• Proceedings of the KIEE Conference
• /
• 1999.07b
• /
• pp.566-568
• /
• 1999

HILS is widely used in the test and evaluation of complex control system. This paper describes the structure of HILS and the control loop performance monitoring of HILS system Distal path delay and FMS(Flight Motion Simulator) dynamics were estimated and output of the estimated model were compared with real FMS output. The monitoring system can be used for analyzing the result of HILS.

• Proceedings of the KIEE Conference
• /
• 2004.07d
• /
• pp.2164-2166
• /
• 2004

QFT는 플랜트의 변동을 고려하여 주파수 영역에서 설계하는 제어기법으로 파라미터의 변화 및 외란에 강인한 제어기 설계에 적합한 제어기 설계 방법이다. 본 논문에서는 종축 방향의 항공기 무게 중심이 변화하는 범위에 대하여 요구 비행성(Flying Quality)을 만족하도록 하는 강인한 QFT 제어기의 설계기법을 제안하였다. 시뮬레이션을 통하여 제안한 QFT 제어기가 무게중심의 변화 범위에서 주어진 비행성능을 만족함을 확인하였다.

• Proceedings of the Korean Society of Marine Engineers Conference
• /
• 2006.06a
• /
• pp.59-60
• /
• 2006

Some useful flow regime data are obtained from the experiments using the flight producing hyper-gravity(2g) conditions and on ground(1g) with the identical flow conditions. The flow regime data obtained at 1g and 2g conditions are compared with new dimensionless flow regime map using Fr, Bo and We number related with gravity, surface tension and inertia force.

• Proceedings of the KIEE Conference
• /
• 2002.07d
• /
• pp.2659-2661
• /
• 2002

The development of guided missile requires complex guidance schemes and hardware units because of high maneuver, delicate and variable missions. In this point of view, simulation systems and facilities which test missile hardwares and softwares are needed. This paper introduces the hardware-in-the loop simulation system and facilities which include the real-time computation systems and 3 Axis FMS(Flight Motion Simulator).

• Proceedings of the IEEK Conference
• /
• 2001.06e
• /
• pp.39-42
• /
• 2001

This paper proposes the design technique of memory sparing to overcome memory hard error Memory Sparing is used to increase the reliability and availability of commercial, military and space computer such as a Data Server, Communication Server, Flight Computer in airplane and On-Board Computer in spacecraft. But the documents about this technique are rare and hard to find. This paper has some useful information about memory error correction and memory error management.

• Proceedings of the Korean Information Science Society Conference
• /
• 2003.10b
• /
• pp.346-348
• /
• 2003

본 논문에서는 2004년 12월 발사 예정인 다목적실용위성 2호의 탑재소프트웨어의 구성과 전반적인 개발 과정 및 개발 환경에 관련된 내용을 서술한다. 다목적실용위성 2호 탑재소프트웨어 개발은 다목적실용 위성 1호 탑재소프트웨어를 근간으로 2호기 요구사양에 따라 요구사양 분석, 설계. 코딩 및 단위 테스트, 통합 테스트와 검증 시험 등을 거쳐 진행되었으며 일련의 모든 개발과정은 국내 연구진에 의해 수행되었다.

• Proceedings of the Korean Information Science Society Conference
• /
• 2003.10b
• /
• pp.367-369
• /
• 2003

인공위성 탑재 소프트웨어는 정해진 시간 내에 필요한 작업을 수행하여야 하는 실시간 내장형 소프트웨어로 타이밍 분석이 중요하다. 기존의 인공위성소프트웨어 개발 시 적용되는 타이밍 분석기법은 개발자의 수작업에 의존하여 많은 시간과 노력이 요구되며 정확성에 문제가 있을 수 있는 단점이 있었다. 본 논문에서는 위성소프트에어의 타이밍 분석에 적용 가능한 최장 실행시간 (Worst Case Execution Time, WCET) 기법을 조사하고 보다 정확한 (tight) WCET를 구하기 위해 입력 데이터를 고려한 WCET 분석 방안을 제안한다.

• Journal of Mechanical Science and Technology
• /
• v.20 no.1
• /
• pp.85-93
• /
• 2006

The trend of miniaturization has been applied to the research of rockets to develop prototypes of micro rockets. In this paper, the development of a web-integrated prototyping system for three-dimensional micro rockets, and the results of combustion tests are discussed. The body of rocket was made of 6061 aluminum cylinder by lathe process. The three-dimensional micro nozzles were fabricated on the same aluminum by using micro endmills with ${\phi}100{\mu}m{sim}{\phi}500{\mu}m$ diameter. Two types of micro nozzle were fabricated and compared for performance. The total mass of the rockets was 7.32 g and that of propellant (gun powder) was 0.65 g. The thrust-to-weight ratio was between 1.58 and 1.74, and the flight test with 45 degree launch angle from the ground resulted in $46\;m{\sim}53\;m$ of horizontal flight distance. In addition, ABS housing for the micro machined rocket was fabricated using Fused Deposition Modeling (FDM). A web-based design, fabrication, and test system for micro nozzles was proposed to integrate the distributed hardware resources. Test data was sent to the designer via the same web server for the faster feedback to the rocket designer.

• Proceedings of the KSME Conference
• /
• 2004.11a
• /
• pp.1586-1591
• /
• 2004

Flow visualization experiments have been performed to investigate the effects of phase lag, reduced frequency qualitatively by examining wake pattern on a dragonfly type wing. The model was built with a scaled-up, flapping wings, composed of paired wings with fore- and hindwing in tandem, that mimicked the wing form of a dragonfly. The present study was conducted by using the smoke-wire technique, and an electronic device was mounted to find the exact positional angle of wing below the tandem wings, which amplitude is ranged from $-16.5^{\circ}$ to $+22.8^{\circ}$. Phase lag applied on the wings is $0^{\circ}$, $90^{\circ}$, $180^{\circ}$ and $270^{\circ}$. The reduced frequency is 0.15, 0.3 and 0.45 to investigate the effect of reduced frequency. It is inferred through observed wake pattern that the phase lag clearly plays an important role in the wake structures and in the flight efficiency as changing the interaction of wings. The reduced frequency also is closely related to wake pattern and determines flight efficiency.

• Proceedings of the KSME Conference
• /
• 2004.11a
• /
• pp.625-630
• /
• 2004

An advanced method of Relaxed Static Stability (RSS) is utilized for improving the aerodynamic performance of modern version supersonic jet fighter aircraft. The laws of flight control system utilize RSS criteria in both longitudinal and lateral-directional axes to achieve performance enhancements. Particularly, the design of longitudinal control laws for utilizing RSS methods greatly affects the performance of the aircraft in Air-to-Air Tracking and Air-to-Ground modes, which improves weapon delivery. In the area of Airto- Air Tracking, the development of longitudinal control laws aids in the fine tracking and gross acquisition of other aircraft. This paper proposes that Air-to-Air fine tracking can be improved via RSS control law design methods without effecting Air-to-Air gross acquisition.