• The Journal of the Acoustical Society of Korea
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• v.41 no.4
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• pp.461-467
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• 2022

Sonobuoy is a disposable device that collects underwater acoustic information and is designed to transmit signals collected in a particular area to nearby aircraft or ships and sink to the seabed upon completion of its mission. In a conventional sonobouy signal transmission and reception system, collected signals are modulated and transmitted using techniques such as frequency division modulation or Gaussian frequency shift keying, and received and demodulated by an aircraft or a ship. However, this method has the disadvantage of the large amount of information to be transmitted and low security due to relatively simple modulation and demodulation methods. Therefore, in this paper, we propose a method that uses an autoencoder to encode a transmission signal into a low-dimensional latent vector to transmit the latent vector to an aircraft or ship and decode the received latent vector to improve signal security and to reduce the amount of transmission information by approximately a factor of a hundred compared to the conventional method. As a result of confirming the sample spectrogram reconstructed by the proposed method through simulation, it was confirmed that the original signal could be restored from a low-dimensional latent vector.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2013.05a
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• pp.538-539
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• 2013

수평 자세제어에 관한 연구는 플랜트 외부에서 발생하는 미지의 진동이나 불특정 외란이 인가되었을 때 이러한 외란을 적절히 제거하여 플랜트의 안전성을 확보할 수 있는 중요한 기술이다. 특히 수평 자세제어에 대한 문제는 선박이나 항공기 등 진동이나 미지의 외란이 발생하는 비선형시스템에 대하여 플랜트의 안전성을 확보하기 위하여 다양한 제어 알고리즘을 적용하여 진동 및 외란을 제거하고 있다. 본 논문에서 활용하고자하는 수평 자세제어용 액추에이터는 전자기적 에너지를 직선운동을 하는 기계적 운동 에너지로 변환하는 장치로서 산업현장에서 많이 활용하고 있는 액추에이터이다. 이러한 리니어 액추에이터(linear actuator) 3개로 구성된 3축을 활용하여 리니어 액추에이터 상부에 놓여진 플랜트의 수평을 제어하고자 한다. 또한 플랜트의 수평 상태를 계측하기 위한 센서로는 플랜트에 인가되는 외란을 계측하기 위한 가속도 센서 및 정확한 플랜트의 자세를 계측하기 위한 자이로 센서를 활용하여 플랜트의 수평 상태를 계측하도록 하며, 3개의 리니어 액추에이터를 제어하기 위한 마이크로프로세서를 기반으로 PID 제어기를 설계하여 리니어 액추에이터를 활용한 수평제어 성능을 제시하고 한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.8
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• pp.707-712
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• 2014

Aircraft fuel indicator is a device to indicate the amount of fuel remained during flight, where accurate and consistent operation of the indicator should be maintained. Previously the Korean Utility Helicopter fuel indicator sporadically displayed abnormal sign by "8888" during flight, jeopardizing flight safety. Inappropriate EMI/EMC performance was detected during trouble shooting process. The cause of the abnormal display was found to be resulted from unstable power induced by electro-magnetic disturbance and CAN communication error. The aircraft fuel indicator design was improved and the design compatibility was verified to avoid abnormal display.

• Journal of Aerospace System Engineering
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• v.16 no.1
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• pp.86-96
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• 2022

The development trend of jet fighter's avionics system architecture is the digitization of subsystem component functions, increased RF sensor sharing, fiber optic channel networks, and modularized integrated structures. The avionics system architecture of the fifth generation jet fighters (F-22, F-35) has evolved into an integrated modular avionics system based on computing function integration and RF integrated sensor systems. The integrated modular avionics system of jet fighters should provide improved combat power, fault tolerance, and ease of jet fighter control. To this aim, this paper presents the direction and requirements of the next-generation jet fighter's avionics system architecture through analysis of the fifth generation jet fighter's avionics system architecture. The core challenge of the integrated modularized avionic system architecture requirements for next-generation fighters is to build a platform that integrates major components and sensors into aircraft. In other words, the architecture of the next-generation fighters is standardization of systems, sensor integration of each subsystem through open interfaces, integration of functional elements, network integration, and integration of pilots and fighters to improve their ability to respond and control.

• The Journal of the Korea institute of electronic communication sciences
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• v.12 no.4
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• pp.591-598
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• 2017

The changes of technology and the size of markets for unmaned aerial vehicle are getting bigger presently. Damage happens because of user's poor operation since accesses to the drones are easy. To minimize the damage, drone's stabilized flight skills are required, and controlling the motor to balanced speed is also needed. Thus, the essay shows that we use Arduino as a main control device for controlling a drone, and used acceleration sensor and gyro sensor for the drone stabilization. Also, we made it able to hover at a certain height by using a sonar sensor. We also controlled a drone by using an Android application, and made the drone hover stably at 0~2 meters.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.5
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• pp.417-428
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• 2017

In this paper, we describe the architectural design, unit component hardware design and core software design(Helmet Pose Tracking Software and Terrain Elevation Data Correction Software) of IHDS(Intelligent Helmet Display System), and describe the results of unit test and integration test. According to the trend of the latest helmet display system, the specifications which includes 3D map display, FLIR(Forward Looking Infra-Red) display, hybrid helmet pose tracking, visor reflection type of binocular optical system, NVC(Night Vision Camera) display, lightweight composite helmet shell were applied to the design. Especially, we proposed unique design concepts such as the automatic correction of altitude error of 3D map data, high precision image registration, multi-color lighting optical system, transmissive image emitting surface using diffraction optical element, tracking camera minimizing latency time of helmet pose estimation and air pockets for helmet fixation on head. After completing the prototype of all system components, unit tests and system integration tests were performed to verify the functions and performance.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.5
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• pp.124-133
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• 2003

We propose an application of the Object-Oriented design methodology to develop operational flight program(OFP) for stores management computer(SMC) which manages and controls stores inventory, stores activation, launch for missiles, and release of the conventional weapons. For the development of SMC, a military version of PowerPC 603e is used as a central processing unit board and VxWorks real-time operating system is used. The Tornado software development environment(SDE) and the programming language Ada95 are used for OFP development. We design three layerd in the OFP for the independency of the software modules. An avionics system computer(ASC) simulator and a test bench are developed for the SMC integration test and verification test. And the tests are rigorously and successfully conducted.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.38 no.5
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• pp.475-482
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• 2014

The precision hydraulic valve is widely used in various industrial field like aircraft, automobile, and general machinery. Servo actuator is the most important device for driving the precise hydraulic valve. The reliable operation of servo actuator effects on the overall hydraulic system. The performance of servo actuator relies on frequency response and step response according to arbitrary input signal. In this paper, we performed the analysis for the components of servo actuator to satisfy the reliable operation and response characteristics through the reliability analysis, and also induced the design parameters to realize the reliable operation and fast response characteristics of servo actuator for hydraulic valve operation through the empirical knowledge of experts and electromagnetic theories. We suggested the design equations to determine the values of design parameters of servo actuator as like bobbin size, length of yoke and plunger and turn number of coil, and verified the achieved design values through FEM analysis and performance tests using some prototypes of servo actuators adapted in hydraulic valve.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.4
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• pp.344-350
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• 2014

Multi Function Display(MFD) of Korean Utility Helicopter(KUH) is the component of mission management/display control system and displays image information(navigation, flight, survivability, digital map, maintenance) acquired from Mission Computer(MC) while the aircraft is operated. It is an essential equipment for pilots to perform flight mission and it has functions of display scene control, data display, built in test(BIT) and brightness control. In this paper, it is analyzed the cause of abnormal display(flickering) on MFD and summarized the design changes to solve the defect. It is also described system safety analysis and suggested verification results of flight/ground test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.5
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• pp.359-365
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• 2022

Air-to-ground missile(AGM), which can be operated by being mounted on the outside of the aircraft, is capable of precision strikes, ensuring high survivability. Helicopter, which is one of the AGM operating platforms, is reported to experience a lightning strike once between 1000 and 20000 flight hours in average. When the lightning strikes the helicopter fuselage, lightning transient signal can be induced to internal and external electronic equipment cables through the skin of the helicopter. If the transient signal exceeding the criteria to electrically initiated device(EID) related to the explosive in the AGM can affect the safety of the helicopter by a warhead explosion, etc. In this paper, we suggest an indirect lightning test method to prove the safety of AGM on helicopter, and present the indirect lightning test results.