural safety and functionality of the developed payloads under a qualification temperature range through the QM thermal vacuum test. Additionally, a reliability of thermal model of the payloads has been confirmed by performing a thermal correlation based on the thermal balance test results.