• 한국항공운항학회지
• /
• 제18권4호
• /
• pp.38-43
• /
• 2010

A continuing challenge in the aviation industry is how to safely keep aircraft in service longer with limited maintenance budgets. Therefore, all the advanced countries in aircraft technologies put great efforts in prediction of failure rate in parts and system, but in the domestic aircraft industry is lack of theoretical and experimental research. Prediction of failure rate provides a rational basis for design decisions such as the choice of part quality levels and derating factors to be applied. For these reasons, analytic prediction of failure rate is essential process in developing aircraft structure. In this paper, a procedure for prediction of failure rate for aircraft structural parts is presented. Cargo door kinematic parts are taken to illustrate the process, in which the failure rate for Hook part is computed by using Monte Carlo Simulation along with Response Surface Model, and system failure rate is obtained afterwards.

• International Journal of Aeronautical and Space Sciences
• /
• 제16권3호
• /
• pp.425-436
• /
• 2015

This paper presents the procedures used for estimating the stability and control derivatives of a general aviation canard aircraft from flight data. The maximum likelihood estimation method which accounts for both process and measurement noise was used for the flight data analysis of a four seat canard aircraft, the Firefly. Without relying on the parameter estimation method, several aerodynamic derivatives were obtained by analyzing the steady state flight data. A wind tunnel test, a flight test of a 1/4 scaled remotely controlled model aircraft, and the prediction of aerodynamic coefficients using the USAF Stability and Control Digital Data Compendium (DATCOM), Advanced Aircraft Analysis (AAA), and Computer Fluid Dynamics (CFD) were performed during the development phase of the Firefly and the results were compared with flight determined derivatives of a full scaled flight prototype. A correlation between the results from each method could be used for the design of the canard aircraft as well as for building the aerodynamic database.

• 한국항공운항학회지
• /
• 제21권4호
• /
• pp.11-16
• /
• 2013

Airworthiness certification is a repeatable process implemented to verify that a specific aircraft can be safely maintained and operated within its approved flight envelope. Airworthiness certification activity for the FA-50 aircraft has been performed according to the Airworthiness Certification Criteria, issued in 2011 by DAPA. It is a right time to study the application of those existing ACC process and tools to the hypothetical modification aircraft. This paper describes airworthiness engineers view of the integrated activities required to substantiate the modified aircraft performance. The compliance methods applicable to the airworthiness certification criteria is also suggested. It will be useful for the establishment of the future Korea modified military aircraft's ACC with the risk assessment and methods of compliances tailored to the legacy aircraft.

• 항공우주시스템공학회지
• /
• 제7권3호
• /
• pp.15-19
• /
• 2013

Tail wing is important to designing of civil aircrafts, because it is responsible for aircraft stability and control. Tail wing has a role in aircraft control and makes aircraft fly stably without any pilot control input. Also, designing of tail wing determine trim drag force in whole aircraft. Center of gravity(CG) of aircraft travels with various effects as placement of passenger's seats, location of cargo bay, etc. In designing horizontal tail volume, aircraft CG travel has to be considered to have margin so that it should be sized to provide adequate stability and control for the airplane's entire CG range throughout the flight envelope. Finally, it is essential to have sufficient elevator control to perform stall at forward CG for all flaps down configurations. Such stalls establish the FAR stall speed which airplane take-off and landing performance. This paper deals with the process for tail wing design regarding the aircraft CG travel and results for 95-seat type turboprop aircraft.

• 한국항공우주학회지
• /
• 제36권2호
• /
• pp.105-114
• /
• 2008

본 연구에서는 고정익과 회전익의 두 가지 모드로 운용되는 canard rotor wing(CRW) 항공기에 대한 사이징과 성능해석 프로그램이 개발되었다. 개발된 프로그램은 기존의 항공기 데이터를 이용하여 각 모드에 대한 검증을 수행하였고 정찰 임무형상에 대해 최적설계 문제를 정의하였다. canard rotor wing의 로터 최적화를 위해 고정익 모드와 회전익 모드에 대해 가중치를 이용한 다중목적함수를 구성하였다. 6개의 서로 다른 가중치와 설계제약조건에 대해 최적설계가 수행되었고 그 결과 개선된 로터형상을 도출하였다.

• 한국항공운항학회지
• /
• 제21권1호
• /
• pp.62-67
• /
• 2013

Human Powered Aircraft (HPA) should be light in weight and have high efficiency because power source of propulsion is human muscles. Airframe structure takes up most of empty weight of aircraft, so weight reduction of structure is very important issue for HPA. In this paper, design/analysis/test procedures for ultra light weight structure of the HPA developed by Korea Aerospace Research Institute (KARI) are explained briefly. Structural design is conducted through case studies on HPA in the USA and Japan. Loads analysis is performed to calculate design loads which is needed for structural design and analysis. Structural analysis is conducted for structure sizing. Static strength test of main wing spar which is primary structure of wing is performed to verify structural integrity.

• Journal of Information Technology Applications and Management
• /
• 제30권6호
• /
• pp.81-90
• /
• 2023

In aviation, with the rapid transformation of the mobility industry, UAMs are emerging to operate green low-altitude airspace in urban environments. In order for UAM aircraft to fly safely transporting passengers and cargo in low-altitude urban airspace, a traffic control system that supports the safe operation of the aircraft is essential. In particular, traffic control systems that reflect the characteristics of the flight environment, such as operating at low altitude in urban environments for a short period of time, are required. In this study, we define the definition of UATM and its main services that perform traffic control for the safe operation of UAMs. In addition, we analyzed the development trends of UATM systems based on domestic and overseas cases. Based on these analyses, we present the results of the concept design of the UATM system. After analyzing UATM development cases, we found that there is no commercialized UATM system, but overseas development is focused on systems that can integrate ATM and UTM. And we identified key stakeholders and interface data, and performed UATM system architecture and functional design based on the identified data. Finally, as a necessary element for the future development of UATM systems, we propose the establishment and advancement of UAM traffic flow management systems, the establishment of integrated control systems, and the development of interface with aircraft operation systems in preparation for the unmanned UAM aircraft.

• International Journal of Aeronautical and Space Sciences
• /
• 제13권4호
• /
• pp.435-445
• /
• 2012

In this paper, a design process is established by integrating aviation safety requirements for the development of general aviation aircraft. An Airworthiness-Design Integration System, which integrates certification requirements with the entire design/analysis process, is developed and presented. For the proposed system, KAS 23/FAR 23/AC 23/CS 23 certification regulations are analyzed to determine design constraints and system compliance checks and to construct an ER&G (Engineering Requirement and Guide) and a Design-Certification Related Table (DCRT). Furthermore, through building a DB (Data Base), the management of design and certification related resources for developing a FAR 23 class aircraft are made. Certification tools and resources are also efficiently managed by the DB. The connection between the certification requirements and the detailed design process is proposed in this system. Tracking of this proposed method is validated by configuring a USE CASE and a system. The Airworthiness-Design Integration system will be constructed based on the system's design plan, certification system, and usage scenarios.

• Nuclear Engineering and Technology
• /
• 제49권2호
• /
• pp.404-410
• /
• 2017

In order to help decision-makers in the early design phase to improve and make more cost-efficient system safety and reliability baselines of aircraft design concepts, a method (Multi-objective Optimization for Safety and Reliability Trade-off) that is able to handle trade-offs such as system safety, system reliability, and other characteristics, for instance weight and cost, is used. Multi-objective Optimization for Safety and Reliability Trade-off has been developed and implemented at SAAB Aeronautics. The aim of this paper is to demonstrate how the implemented method might work to aid the selection of optimal design alternatives. The method is a three-step method: step 1 involves the modelling of each considered target, step 2 is optimization, and step 3 is the visualization and selection of results (results processing). The analysis is performed within Architecture Design and Preliminary Design steps, according to the company's Product Development Process. The lessons learned regarding the use of the implemented trade-off method in the three cases are presented. The results are a handful of solutions, a basis to aid in the selection of a design alternative. While the implementation of the trade-off method is performed for companies, there is nothing to prevent adapting this method, with minimal modifications, for use in other industrial applications.

• 한국항공운항학회지
• /
• 제25권4호
• /
• pp.83-90
• /
• 2017

Unmanned Aerial Vehicles(UAVs) require collision avoidance capabilities equivalent to the capabilities of manned aircraft to enter the airspace of manned aircraft. In the case of Visual Flight Rules of manned aircraft, collision avoidance is performed by 'See-and-Avoid' of pilots. To obtain those capabilities of UAVs named as 'Sense-and-Avoid', sensor-system-based intruder tracking and collision avoidance methods are required. In this study, a multi-sensor-based tracking, data fusion, and collision avoidance algorithm is designed by using a model-based design tool MATLAB/SIMULINK, and validations of the designed model and code using numerical simulations and processor-in-the-loop simulations are performed.