• Journal of Aerospace System Engineering
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• v.13 no.6
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• pp.36-42
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• 2019

This research illustrates how the simulation environment for operating the simultaneous man/unmanned aerial vehicle teaming is constructed. X-Plane program, HILS for the ducted fan aircraft (unmanned) and CTLS (manned aircraft) with communication devices are interfaced to simulate the basic co-operational flight. The X-plane and HILS can allow operators to experience the maned and unmanned aircraft operation in the airspace on the ground in turn they can perform various simulated missions in advance before the actual flight. For the test purpose, the data link between man/unmanned aircraft and ground control station is examined using C Band and UHF radio channels by the manned aircraft.

• Journal of Astronomy and Space Sciences
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• v.26 no.1
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• pp.99-110
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• 2009

The main purpose of the current research is to developments a real-time Hardware In-the-Loop (HIL) simulation testbed for the satellite formation flying navigation and orbit control. The HIL simulation testbed is integrated for demonstrations and evaluations of navigation and orbit control algorithms. The HIL simulation testbed is composed of Environment computer, GPS simulator, Flight computer and Visualization computer system. GPS measurements are generated by a SPIRENT GSS6560 multi-channel RF simulator to produce pseudorange, carrier phase measurements. The measurement date are transferred to Satrec Intiative space borne GPS receiver and exchanged by the flight computer system and subsequently processed in a navigation filter to generate relative or absolute state estimates. These results are fed into control algorithm to generate orbit controls required to maintain the formation. These maneuvers are informed to environment computer system to build a close simulation loop. In this paper, the overall design of the HIL simulation testbed for the satellite formation flying navigation and control is presented. Each component of the testbed is then described. Finally, a LEO formation navigation and control simulation is demonstrated by using virtual scenario.

• Journal of the Korea Society for Simulation
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• v.15 no.1
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• pp.43-50
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• 2006

The major objective of this paper is to propose a hybrid simulation environment for autonomous UAV system by integrating the continuous-time model with discrete-event model. Proposed system is able to support high autonomous behavior by combining the planner, recognizer, and controller model to deal with the HL20 AIRPLANE model. Thus, the high level decision may be efficiently issued even upon the unexpected circumstance. The proposed system model has been successfully verified by several simulation test performed on the DEVS simulation S/W environment.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.8
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• pp.807-815
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• 2008

In this paper, design, development and evaluation of DIP(Database Interface Program) are presented. The main purpose of this study is to improve the simulation quality to get more realistic response of target system. The designed and developed major function is composed of flexible memory structure, efficient arithmetic database language and high speed interpolation/extrapolation algorithm. To evaluate the operation speed and accuracy of returned data, trim simulation is performed based on in-house software and, DIP is applied to existing real-time simulator such as engineering HQS(Handling Quality Simulator) to evaluate reliability and performance. The result of evlaution reveals that calculation speed and data accuracy are satisfied, and flight performance is satisfied in the real-time simulator environments.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.11
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• pp.903-910
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• 2020

This paper introduces a simulator to assess the impacts of the wind and the airframe vibration on the performance of the Active Electronically Scanned Array (AESA) radar mounted in an aircraft. The AESA radar is mounted on the nose cone of an aircraft, and vibration occurs due to the drag force. This vibration affects the behavior of the AESA radar and can cause phase errors in signal. The simulator adopts the geometric model for nose cone, the mathematical models on the rigid-body dynamics of the aircraft, the average/turbulent winds, and the mode/ambient vibrations to compute the position and the attitude of the radar accurately. Numerical studies reflecting a set of test scenarios were conducted to demonstrate the effectiveness of the developed simulator.

• Journal of Advanced Navigation Technology
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• v.22 no.2
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• pp.133-140
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• 2018

In recent years, model-based design techniques have been used as a way to support cost reduction and safety certification in the development of avionics systems. In order to support performance analysis and safety analysis of aircraft and avionics equipment (item) using model based design, we developed a multi-domain simulation environment that inter-works with heterogeneous simulators. We present a multi-domain simulation environment that can verify air data computers and integrated multi-function probes at the aircraft level. The model was developed by Simulink and the flight simulator X-Plane 10 was used to verify the model at the aircraft level. Avionics model functions were tested at the aircraft level and the air data errors of the model and flight simulator were measured within 0.1%.

• Journal of Aerospace System Engineering
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• v.17 no.1
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• pp.59-67
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• 2023

Recently, interest in flight simulators based on HMD and mixed reality is increasing. However, they have limitations in providing various interactions and a sense of presence to pilot wearing HMD. To overcome these limitations, a mixed reality image corresponding to the interaction under the actual cockpit environment must be generated in real time and provided to the pilot. For this purpose, we proposed a mixed reality image generation method, in which the cockpit area including the pilot's body could be extracted from real image obtained from the camera attached to the HMD and then composed with virtual image to generate a high-resolution mixed reality image. Simulation results showed that the proposed method could provide mixed reality images to HMD at 30 Hz frame rate with 99% image composition accuracy.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.4
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• pp.95-100
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• 2004

This paper represents the development of a CLS(Control Loading System) for a target a airplane (KT-1) with mechanical linkage reversible flight control system. The system is composed of mechanical frame, controller, sensing part to measure the force from the stick, driving system generating the reaction forces. The DS1103 DSP(Digital Signal Processor) of the dSpace Corp. was used as the controller. The control algorithm of the CLS and the operational environment including monitoring software and evaluation tools are described. The evaluation of the system was conducted according to the requirement specification. The results of the test were analyzed by comparing with the actual data of the target airplane.

• 한국항공운항학회:학술대회논문집
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• 2015.11a
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• pp.183-185
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• 2015

A-SMGCS는 외부로부터 비행계획정보, 레이더 정보 및 기상정보를 수신하여 경로, 안내, 감시 및 항공등화 제어 기능을 수행하는데, 이러한 기능을 검정하기 위한 시뮬레이터는 기초자료 준비, 기상 시나리오 생성, 이벤트 시나리오 생성 및 항적자료 생성 등의 4가지 기능으로 구성되어 가상의 정보를 자동으로 생성하게 된다. 생성된 정보는 A-SMGCS에서 수신하여 그 정보를 바탕으로 각각의 기능들을 실행하게 되고, 그 실행 상태는 A-SMGCS HMI에 모니터링 된다. 그러므로 시뮬레이터에서 생성되는 가상의 시나리오들은 실제 공항에서 발생하거나 예측되는 모든 경우의 상황을 A-SMGCS에 제공하여 정확한 검정을 할 수 있도록 지원함으로써 A-SMGCS의 성능을 한층 더 향상시킬 수 있을 것이다. 따라서 본 논문에서는 이러한 효과가 기대되는 시뮬레이터의 기능과 연동관계를 정리하여 최적의 시뮬레이터를 제작할 수 있는 방법에 대한 연구를 실시하였다.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.105-105
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• 2003

인공위성의 개발과정에서 비행모델을 만들기 전 EM (Engineering Model) 들로 구성하는 Electrical Test Bed (ETB) 를 개발하여 위성의 하니스를 포함함 각 서브시스템 전장품들의 성능을 점검하게 되고, ETB 시험기간 동안 발생된 문제점 들은 비행모델 설계와 제작에 반영하게 된다. 다목적실용위성 2호에 대한 ETB를 개발하여 각종 위성 전장품에 대한 성능과 부분품들간의 인터페이스 신호들의 점검을 성공적으로 완료하였으며, 시험기간 동안 발생된 각종 문제점들은 비행모델 설계와 제작에 이미 반영하였다. 본 논문에서는 다목적실용위성 2호 비행모델에 대한 시험을 위하여 각 서브시스템 즉, 원격측 정명령계, 전력계, 자세제어계의 전장품과 탑재소프트웨어 그리고 각종 시뮬레이터들의 구성과 전기/전자적인 기능시험을 위한 시험항목 및 방법에 대해 고찰하고자 한다.