• 한국항공우주학회지
• /
• 제38권8호
• /
• pp.813-822
• /
• 2010

안전성 요구수준이 서로 다른 비행필수 데이터(Flight Critical Data)와 임무필수 데이터(Mission Critical Data)의 시현을 처리하기 위해 별도의 독립된 계기를 사용하지 않고 Glass Cockpit 설계를 적용하여 데이터를 통합처리하였다. 본 논문에서는 독립적으로 설계 진행되어온 비행조종계통과 임무탑재시스템의 통합설계를 위해 설계변경을 최소화하면서 비행조종계통에서 요구되는 비행필수 데이터처리의 안전성 요구수준을 만족시키는 최적화 설계를 제안하였다. 비행필수 데이터의 시현을 처리하기 위해 KUH 임무탑재시스템의 핵심구성품인 임무컴퓨터(Mission Computer)의 하드웨어 및 소프트웨어 설계변경을 최소화하였다. 임무탑재시스템의 안전성 요구도(Safety Requirement)를 검증하기 위한 시험절차를 개발하여 임무탑재시스템 통합시험장비(SIL)를 이용한 시험 수행 결과 안전성 요구도가 만족됨을 확인하였다.

• 한국군사과학기술학회지
• /
• 제14권2호
• /
• pp.213-221
• /
• 2011

Avionics system tends to be designed to have the integrated architecture, and it is getting difficult and complex to verify the flight-critical function because of sophisticated structure. In Korean Utility Helicopter, mission computer acts as the MUX Bus Controller to handle the data from both communication, identification, mission/display and survivability equipment inside Mission Equipment Package and aircraft subsystems such as fuel system and electrical system while it is interfacing with Automatic Flight Control System and Full-Authority Digital Engine Control via ARINC-429 bus. The Flight Displays which is classified as flight-critical function in aircraft is implemented on Primary Flight Display after mission computer processes data from AFCS in order to generate graphics. This paper defines the flight-critical function implemented in mission computer for KUH, and presents the static and dynamic test procedures which is performed on System Integration Laboratory along with Playback Recorder prior to flight test.

• 대한임베디드공학회논문지
• /
• 제7권3호
• /
• pp.157-162
• /
• 2012

In this paper, we propose a flight data storing system for effective data processing. Since the flight data contains critical information and their sizes are vast, encryption and compression would be needed to manage the flight data in effect. And we implemented the flight data storing system using an embedded board with DSP based on DPCM compression and AES encryption. Especially, we applied the reordering technique to advance the security function. From the simulations for two type data of voice and avionics, we found the developed system is well performed.

• Advances in aircraft and spacecraft science
• /
• 제11권1호
• /
• pp.33-53
• /
• 2024

This paper presents a comprehensive investigation into the optimization of Flight Management Systems (FMS) with a particular emphasis on data processing efficiency by conducting a comparative study with conventional methods to edge-computing technology. The objective of this research is twofold. Firstly, it evaluates the performance of FMS navigation systems using conventional and edge computing methodologies. Secondly, it aims to extend the boundaries of knowledge in edge-computing technology by conducting a rigorous analysis of terrain data and its implications on flight path optimization along with communication with ground stations. The study employs a combination of simulation-based experimentation and algorithmic computations. Through strategic intervals along the flight path, critical parameters such as distance, altitude profiles, and flight path angles are dynamically assessed. Additionally, edge computing techniques enhance data processing speeds, ensuring adaptability to various scenarios. This paper challenges existing paradigms in flight management and opens avenues for further research in integrating edge computing within aviation technology. The findings presented herein carry significant implications for the aviation industry, ranging from improved operational efficiency to heightened safety measures.

• Journal of Biosystems Engineering
• /
• 제36권6호
• /
• pp.476-483
• /
• 2011

The aerial application using an unmanned helicopter has been already utilized and an attitude controller would be developed to enhance the operational convenience and safety of the operator. For a preliminary study of designing flight controller, a state space model for an RC helicopter would be identified. Frequency sweep flight tests were performed and time history data were acquired in the previous study. In this study, frequency response of the flight test data of a small unmanned helicopter was analyzed by using the CIFER software. The time history flight data consisted of three replications each for collective pitch, aileron, elevator and rudder sweep inputs. A total of 36 frequency responses were obtained for the four control stick inputs and nine outputs including linear velocities and accelerations and angular velocities in 3-axis. The results showed coherence values higher than 0.6 for every primary control inputs and corresponding on-axis outputs for the frequency range from 0.07 to 4 Hz. Also the analysis of conditioned frequency response showed its effectiveness in evaluating cross coupling effects. Based on the results, the dynamic characteristics of the model helicopter can further be analyzed in terms of transfer functions and the undamped natural frequency and damping ratio of each critical mode.

• 한국추진공학회:학술대회논문집
• /
• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
• /
• pp.14-20
• /
• 2017

본 논문은 한국형발사체(KSLV-II) 발사대시스템 상세설계 단계 중 수행된 산화제 충전 운용 설계를 검증하고자, 나로호 1차 비행 시험 실증 자료과 해당 설계 모델링 유동 해석 결과를 비교하였다. 나로호 비행 시험에 적용되었던 공급 조건과 충전모드에 따른 유량조절밸브 개도와 구동 절차 조건을 한국형발사체 발사대시스템 상세설계 모델링에 적용하여, 실증 자료와 모델링의 산화제 공급 유량값과 주요 압력값을 비교하였다.

• 한국항공우주학회지
• /
• 제41권8호
• /
• pp.657-664
• /
• 2013

상용 프로그램 MSC/NASTRAN의 FlightLoad를 사용하여 고세장비 유연날개 항공기의 하중해석을 수행하였다. 풍동시험 결과를 이용하여 공력모델을 보정하고, 항공기의 모든 기동조건을 묘사하기 위한 트림조건을 정립하였다. 또한 항공기 중량 모델링, 설계 임계조건 판단 및 해석용 하중카드 생성 등 모든 업무를 자동으로 생성할 수 있는 프로그램을 개발하였다. 이러한 기법과 프로그램을 이용하여 효율적인 항공기 개발을 위한 비행하중해석 절차를 수립하였다.

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

• International Journal of Aeronautical and Space Sciences
• /
• 제1권2호
• /
• pp.30-42
• /
• 2000

On-orbit thermal environment test of KOMPSAT was performed in early 1999. An analysis of the test data are addressed in this paper. For the thermal-environmental simulation of spacecraft bus, an artificial heating through the radiator zones and onto some critical heat-dissipating electronic boxes was made by Absorbed-heat Flux Method. Test data obtained in terms of temperature history were reduced into flight heater duty cycles and converted into the total electrical power required for spacecraft thermal control. Verification result of flight heaters dedicated to the bus thermal control is presented. Additionally, an exhaustive heating-control process for maintaining the spacecraft thermally safe and for realistic simulation of the orbital-thermal environment during the test are graphically shown. Qualitative suggestions to post-test model correlation are given in consequency of the analysis.

• 한국항공운항학회지
• /
• 제19권1호
• /
• pp.29-37
• /
• 2011

Last April, Europe was severly damaged as all social and economic activities came to a halt prompted by the cancellation of all flights resulting from volcanic ash. This exemplifies that the meteorology conditions have significant influence on the flights of airplanes. Hence, in this research the influence that the meteorology has on the domestic flights and its characteristics will be examined, and the core meteorological factors that influence flights in each airport will be drawn. In order to do this, statistical analysis on the influence that the meteorology has on flights was carried out in order to analyze the data about flight cancelation and delay and also its cause, primarily based on the Gimpo, Gimhae, and the Jeju airports. As a result, first, the meteorological factors which impact flight cancellation and delay were different among the domestic airports, and second, it was analyzed that fog was the main meteorological factor in the Gimpo airport, strong wind in the Jeju airport, and fog in the Gimhae airport. Third, between the day the flights were cancelled and delayed occurred, and the day that weren't, the fact that there existed a difference among the actual meteorological factors was statistically drawn. With the result of such analysis, meteorological factors pertaining to the cancellation and delay of flights must be considered seperately by each airport and specialized meteorological information must be provided accordingly. Further, when selecting the position of an airport that is to be constructed in the future, implications that there is a definite need for the meteorology effect evaluation based on past meteorology data can be drawn.