• Proceedings of the Korea Information Processing Society Conference
• /
• 2019.05a
• /
• pp.342-345
• /
• 2019

드론의 동작 검증을 위한 테스트는 최종적으로 드론이 운용될 환경에서 이루어진다. 그러나 테스트 비용이 크고 테스트 비행 중 파손의 위험이 있기 때문에 시뮬레이션을 통한 사전 검증을 수행하는 것이 중요하다. 시뮬레이션은 SIL 방식이나 HIL 방식으로 이루어지는데 추가적인 외부 센서를 활용하는 경우 검증하기가 어렵다. SIL에서는 검증을 위해 가상의 외부 센서 구현이 필요하다. HIL 에서는 실제 센서를 사용하므로 가상의 외부 센서 구현은 필요 없다. 그러나 테스트 환경이기 때문에 실제 환경과 비슷한 데이터나 동작 검증에 적합한 데이터를 얻기 어렵다. 이러한 HIL에서의 문제를 해결하기 위해 외부 센서를 실제 환경에서 사용한 로그나 테스트 환경에서 센서 검증에 사용한 로그를 이용할 수 있다. 본 논문에서 제안하는 외부 센서의 로그를 활용한 HIL 시뮬레이션 기법 확장 내용은 외부 센서 데이터 입력기가 로그로부터 얻은 센서 데이터를 비행 컨트롤러로 보내 검증을 수행하기 때문에 데이터를 재사용할 수 있고 테스트 비용을 줄일 수 있다. 또 외부 센서 데이터 입력기는 로그 파서, 뷰어, 슬라이서, 데이터 전송기로 구성되어 로그로부터 검증에 적합한 데이터를 쉽게 얻어 활용할 수 있다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.37 no.1
• /
• pp.28-35
• /
• 2009

This paper derives the equation of coordinated attitude formulation taking into account the orbital dynamics of a target vehicle and the attitude of a tracking satellite in geostationary orbit. The coordinated attitude is always to communicate with the ground station during the target tracking. Because the tracking satellite could perform high angle maneuver, MRP parameters having no singular point are used. Also for the sequential tracking of several target vehicles, the equation automatically making a coordinated attitude is suggested. Coordinated attitude flying and sequential tracking are confirmed through simulations. In short, this paper shows that a satellite could track a target vehicle and communicate with ground station simultaneously using the derived equation of coordinated attitude even though without a accuracy sensor.

• Aerospace Engineering and Technology
• /
• v.12 no.2
• /
• pp.202-208
• /
• 2013

This paper describes establishment of a pilot training plan, training and an outcome for Human Powered Aircraft which can take off, landing and fly using the energy generated by only human muscle without using mechanical power. To achieve these, a special trainer made a plan by considering physical trait of each pilot and each pilot was performed an indoor training for principle physical improvement, an outdoor training for generating sustainable power, a simulation training to learn maneuver ability. The pilot mastered the basic maneuver ability needed to fly and each pilot was lose their weight and experienced their improved physical strength via the training.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.26 no.3
• /
• pp.1-9
• /
• 2022

The aircraft targeted in this study is a vertical take-off and landing aircraft with 4 to 5 passengers, and the propulsion system for the aircraft is a distributed hybrid propulsion system that uses a gas turbine engine and a battery pack as the main power source to supply the power required by multiple motors. In this study, a design/analysis platform for a hybrid propulsion system was developed using the MATLAB/Simulink program based on the preliminary design results. Through simulation analysis, the output characteristics and operating range of each power source according to the mission profile were confirmed, and through this, the feasibility of the preliminary design result was confirmed.

• Aerospace Engineering and Technology
• /
• v.3 no.2
• /
• pp.238-247
• /
• 2004

Realtime Simulation and HILS are essential tools for modern aircraft control system design and development. But developing the HILS has been a big and complex task to meet the realtime simulation requirement. So these days there have been efforts to minimize these task. New advanced concept and design tools are being developed. In this paper, these new advanced concept and design tools were used to develop the realtime simulation and HILS environment for rotorcraft. The H/W 문 S/W requirement and system configuration for the developing system will be described on the paper.

• Journal of the Korea Academia-Industrial cooperation Society
• /
• v.20 no.4
• /
• pp.479-488
• /
• 2019

The flight test operational procedure artifact includes mission planning, execution methods, and safety measures for each step of test progress. As the development of guided missiles has become more advanced and strategic, flight test has become increasingly complex and broadened. Therefore, increased reliability of the flight test operation procedures was required to ensure test safety. Particularly, the design of the flight test operational procedures required verification through M&S to predict and prepare for the uncertainty in a new test. The relevant studies have published the optimal framework development for flight tests and the model-based improvements of flight test processes, but they lacked the specificity to be applied directly to the flight test operational procedures. In addition, the flight test operational procedures, which consist of document bases, have caused problems such as limitations of analysis capabilities, insensitive expressions, and lack of scalability for the behavior and performance analysis of test resources. To improve these problems, this paper proposes how to design operational procedure of guided missile flight test system by applying MBSE(Model-based Systems Engineering). This research has improved reliability by increasing the ability to analyze the behavior and performance of test resources, and increased efficiency with the scalability applicable to multiple flight tests. That can be also used continuously for the guided missile flight tests that will be developed in the future.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.45 no.9
• /
• pp.711-723
• /
• 2017

This paper proposes a flight control system for an organic flight array(OFA) which has a new configuration to consist of multi modularized ducted-fan unmanned aerial vehicles (UAVs). The OFA is able to apply to various missions such as indoor reconnaissance, communication relay, and radar jamming by using capability of hover flight. The OFA has a distinguished advantage due to reconfigurable structure to assemble or separate with respect to its missions or operational conditions. A dynamic modelling of the OFA is derived based on equations of motion of the single ducted-fan modules. In order to apply nonlinear control method, an affine system of attitude dynamics is derived. Moreover, the control system is composed of a back-stepping controller for attitude control and a PID controller for position control. Then the performance of the proposed controller is verified via a numerical simulation under wind disturbance.

• Journal of Aerospace System Engineering
• /
• v.18 no.2
• /
• pp.40-46
• /
• 2024

This study suggests a method to enhance drone flight path planning and safety evaluation in urban areas using Computational Fluid Dynamics (CFD). As the use of drones in urban environments has been growing rapidly, there is a lack of established methods for path planning and safety evaluation, which leads to a risky approach relying on experimental methods. Therefore, this research takes into account the intricate 3D fluid dynamics between drones and buildings by employing CFD to quantitatively plan flight paths and evaluate their safety. To accomplish this, the study focuses on Gimcheon Innovation City as the target area and collects relevant terrain and building data, and selects prospective flight routes. CFD analysis is then carried out to gather essential data for flight simulations and safety assessment. The safety assessments are conducted based on environmental fluid dynamics when the drone operates along the proposed flight paths

• Proceedings of the KIEE Conference
• /
• 2005.07d
• /
• pp.2849-2851
• /
• 2005

본 논문에서는 소형 카오스 무인 비행체에서의 장애물 회피 기법과 목표물 탐지 기법을 제안하였다. 장애물은 불안정한 VDP(van der Pol) 방정식을 이용하였으며 목표물은 안정한 VDP 방정식을 이용하였다. UAV가 장애물과 목표물에 접근하게 되면 불안정 또는 안정한 VDP 방정식이 UAV를 밀어내거나 끌어들임으로서 장애물을 피해가거나 목표물 탐색할 수 있는 알고리즘을 제시하고 컴퓨터 시뮬레이션으로 그 결과를 검증하였다.

• Proceedings of the KIPE Conference
• /
• 2015.07a
• /
• pp.133-134
• /
• 2015

본 논문에서는 유도형 활공 탄약의 방향과 자세 제어를 위한 4축 조종 날개의 위치 제어용 Sensorless BLDC 전동기 구동 시스템을 개발하였다. HILS(Hardware in the loop system)를 이용하여 유도형 탄약의 발사 조건과 비행 환경을 시뮬레이션하면서 비행 시 발생하는 공력 부하를 기구부로 재현하였고 이러한 조건하에서 4축 조종 날개의 위치 제어 특성을 확인함으로써 개발된 구동 시스템의 성능을 검증하였다.