• 제어로봇시스템학회:학술대회논문집
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• 1992.10a
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• pp.135-140
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• 1992

This paper presents the configuration, HILS procedure and performance simulation results of the RPV autopilot including a strapdown AHRS. Real time hardware-in-the-loop simulation was performed by using a 3 axis flight motion simulator alonged assumed flight trajectory of the RPV. Being compared with the result of the 6 DOF simulation, the HILS results showed that the performance of the autopilot was satisfactory.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.28 no.4
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• pp.125-131
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• 2020

In order to study the correlation between the pilot's cognitive ability and recovery ability by applying a physical element that can cause spatial loss of position to the pilot, a turntable was installed on the top of the motion system to give a quantitative rotational error. We propose a method of simulating flight movement to reduce a difference in feeling and an intuitive method of forward kinematic analysis.

• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.170-178
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• 2004

This paper deals with six degree-of-freedom HILS(hardware-in-the-loop-simulation) of KSR-III rocket using a TAFMS(three axis flight motion simulator). This TAFMS HILS test is accomplished before main HILS tests in order to verify the control stability in the presence of TAFMS dynamic effects. The TAFMS HILS test includes initial attitude holding tests for INS initial alignment procedures, timer synchronization tests with an auxiliary lift-off signal, real-time calibration tests using an external thermal recorder, open-loop TAFMS operating tests, and final closed-loop TAFMS HILS tests using the TAFMS attitude measurements as inputs to the closed control loop. The HILS tests are accomplished for several flight conditions composed with nominal flight condition, TWD effect added condition, slosh modes and/or bending modes existing condition, and windy condition, etc.

• 제어로봇시스템학회:학술대회논문집
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• 1989.10a
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• pp.50-53
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• 1989

This paper presents the configuration and performance test results of a SDARS, which consists of three rate gyros and Zilog 8002 microprocessor. Real time hardware-inthe-loop simulation was performed by 3 axis flight motion simulator applying the assumed typical profiles of angular motion. Test results showed that the performance of SDARS was satisfactory. And, attitude errors was reduced by compensation of gyro errors.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.6
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• pp.438-445
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• 2019

In this paper, we present a new approach to extract the g-sensitivity scale-factor error for a MEMS gyroscope. MEMS gyroscopes, based on the use of both angular momentum and the Coriolis effect, have a g-sensitivity error due to mass unbalance. Generally, the g-sensitivity error is not considered in general use of gyroscopes, but it deserves our attention if we are to develop for tactical class performance and reliability. The g-sensitivity error during vehicle flight increases navigation error; so it must be analyzed and compensated for the use of MEMS IMU for high dynamics vehicle systems. Therefore, we analyzed how to extract the g-sensitivity scale-factor error from the inertial sensor error model. Furthermore we propose a new method to extract the g-sensitivity error using flight motion simulator. We verified our proposed method with experimental results.

• Proceedings of the KIEE Conference
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• 1999.07b
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• pp.566-568
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• 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 Korean Operations and Management Science Society Conference
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• 1994.04a
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• pp.587-595
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• 1994

The use of flight training simulators has been increased remarkably during the past 20 years stimulated by the benefit that simulators can contribute to safety and training efficiency. Simulators have incorporated higher and higher levels of reality to provide more realistic training. Now, however, users are beginning to question how such reality is enough. Especially, it has raised question about the need for a notion system in the aircraft simulator. To help answer this question, this report describes notion cue requirements and types of motion system, and finally presents the assessment of the effectiveness of three different notion system alternatives.

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

• Journal of Advanced Navigation Technology
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• v.28 no.1
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• pp.60-67
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• 2024

The majority of civil aviation accidents are caused by human factors, and especially for rotary-wing aircraft, accidents often occur in situations where pilots unexpectedly or unintentionally enter into instrument meteorological conditions (IIMC). This research analyzed the error rates of rotary-wing aircraft pilots under low visibility conditions from various angles to gain insights into flight characteristics and to explore measures to reduce accidents in IIMC situations. The occurrence rate of errors by pilots under low visibility conditions was examined using a flight simulator equipped with motion, with 65 pilots participating in the experiment. Flight data obtained through the experiment were used to aggregate and analyze the number of errors under various conditions, such as reductions in flight visibility, the presence or absence of spatial disorientation, and the pilot's qualifications. The analysis revealed peculiarities in flight characteristics under various conditions, and significant differences were found in the rate of error occurrence according to the pilot's qualification level, possession of instrument flight rules (IFR) qualifications, and during different phases of flight. The results of this research are expected to contribute significantly to the prevention of aircraft accidents in IIMC situations by improving pilot education and training programs.

• Proceedings of the Korean Society of Computer Information Conference
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• 2017.07a
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• pp.11-12
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• 2017

본 논문에서는 항공기 비행 자세를 직관적으로 이해하고 동작의 원리를 시각화 할 수 있는 비행 자세 시뮬레이터를 구현하였다. 항적 정보의 변화에 따라 6축 모션 플랫폼을 동작시키고, 자이로 센서로 부터 전달 받은 비행 자세를 시뮬레이터에 전달하여 시스템을 구성한다. 항공기의 자세를 분석하기 위하여 자이로 센서와 가속도 센서를 같이 사용하는데 자이로 센서는 적분과정의 누적오차가 발생하고 가속도 센서는 짧은 순간의 진동에 따른 노이즈가 심하여 상보 필터를 이용한 보정작업을 하였다. 산출된 센서 정보를 이용하여 6축 모터에 전달할 각도를 계산하여 모션 플랫폼을 동작시키게 되며 시각화 결과는 OpenGL을 이용하여 구현하였다. 본 연구의 결과는 향후, 항공관련 학생들의 교육 기자재로 활용될 수 있을 것으로 사료된다.