• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.3
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• pp.228-235
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• 2010

This paper deals with an autonomous flight controller design problem for a tilt-rotor aircraft in rotary-wing mode. The inner-loop algorithm is designed using the output-based approximate feedback linearization. The model error originated from the feedback linearization is cancelled within allowable tolerance by using single-hidden-layer neural network. According to Lyapunov direct stability theory, the adaptive update law is derived to run the neural network on-line, which is based on the linear observer dynamics. Moreover, the outer-loop algorithm is designed to track the trajectory generated from way-point guidance. Especially, heading and flight-path angle line-of-sight guidance are applied to the outer-loop to improve accuracy of the landing tracking performance. The 6-DOF nonlinear simulation shows that the overall performance of the flight control algorithm is satisfactory even though the collective input response shows instantaneous actuator saturation for a short time due to the lack of the neural network and the saturation protection logic in that loop.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.10
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• pp.842-850
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• 2014

This paper presents a trajectory tracking controller for rotorcraft UAVs to improve the tracking performances in the presence of various uncertainties. The proposed tracking method consists of a velocity guidance law based on the relative distance and L1 adaptive augmentation loop for tracking the velocity commands. In the proposed structure, the desired velocity generated by the guidance law is the reference value of the adaptive controller for accurate path tracking. In the guidance law, the desired acceleration is generated based on the relative distance and its derivatives, and then the velocity command of the inner control loop is calculated by integrating the accelerations. $L_1$ augmentation loop supplements the linear controller to guarantee the flight performances such as a tracking accuracy in the presence of the uncertainties. The proposed controller was validated in actual flight tests to successfully demonstrate its capability using a quadrotor UAV.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.10
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• pp.805-812
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• 2013

The operational flight program(OFP) which has the functions of I/O processing with avionics, flight control logic calculation, fault diagnosis and redundancy mode is embedded in the flight control computer of Smart UAV. The OFP was developed in the environment of PowerPC 755 processor and VxWorks 5.5 real-time operating system. The OFP consists of memory access module, device I/O signal processing module and flight control logic module, and each module was designed to hierarchical structure. Memory access and signal processing modules were verified from bench test, and flight control logic module was verified from hardware-in-the-loop simulation(HILS) test, ground integration test, tethered test and flight test. This paper describes development environment, software structure, verification and management method of the OFP.

• Journal of Korea Water Resources Association
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• v.41 no.8
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• pp.797-806
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• 2008

The geometric properties of the drainage structures are analyzed through depicting the drainage network which is composed of the whole drainage paths in the natural basin defined at the specific scale. The theoretical consideration is performed on the general structures of networks organized by ramification process based on Fractal tree and Horton's law. The drainage network is generated via ArcGIS, ordered by Strahler's ordering scheme and investigated with Strahler's order. As a results of the Richardson's method it is shown that there may exist the distinct behavioral characteristics between overland-flow and channel flow and the natural stream networks would be space-filling Fractals. As a result, it is shown that the values estimated by considering the overland-flow on being applied to the field data give the different results from the empirical method applied until now. As expected, therefore the results obtained from this study are sure to be devoted further researches on the channel networks.

• The Korean Journal of Financial Management
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• v.15 no.2
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• pp.279-337
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• 1998

이 논문에서는 주가가 확률과정, 즉 확률미분방정식에 의하여 생성되는가를 검정하고 주가의 운동법칙을 규명한다. 일별종합주가지수가 양수의 완전시계열상관을 갖고 있으며, 더욱이 3년 정도의 시차까지 의미있는 시계열상관을 갖고 있음이 발견되었다. 수익률과 가격변화의 시계열상관도 존재하고 시계열은 정상성(定常性)을 갖고 있다. 마팅게일에 의하여 주가가 생성되고있지 않음이 밝혀졌다. 한국증권거래소에서 계산하고 있는 일별 종합주가지수를 포함한 41개 산업별 지수를 사용하여 자본시장의 운동법칙을 규명하기 위하여 가장 많이 이용하고 있는 세개의 확률미분방정식을 검정하였다. 각 주가지수들이 온스타인 울렌벡 브라운 운동과정과 평균회귀과정을 따르지 않고 있다는 것이 발견되었다. 그러나 주가가 편류를 갖는 일반 기하 브라운 운동과정에 의하여 생성되고 있음이 검정을 통하여 확인되었다. 평균회귀과정에 의하여 주가가 생성되지 않는다는 발견은 의외라 할 수 있다. 주가가 온스타인 울렌벡 과정을 따르지 않는다는 것은 주가가 제 1계 정상적 자기회귀과정이 아니라는 것을 의미한다. 일별종합주가지수는 제 4계 자기회귀과정에 의하여 생성된다. 가격변화와 수익률의 생성함수는 제 4계 자기회귀과정이다. 종합주가지수의 제 1계 시계열상관계수는 1이다. 상당히 큰 시차를 갖을 때까지 시계열상관이 대략적으로 1을 유지하고 있다. 따라서 지수가 마팅게일을 따르고 있지 않다. 이 점은 가격변화와 수익률에 있어서도 유사하다. 가격변화, 수익률, 대수수익률의 제 1계 시계열상관이 0.1로 유의적이다. 따라서 수익도 마팅게일 과정을 따르고 있지 않다. 증권가격은 세 번에 걸쳐 구조의 번화가 발생하였다. 구조의 변화가 발생할 때마다 평균가격이 상승하였다. 이와 같은 현상은 장기적 기대가격이 미지일 가능성이 배제되지 않는다. 단기적 기대 주가가 알려진 반면 장기적 기대 주가가 미지라면 평균회귀과정은 장기적 기대주가로 회귀하고 있는 과정이므로 장기기대 주가의 미지성이 평균회귀 과정의 기각을 유도하게 된다. 우리나라의 투자자들은 무위험자산과 위험을 동시에 고려하여 투자활동을 전개하고 있음이 발견되었다. 선형의 효용함수를 갖는 위험중립적 태도의 투자자가 아니다. 위험기피형 효용함수 아래에서 투자활동을 수행하고 있는 합리적 투자자들이라 할 수 있다. 뿐 만 아니라 자신의 평생에 걸친 소비를 소비가 이루어지는 각 기마다 가급적 일정하게 하는 소비행동을 목표로 삼고 소비와 투자에 대한 의사결정을 내리고 있음이 실증분석을 통하여 밝혀졌다. 투자자들은 무위험 자산과 위험성 자산을 동시에 고려하여 포트폴리오를 구성하는 투자활동을 행동에 옮기고 있다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.9
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• pp.742-751
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• 2018

In this paper, we propose a time varying biased proportional navigation guidance law that controls the impact angle under Field-of-View(FOV) and the acceleration limit of the missile. The proposed law is composed of three stages in consideration of the FOV limitation. Since the bias directly affects the acceleration at each stage, the final bias value of the previous stage becomes the initial bias value of the next stage when the stage is switched. In addition, the impact angles were controlled by judging whether impact angles were reached in consideration of engagement conditions and physical constraints.

• Computational Structural Engineering
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• v.10 no.4
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• pp.229-238
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• 1997

Mechanical behavior of asphalt concrete that accounts for viscoelasticity and damage evolution under cyclic loading conditions is modeled and presented in this paper. An elastic-viscoelastic correspondence principle in terms of pseudo variables is applied to separately evaluate viscoelasticity and time-dependent damage growth in asphalt concrete. A microcrack growth law, which is commonly employed in linear viscoelastic fracture mechanics, is successfully used for describing the damage growth in the body. A constitutive equation in terms of stress and pseudo strain is first established for controlled-strain mode, and then transformed to controlled-stress constitutive equation by simply replacing stress and pseudo strain with pseudo stress and strain. The transformed constitutive equation in terms of pseudo stress satisfactorily predicts the mechanical behavior of asphalt concrete all the way up to failure under controlled-stress modes.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.3
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• pp.34-40
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• 2012

A pressure control law to regulate pressure of gas generator is suggested. To design a model based control law, the governing equation which consists of Robert and conservation equation is built and verified through the ground burning test. PID and nonlinear adaptive control laws are designed to analyze the loop response characteristics under the system which has varying eigen properties arisen from combustion volume change. It is suggested that new approach, gain scheduling design, is required to overcome the defects identified from numerical simulation results of the two control laws. The newly suggested scheme shows good control performance even under disturbances and measurement noise.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.1
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• pp.89-98
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• 2009

CMG cluster which consists of four CMGs can be used to produce 3-axis torque. There are many issues that we have to investigate and validate when CMG cluster itself is developed. Thus, its ground validation and verification processes are essential. Therefore, CMG simulator which uses a torque sensor to calculate satellite attitude is proposed in this paper. Update and kalman filter are also proposed for gimbal angle problem occurred in development. The first way uses a calculated gimbal angle as a primary and a sensor angle as a scondary to reduce error. Also, the test results of specific CMG steering law as well as attitude control logic are presented as an example.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.618-623
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• 2011

A pressure control law to regulate pressure of gas generator is suggested. To design a model based control law, the governing equation which is consisted of Robert and conservation equation is built and verified through the ground burning test. PID and nonlinear adaptive control laws are designed to evaluate the loop response characteristics under the system which has varying eigen properties as combustor volume is increased. It is suggested that new approach, gain scheduling design, is required to overcome the defects identified from numerical simulation results of the two control laws. The newly suggested scheme showed good control performance even under disturbances and measurement noise.