• Proceedings of the Korean Society of Computer Information Conference
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• 2020.01a
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• pp.35-36
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• 2020

본 연구는 TA-50 항공기 임무컴퓨터에서 JDAM을 가상으로 운용하는데 필요한 소프트웨어 개선 내용 중 가상 JDAM 무장 투하 구역 계산 방법을 제안한다. 이 연구에서 제안한 무장투하구역 알고리즘은 FA-50 JDAM DLZ에서 추출한 무장투하구역 입/출력값을 tensorflow를 사용하여 학습한 알고리즘이다. 이 연구를 통해 제안한 가상 JDAM DLZ 알고리즘을 사용할 경우 실제 무장을 장착하지 않은 항공기에서 가상으로 JDAM 무장 투하 구역 표시가 가능하고, 조종사는 가상의 JDAM DLZ를 참고하여 무장 투하 훈련을 수행할 수 있다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.10
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• pp.894-900
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• 2012

The purpose of this research is to investigate the dynamic roll-damping characteristics of a spin-stabilized projectile in wind-tunnel testing. In the present work, the high-speed wind-tunnel tests for the roll-damping measurements were conducted on a finned spin-stabilized projectile model in the Agency for Defense Development's Trisonic Wind Tunnel at spin rates about 8,000 rpm. The test Mach numbers ranged from 0.6 to 0.9, and the angles of attack ranged from 0 to +15 deg. The evaluation of the bearing friction parameter was also conducted to eliminate the tare damping moment from the aerodynamic damping moment.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.10
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• pp.912-918
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• 2011

The purpose of this research is to determine the dynamic roll-damping data of a spinning projectile in wind-tunnel testing. In the present work, the high-speed wind-tunnel tests for the roll-damping measurements were conducted on a spin-stabilized projectile model in the Agency for Defense Development's Tri-Sonic Wind Tunnel at spin rates about 12,000 rpm. The test Mach numbers ranged from 0.7 to 1.05, and the angles of attack ranged from -4 to +10 deg. The validity of the wind-tunnel measurement techniques was evaluated by comparing them with the previous test results on the same configuration.

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.2
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• pp.48-59
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• 2017

In this study, an analysis of the thermo-fluid dynamic and missile-motion performance was carried out through a numerical simulation inside the missile canister. Calculation was made in an analytical volume using dynamic grid and evaporated water was used as a coolant. To analyze the interaction among the hot gas, coolant, and mixture flow, Realizable $k-{\varepsilon}$ turbulence and VOF (Volume Of Fluid) model were chosen and a parametric study was performed with the change of coolant flow rate. As a result of the analysis, pressure of the canister showed a large difference depending on the presence or absence of the coolant, and also showed a dependancy on the amount of coolant. Velocity and acceleration were dependent on the canister pressure.

• Transactions of the Korean Society of Mechanical Engineers
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• v.17 no.5
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• pp.1084-1094
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• 1993

An efficient method for determining forced responses of a general linear structural system in time domain using subtructure modes and Lagrange multipliers is presented. Compared with the conventional mode synthesis methods, the suggested method does not construct the equations of motion of the combined whole structure and thus the modal parameters of the whole structure are not required. Only modal parameters of each substructure and geometric compatibility conditions are needed. Both the loaded interface free-free modes and free interface modes can be employed as the modal bases of each substructure. Recurrence discrete-time state equations based upon state transition matrix are formulated for the transient analysis of a parameter-changing system. It is shown form numerical examples that the suggested method is very accurate and efficient to calculate transient responses compares with the direct numerical integration method.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.9
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• pp.762-772
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• 2014

A weapon control algorithm equipped on a fighter is closely related to the mission accomplishment and fighter survivability during engagement. The weapon control algorithm typically provides a pilot the dynamic launch zone(DLZ), the target shoot-down range of air-to-air missiles, in the head-up display(HUD). DLZ is produced by an engagement range computation algorithm. In this paper, the components of DLZ for AIM-9 and AIM-120 air-to-air missiles are introduced. The real-time computation algorithm for DLZ based on the pseudo 6-DOF program is then addressed The operational aspects of DLZ algorithm for the air-to-air missiles to various engagement scenarios is investigated vis simulations.