• Journal of the Korea Institute of Military Science and Technology
• /
• v.17 no.2
• /
• pp.189-196
• /
• 2014

Automated design program using commercial process integration and optimization program was developed for conceptual design of fighter-class aircraft. Wind tunnel test data and performance analysis results were compared for the verification of analysis tool of this program, and the usefulness of the tool was found. After integration with radar cross section analysis tool, the correlation with configuration design variables of wing, tail and performance parameters was identified by design of experiment, and the optimized configuration for weight and RCS was derived from optimization of empty weight and average frontal RCS value. After parameter definition of fuselage, the program can be implemented for full aircraft configuration.

• Journal of the military operations research society of Korea
• /
• v.33 no.1
• /
• pp.117-133
• /
• 2007

The weapon accuracy is a basic measure of performance in the area of weapon system acquisition. It requires the establishment of correct concept and the T&E methods. Existing T&E method for aircraft weapon systems have not considered types of exact hitting area for various weapons. This study intends to suggest an optimal T&E methods in Korean T&E environment. In order to sampling and to test aircraft weapon accuracy, we need probability and statistic theories. There are many types of CEP(Circular Error Probable) methods. We recommend 2 types of CEP methods which are Lockheed Martin CEP method and Johnson CEP method. Also, suggest some other T&E methods. These methods can be used to accuracy test in the area of weapon system acquisition in the future.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
• /
• 2004.11a
• /
• pp.768-771
• /
• 2004

항공기 소음평가 방법에 있어 전혀 다른 소음특성을 갖는 군용 항공기 소음과 민간 항공기 소음을 환경부에서 고시한 소음 진동공정 시험방법에 의거하여 소음을 측정하고 평가하는데는 많은 문제점이 뒤따른다. 따라서 본 연구에서는 민간 항공기와 군용 항공기 소음의 측정 및 평가방법에 대한 문제점들을 고찰하였다. 연구결과로 부터, 민간 항공기나 군용 항공기의 정확한 소음측정을 위해서는 동특성을 빠름(Fast)으로 설정하여 측정하는 것이 바람직한 것으로 확인되었다. 또한 등가 소음도를 측정하여 항공기 소음을 평가하는 방식은 민간 항공기 소음평가시에는 적절하지만, 이를 군용 항공기 소음에 적용하여 평가할 때에는 상당한 오차를 포함하는 것으로 조사되었다. 그리고 군용 항공기 이 착륙지점에서의 소음 지속시간이 대부분 30초를 초과하는 것으로 조사되었기 때문에, 군용 항공기 소음평가시에는 지속시간에 대한 보정이 반드시 반영되어야 할 것으로 사료된다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.47 no.3
• /
• pp.212-219
• /
• 2019

As unmanned aerial vehicle (UAV) has been utilized for military operation, efficient ways for controlling UAV has been necessary. In particular, instead of conventional approach using console control, speech recognition based UAV control is essential for military environments in which rapid command operation is required. But research on this novel approach is not actively studied yet. In this study, we introduce efficient ways of speech recognition system operation for voice-driven UAV control, focusing on mission command control from manned aircraft rather than ground control center. We propose an efficient way of system operation for UAV control in cooperation of aircraft and UAV, and verify its efficiency via speech recognition experiment.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.25 no.4
• /
• pp.401-411
• /
• 2022

As the role of high-value air assets(e.g., AWACS, JSTARS, Rivet Joint, E-2) becomes more critical in modern warfare, the air escort for these assets blocking attacks from any potential enemy fighter also becomes vital. Without the escort, the operations of the assets become restricted. However, such an escort is not always possible due to the limited flight time of the escort fighters. In this paper, we introduce an escort tactics for high-value air assets performed by the manned-unmanned teaming composed of a transport aircraft and UAVs(unmanned aerial vehicles). In this tactics, the transport aircraft plays the role of an aircraft carrier, which carries, launches, and retrieves the UAVs. The missions of UAVs in this tactics are to detect and engage enemy fighters. We also introduce the simulation result of this tactics to identify the UAVs' required capabilities and optimal maneuvering.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.26 no.3
• /
• pp.214-226
• /
• 2023

A transfer alignment is used to initialize, align, and calibrate a SINS(Slave INS) using a MINS(Master INS) in motion. This paper presents an airborne transfer alignment with velocity and azimuth matching to estimate inertial sensor biases under the wing flexure influence. This study also considers the lever arm, time delay and relative orientation between MINS and SINS. The traditional transfer alignment only uses velocity matching. In contrast, this paper utilizes the azimuth matching to prevent divergence of the azimuth when the aircraft is stationary or quasi-stationary since the azimuth is less affected by the wing flexibility. The performance of the proposed Kalman filter is analyzed using two factors; one is the estimation performance of gyroscope and accelerometer bias and the other is comparing aircraft dynamics and attitude covariance. The performance of the proposed filter is verified using a long term flight test. The test results show that the proposed scheme can be effectively applied to various platforms that require airborne transfer alignment.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.2 no.1
• /
• pp.121-131
• /
• 1999

Automatic Rudder Trim System(ARTS) is a device to reduce the pilot's work load for rudder trimming greatly required in varying abruptly aircraft's engine power. This paper represents a technical analysis and a design of control law of the ARTS. The control law of the ARTS is designed based on the analysis of aircraft's characteristics, system's requirements, and limitations. The control law is comprised of open loop control using the rudder trim map for a specific aircraft and closed loop control to compensate the error of the open loop control system. flight test results show that the ARTS can reduce pilot's work load for rudder trimming dramatically and can compensate the aircraft's transient yaw motion.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.4 no.1
• /
• pp.137-146
• /
• 2001

According to the advanced development of Light Weight Torpedo, the overall items related with the parachute type and gore layout and air stabilizer of the parachute for fixed and rotary wing aircraft are described in this paper. Also, the drag-area which should satisfy the firing envelope, parachute inflation characteristics, stability of parachute and torpedo in airdropping, water entry impact on torpedo and parachute constituted the principle design factors. The important trial and errors occurred in the step of performance of the parachute for fixed and rotary wing aircraft are investigated and analyzed.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
• /
• 2007.05a
• /
• pp.604-608
• /
• 2007

The INM simulation program is used to estimate the condition of the exposed area to the noise near a military airport in Korea. $WECPNL_k$, the evaluation unit of korean airport noise, is different from the ICAO $WECPNL_I$ that is used in the simulation program. Therefore, it is inappropriate to compare these units each other directly. This study presents method of comparison between them by using $LA_{MAX}$. The aircraft events are classified into three classes, as departure, overfly and approach. In result, the measurement and simulation seemed to be similar at departure and approach pattern. However, overfly pattern had higher errors between measurement and simulation. Finally, it is necessary to examine the method to determine flight events and duration for the $WECPNL_k$ application.

• Journal of the military operations research society of Korea
• /
• v.3 no.2
• /
• pp.119-134
• /
• 1977

The goal of this study is to determine which is the better bomb; a general purpose bomb or a special bomb, from the point of view of cost-effectiveness of air munitions. What we call the special bomb is a laser guided bomb which adds a guidance control unit on the head of a general purpose bomb. Althrough their characteristics of explosion are the same, their effectivenesses are very defferent due to their probability of hitting the targets. Now, in order to measure their relative a effectiveness, we could select various enemy targets such as runway, radar, and then Ive could also calculate requirments of both bombs and firghter aircraft sorties according to the desired damage level of each target, Following above steps, we can derive the total costs and compare effectiveness. As a results of this study, when the attrition rate of aircraft is under $1.1\%$, the general purpose bomb is better than the laser guided bomb. Above $1.1\%$ attrition rate, we could say that luser guided bomb is the most economical bomb.