• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.10
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• pp.79-88
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• 2003

The paper presented here covers the work associated with the flight control law design, ground based and in flight simulation and handling qualities assessment of the Fly-by-Wire type Aircraft (FBWA). The FBWA configurations are of the same generic form of the Korean advanced trainer. The normal acceleration (Nz) and pitch rate (q) feedback control system is employed for longitudinal axis and roll rate (p) and lateral acceleration (Ny) feedback flight control law is developed in lateral/ directional axis. The flight tests for the FBW A dynamics evaluation were executed for the target aircraft (FBWA) on the IFS (In-Flight-Simulator) aircraft . The test results showed that Level 1 handling qualities for the most unstable flight regime and Level 1/2 for the landing approach flight regime were achieved. And the designed FBWA flight control law has revealed acceptable CHR (Cooper-Harper handling qualities Ratings).

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.11a
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• pp.9-9
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• 2000

우주추진기관의 모든 부품은 생산 시 규정된 절차를 거쳐서 작동의 이상유무를 확인하는 시험을 거친다. 우주추진기관은 특별한 경우를 제외하고는 실 비행 상태에서 시험하기가 어렵거나 불편하기 때문에 지상에서 시험을 수행하여 성능 및 안정성 등을 확인하게 된다. 지상연소시험을 수행하기 위해서는 비행용 엔진을 대상으로 엔진 메니폴드에 비행 시와 같은 조건의 추진제가 공급될 수 있게 해줘야 한다. 기존에 시험장이 이미 구축되어 있는 경우 엔진의 운용조건에 맞추어 엔진에 맞게 엔진과 시험설비 연결부분이 수정되게 된다.(중략)

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1054-1056
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• 2017

The Preparation for a flight test of the launch vehicle to verify the performance of the liquid rocket engine(LRE) is proceeding. Flight test of liquid rocket engine costs an enormous amount of money, has a restriction on measurement channels, so it requires the optimal measurement plan to check the prelaunch operation and determine the cause of abnormal situation. This paper surveys the foreign sources for LRE flight test. In recent years, as the tendency to eliminate all faults of LRE at the ground test the number of flight test is decreasing and in contrast, the number of measurements and measurement accuracy is increasing. This paper may be used as a reference for the preparation of an LRE flight test.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.153.1-153.1
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• 2012

조립 후 발사대로 이송된 추진기관(또는 발사체)는 지상시험 및 비행시험을 위한 충전을 하게 되는데, 추진제 및 고압가스 등 추진기관 구성품의 운용절차는 하드웨어의 설계 단계에서 그 개념이 수립되어야 한다. 다시 말해, 발사체 및 추진기관 설계 단계에서 연료와 산화제의 충전/배출, 시험 취소시의 운용절차 개념이 수립되어 있어야 추진기관 구성품들의 설계, 지상인터페이스 구성품의 설계에 그 내용이 반영될 수 있다. 따라서, 본 논문에서는 발사체 및 추진기관 운용와 관련된 일반적인 충전/배출 절차와 지연 또는 취소시의 작업절차의 주요개념을 다루었고, 추진기관 운용에 필요한 각종 지상설비에 요구되는 주요 기능을 검토하였다. 또한, 추진제 충전 이후 발사 대기시까지의 업무와 발사 전에 수행되어야 하는 추진기관 운용 업무(Pre-Launch Operation)도 다루었다. 특히 다단 발사체의 경우에는 운용과 관련된 준비 업무량이 단수에 비례하여 늘어나므로, 효율적으로 모든 시험 준비 업무를 마치기 위해, 지상에서의 추진기관 운용절차는 각 단별로 유기적으로 진행되어야 한다. 즉, 각 단별 하드웨어에 대한 사전 검사, 충전, 대기 등의 운용시간 설계 및 그 절차가 중요하다. 한국형 발사체 및 추진기관의 운용 개념설계를 수행하는데에는 기 확보된 운용기술을 활용하였다.

• Journal of Aerospace System Engineering
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• v.13 no.3
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• pp.40-47
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• 2019

This paper proposes the environment construction and test method of system integration laboratory (SIL) and system integration test (SIT) for verification of interface between onboard equipment and ground control equipment of unmanned aerial systems (UAS). This research also describes the interface environment between subsystems built in SIL and verification methods for the systems' operation logic through simulated flights. Similarly, the paper handles the ground integration test process of UAS in the real testing environments.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.5
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• pp.446-453
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• 2012

As part of the integration phases in developing a UAV, a System Integration Laboratory (SIL) has been developed to provide integrated test capability for the verification of avionics system requirements. The SIL has realized primary functions that are common in manned aircraft SIL's, and specialized laying stress on test data visualization and test automation under the closed-loop structure of the ground control simulation, aircraft simulation and flight simulation components. Those design results have led to easy and sure verification of lots of complex requirements of the UAV avionics system. The functions and performances of the SIL have been proved in four gradational test steps and checked to operate successfully in aircraft System Integration Test Environment for the integration of UAV ground station and aircraft.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.6
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• pp.540-547
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• 2015

This paper describes development contents and flight tests of an ACMI simulator based on LVC integrating architecture. ACMI is the system that provides air combat training and ground bombing training for improving fighting efficiency, that is the live simulation involving real people to operate real systems. ACMI simulator was developed for technic acquisition of LVC interoperability by using data link communication. ACMI simulator simulated maneuvering of a fighter by operating an UAV, a fighter can be distinguished from an UAV by maneuvering characteristics. This study proposes maneuvering simulation method by using flight data of the UAV, and performed its flight test for verifying similarity of fighter maneuvering.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.5
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• pp.490-498
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• 2010

This paper presents an autonomous target tracking approach and technique for transmitting ground control station image periodically for an unmanned aerial vehicle using onboard gimbaled(pan-tilt) camera system. The miniature rotary UAV which was used in this study has a small, high-performance camera, improved target acquisition technique, and autonomous target tracking algorithm. Also in order to stabilize real-time image sequences, image stabilization algorithm was adopted. Finally the target tracking performance was verified through a real flight test.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2008.10a
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• pp.183-188
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• 2008

Engine control/performance model for helicopter simulator is one of the most important models which affect flight performance and handling quality. It is typical to develop the model based on the raw data and models from the engine designers/manufacturers. The approaches in this study were to develop the basic model based on the available resources and to tune and verify it based on the ground/flight test results. The maintenance manuals of TB3-117 which is installed in KA-32T were reviewed and the components to be simulated for the engine control model were categorized and modeled. Piece-wise linear modeling method was used for the engine performance model. The engine performance data in the engine maintenance manuals were incorporated into the engine steady state performance tables, which were incorporated with the transfer functions for the dynamic performance. Engine control/performance model was compared and tuned with the ground/flight test results. It was verified that the fidelity of the model was within the tolerances in FAA AC120-63.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.12 no.12
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• pp.2239-2246
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• 2008

Engine control/performance model for helicopter simulator if one of the most important models which affect flight performance and handling quality. It is typical to develop the model based on the raw data and models from the engine designers/manufacturers. The approaches in this study were to develop the basic model bated on the available resources and to tune and verify it based on the ground/flight test results. The maintenance manuals of TB3-117 which is installed in KA-327 were reviewed and the components to be simulated for the engine control model were categorized and modeled. Piece-wise linear modeling method was used for the engine performance model. The engine performance data in the engine maintenance manuals were incorporated into the engine steady state performance tablet, which were incorporated with the transfer functions for the dynamic performance. Engine control/performance model was compared and tuned with the round/flight test results. It was verified that the fidelity of the model was within the tolerances in FAA AC120-63.