• Journal of Advanced Navigation Technology
• /
• v.17 no.1
• /
• pp.107-114
• /
• 2013

In this paper, we propose controller to control the acceleration of unmanned aircraft turbojet engine. The high-gain observer to estimate the rotational speed of compressor is used, and the turbojet engine controller applying fuzzy heuristic techniques and PID control algorithm are designed. fuzzy PID controller produces the flow control input to prevent the surge and flame-out phenomena at the acceleration and deceleration of the turbojet engine. The standard acceleration is set and the fuel flow control is defined by the fuzzy heuristic. Computer simulations are performed using MATLAB in order to verify the performance of the proposed controller.

• Journal of Advanced Navigation Technology
• /
• v.15 no.6
• /
• pp.1187-1193
• /
• 2011

In this paper, proposed controller preventing compressor surge and reducing the acceleration time of the fuel flow control system for turbo-jet engine. Turbo-jet engine controller is designed by applying fuzzy PID control algorithm and high-gain observer. Observer is used to estimate to compressor rotation speed of turbo-jet engine. Result of fuzzy inference is used as the fuel flow control inputs for preventing compressor surge and flame-out in turbo-jet engine. The controller is designed to converge to the desired speed quickly and safely. Using MATLAB to perform computer simulations verified the performance of the proposed controller.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
• /
• v.25 no.4
• /
• pp.434-441
• /
• 2014

Recently, a mutual interference threat has been increasing among the radar systems due to the rapid growth of the military radar operation. In this paper, the radar interference protection criteria is presented for interoperability in terms of the radar coverage and target detection probability in association with the international recommendation on the interference spectrum by ITU-R. The required criteria for the minimum allowable interference is also presented in terms of INR. In order to ensure the maximum detection probability of the radar under the mutual interference situation, only 5 % of detection range loss is allowed for the case of INR of -6 dB, and required SNR is presented at each INR in terms of the detection range and detection probability. This result will be useful for establishing the interference protection criteria in the combined military radar systems.

• Journal of Advanced Navigation Technology
• /
• v.17 no.6
• /
• pp.777-784
• /
• 2013

Synthesis process from the data produced by different types of sensor into a single information is being studied and used in a variety of platforms in terms of multi-sensor data fusion. Heterogeneous sensors has been integrated into various aircraft and modern avionic systems manage them. As the performance of sensors in aircraft is getting higher, the integration of sensor information is required from the viewpoint of avionics gradually. Information fusion is not studied widely in the view of software that provide a pilot with fused information from data produced by the sensor in the form of symbology on a display device. The purpose of information fusion is to assist pilots to make a decision in order to perform mission by providing the correct combat situation from avionics of the aircraft and to minimize their workload consequently. In the aircraft avionics equipped with different types of sensors, the software architecture that produce a comprehensive information using the sensor data through multi-sensor data fusion process to the user is shown in this paper.

• Journal of Advanced Navigation Technology
• /
• v.17 no.5
• /
• pp.560-567
• /
• 2013

In this paper, it is proposed the fault detection method of the ASIC, without the Test Requirement Document(TRD), extracting internal logic circuit and analyzed the function of the ASIC using the multipurpose development program and simulation. If there don't have the TRD, it is impossible to analyze the operation of the circuit and find out the fault detection in any chip. Therefore, we make the TRD based on the analyzed logic data of the ASIC, and diagnose of the ASIC circuit at the gate level through the signal control of I/O pins using the Dynamic Pattern signal. According to the experimental results of the proposed method, we is confirmed the good performance of the fault detection capabilities which applied to the non-memory circuit.

• Journal of Advanced Navigation Technology
• /
• v.17 no.6
• /
• pp.749-756
• /
• 2013

This paper presents an algorithm concerning the ground altitude measurement using a laser altimeter and an ultrasonic rangefinder for UAV(Unmanned Aerial Vehicle). A simple ground test conducted using the laser altimeter and ultrasonic rangefinder that are used for conducting the low altitude measurement of UAV and identify the characteristics of each sensor. Especially, the disadvantages of the laser altimeter were checked through the ground test. After that who those are participated in this paper planned the algorithm which is complemented by the ultrasonic rangefinder and the experiment was conducted. The laser altimeter and the ultrasonic rangefinder were fused by a loosely coupled method by Kalman filter. The paper shows that stable value of altitude complemented by the ultrasonic rangefinder that covers the laser altimeter's drawbacks can be measured through the ground test.

• Journal of Advanced Navigation Technology
• /
• v.22 no.2
• /
• pp.133-140
• /
• 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 Advanced Navigation Technology
• /
• v.8 no.1
• /
• pp.38-47
• /
• 2004

To achieve functions of doppler measurement, MTI(Moving Target Indicator), high-resolution, and others in radar system, all circuits of transmitter and receiver are to be performed in coherent system. In this paper, we use TWTA(Traveling Wave Tube Amplifier), STALO(Stable Local Oscillator) and COHO(Coherent Oscillator) to design of coherent radar transceiver, and calculates noise figure of designed receiver. Using radar equation calculated noise figure, maximum detecting range of each transmitting mode can be calculated.

• Journal of Advanced Navigation Technology
• /
• v.7 no.2
• /
• pp.162-170
• /
• 2003

In this paper, we propose a robust controller for trajectory control of n-link robot manipulators using feature based on visual feedback. In order to reduce tracking error of the robot manipulator due to parametric uncertainties, integral action is included in the dynamic control part of the inner control loop. The desired trajectory for tracking is generated from feature extraction by the camera mounted on the end effector. The stability of the robust state feedback control system is shown by the Lyapunov method. Simulation and experimental results on a 5-link robot manipulator with two degree of freedom show that the proposed method has good tracking performance.

• Journal of Advanced Navigation Technology
• /
• v.3 no.1
• /
• pp.1-12
• /
• 1999

For the phase measurement of radar signal in the coherent-on-receiver system, the COHO(Coherent Oscillator) generates the signal which locks to the phase of the transmit pulse. In this paper, COHO unit is developed to generate 60 MHz phase-locked signal. ILO(Injection Locking Oscilator) locks to the sample of the transmit pulse. Gate circuit, ILO, buffer amplifier, and pulse generator are designed and implemented.