• Journal of Positioning, Navigation, and Timing
• /
• 제9권4호
• /
• pp.387-395
• /
• 2020

Accuracy of an integrated Global Positioning System (GPS) / Inertial Navigation System (INS) relies heavily on the visibility of GPS satellites. Especially, its accuracy is dramatically degraded in urban canyon due to signal obstructions due to large structures. In this paper, we propose a new integrated positioning system that effectively combines INS, GPS, ultrasonic sensor, and barometer in GPS-denied environments. In the proposed system, the ultrasonic sensor provides velocity information along the forward direction of moving vehicle. The barometer output provides height information compensated for the pressure variation due to fast vehicle movements. To evaluate the performance of the proposed system, an experiment was carried out by mounting the proposed system on a test car. By the experiment result, it was confirmed that the proposed system bears good potential to maintain positioning accuracy in harsh urban environments.

• 항공우주
• /
• 통권104호
• /
• pp.58-59
• /
• 2009

• 시스템엔지니어링학술지
• /
• 제2권1호
• /
• pp.31-36
• /
• 2006

Development of launch vehicle needs a large-scale and complicated System Engineering discipline interfacing to small-quantity production with special manufacturing processes. In general, the System Engineering discipline of launch vehicle has its relationship with Production, Operations, Product Assurance and Management disciplines and its internal partitions into the functions of System Engineering Integration & Control, Requirements Engineering, Analysis, Design and Configuration and Verification. As a function of Product Assurance, reliability of launch vehicle plays an significant role in risk management, system safety, flight safety and launch certification through design assurance. Moreover, major functions of systems engineering are integrated by means of reliability in the phases of design and verification. Therefore, derailed identification of system engineering interfaces of reliability, and execution of tasks for reliability assurance is required for successful development of launch vehicle. This paper identifies specific pattern and mechanism of the interfaces between reliability and system engineering.

• 한국자동차공학회논문집
• /
• 제24권5호
• /
• pp.495-503
• /
• 2016

Regulation for the testing and operation of autonomous vehicles on public roadways has been recently developed all over the world. For example, the licensing standards and the evaluation technology for autonomous vehicles have been proposed in California, Nevada and EU. But specific safety evaluation scenarios for autonomous vehicles have not been proposed yet. This paper presents safety evaluation scenarios for extraordinary service permission of autonomous vehicles on highways. A total of five scenarios are selected in consideration of safety priority and real traffic situation. These scenarios are developed based on existing ADAS evaluation and simulation of autonomous vehicle algorithm. Also, Safety evaluation factors are developed based on ISO requirements, other papers and the current traffic regulations. These scenarios are investigated via computer simulation.

• International Journal of Aeronautical and Space Sciences
• /
• 제14권3호
• /
• pp.247-255
• /
• 2013

The flight control of re-entry vehicles poses a challenge to conventional gain-scheduled flight controllers due to the widely spread aerodynamic coefficients. In addition, a wide range of uncertainties in disturbances must be accommodated by the control system. This paper presents the design of a roll channel controller for a non-axisymmetric reentry vehicle model using the trajectory linearization control (TLC) method. The dynamic equations of a moving mass system and roll control model are established using the Lagrange method. Nonlinear tracking and decoupling control by trajectory linearization can be viewed as the ideal gain-scheduling controller designed at every point along the flight trajectory. It provides robust stability and performance at all stages of the flight without adjusting controller gains. It is this "plug-and-play" feature that is highly preferred for developing, testing and routine operating of the re-entry vehicles. Although the controller is designed only for nominal aerodynamic coefficients, excellent performance is verified by simulation for wind disturbances and variations from -30% to +30% of the aerodynamic coefficients.

• 한국항공우주학회지
• /
• 제50권4호
• /
• pp.277-285
• /
• 2022

뉴스페이스 시대를 대표하는 소형위성 분야에서 발사기회에 대한 수요가 크게 증가하고 있다. 이를 위한 소형위성 전용 발사서비스를 합리적인 가격에 제공하는 것은 많은 스타트업 기업들이 추구하는 새로운 비즈니스 모델이 되고 있으며, 여기에는 저비용 부품과 대량생산, 최적화된 제작 공정이 결합된 비용 절감을 위한 혁신적인 솔루션들이 요구되고 있다. 이러한 흐름 속에서 우리나라에서도 한국항공우연구원에서 제3차 우주개발 진흥 기본계획에 따라 누리호를 통해 개발된 액체로켓엔진 기술을 기반으로 2단형 소형발사체 개발에 대비하여 핵심기술 및 비용절감 기술들을 개발하기 위한 선행기술 연구에 착수하였다. 본 논문에서는 소형위성을 위한 혁신적이며 가격 경쟁력을 가지는 것을 목표로 하는 2단형 소형발사체의 개념을 소개하고, 스테이징 설계 및 2단형 발사체의 전기체 구성안을 포함한 임무설계 결과를 기술하였다.

• International Journal of Naval Architecture and Ocean Engineering
• /
• 제4권3호
• /
• pp.183-198
• /
• 2012

Dynamic buckling, also known as parametric resonance, is one of the dynamic instability phenomena which may lead to catastrophic failure of structures. It occurs when compressive dynamic loading is applied to the structures. Therefore it is essential to establish a reliable procedure to test and evaluate the dynamic buckling behaviors of structures, especially when the structure is designed to be utilized in compressive dynamic loading environment, such as supercavitating underwater vehicle. In the line of thought, a dynamic buckling test system is designed in this work. Using the test system, dynamic buckling tests including beam, plate, and stiffened plate are carried out, and the dynamic buckling characteristics of considered structures are investigated experimentally as well as theoretically and numerically.

• International Journal of Aeronautical and Space Sciences
• /
• 제17권1호
• /
• pp.1-7
• /
• 2016

The influence of boundary condition of the bodies with gas flows is one of the most important problems in high-altitude aerodynamics. In this paper presents the results of the calculation of aerodynamic characteristics of aerospace vehicle using Monte-Carlo method based on three different gas-surface interaction models - Maxwell model, Cercignani-Lampis-Lord (CLL) model and Lennard-Jones (LJ) potential. These models are very sensitive for force and moment coefficients of aerospace vehicle in the hypersonic free molecular flow. The models, method and results can be used for new generation aerospace vehicle design.

• 한국신뢰성학회지:신뢰성응용연구
• /
• 제4권2호
• /
• pp.105-119
• /
• 2004

Reliability program is essential to the development of space systems like launch vehicles and satellites, as they are non-repairable after launch and the failure of a launch vehicle resulted in catastrophic consequences for the mission. Foreign advanced space organizations have developed and implemented their own reliability management programs for launch vehicles from the conceptual design stage to the detail processes for the individual components, procedures and test reports. A study on the launch failures and the reliability analysis methods for one-shot devices contained in this paper will contribute to the reliability improvement for Korean launch vehicle and components.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
• /
• 한국우주과학회 2004년도 한국우주과학회보 제13권2호
• /
• pp.247-250
• /
• 2004

Tracking systems for launch vehicle consist mainly of radar transponder (beacon), RF switch or power divider, antennas as onboard system, and single or multiple radars as ground one. In this paper, tracking systems, which are applicable to KSLV (Korea Space Launch Vehicle)-l, are introduced and the electrical performances for developed prototypes are presented. We have also performed RF link analysis for both uplink and downlink, and estimated that the maximum distance to be able to track KSLV-l stably is dependent on uplink characteristic in our system.