• Defense and Technology
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• no.12 s.250
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• pp.46-53
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• 1999

미래 전술기의 생존성을 향상시키기 위한 기술적 수단으로 효과측면에서 충분히 고려할만한 가치가 있다고 생각되는 것을 다음과 같은 6개 항목으로 제한된다. (1) 침투비행시의 비행속도를 증가시킨다. (2) 침투비행시의 비행고도를 낮게 유지한다. (3)탑재무장에 큰 스탠드 오프 특성을 부여한다. (4) 탑재무장의 유도방식을 Fire and Forget 특성을 갖게 한다. (5) 기체에 스텔스 기술을 적극 활용한다. (6) EMC 능력을 더욱 강화시킨다.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.2
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• pp.23-45
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• 1994

본 연구 논문은 항공기 개발에 있어서 비행시험의 최종 단계라 할 수 있는 스핀시험의 정의, 스핀 시험방법 및 스핀 진입시의 회복방법과 실제 비행에서의 스핀 특성으로 스핀에 대한 안전성 제고 및 비행시험의 중요성을 논하였다.

• Journal of the Korea Society of Computer and Information
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• v.19 no.1
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• pp.169-179
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• 2014

This study conducted a comparison analysis of the differences by scope between juvenile delinquents, under sentence of juvenile protective disposition, and normal middle high school boys' self-esteem and sociality; it aims to search for the correctional policy to prevent juvenile delinquency. I conducted a survey, as a sampling target, of students (84) at Daedeok Juvenile Reformatory, located in Daejeon-si, Korea, and the normal middle high school boys (230). The results of analysis showed that in the analysis of self-esteem difference, juvenile delinquents were found high in the global self-esteem and school-academic self-esteem, but the normal adolescents were found high only in the scope of family-parents self-esteem. In leadership, a subordinate scope of sociality, juvenile delinquents showed the high result, and in independence and cooperativity, normal adolescents were found high. In conclusion, as the distinction between self-esteem and sociality is different by scope, depending on the individual's characteristic and environment, it suggests that the correctional policy through the customized plan is effective at preventing delinquency.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.10
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• pp.695-704
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• 2019

In hypersonic regime, the complicated interaction between the air and surface of aircraft results in intensive aerodynamic heating on body. Provided this phenomenon occurs on a hypersonic vehicle, the temperature of the body extremely increases. And consequently, thermal deformation is produced and material properties are degraded. Furthermore, those affect both the aerothermoelastic stability and thermal safety of structures significantly. With the background, thermal safety and dynamic stability are studied according to the altitude, flight time and Mach number. Based on the investigation, design guideline is suggested to guarantees the structural integrity of hypersonic vehicles in terms of both of thermal safety and dynamic stability.

• Journal of the Institute of Electronics Engineers of Korea SC
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• v.46 no.1
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• pp.87-96
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• 2009

In conventional method, flight model is discribed to differential equation by linealization of nonlinear object motion equation. As state equation from differential equation of moving object, the controller is designed by transfer functions of each module under discrimination of stability criteria. But this conventional method is designed under limitation of nonlinearity from object's shape and speed. In other word, The greater part of guidance/navigation system was satisfied with the result of good performance for normal figure of flight object, not sudden changed flight condition, not high speed. But it is not able to give full play to its ability on flight object which has abnormal figure, sudden changeable motion, high speed. Therefore, in this paper was presented performance analysis of load control model for navigation/guidance system on flying object being uncertainty, non-linear like abnormal figure, sudden changeable motion, high speed and is presented method of trajectory control(controllability) ahead of controllability and stability to achieve flight mission. In other word, this paper shows the first step of Min-design method and flight control model.

• Proceedings of the Korean Society of Computer Information Conference
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• 2008.06a
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• pp.63-68
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• 2008

성인 조직범죄집단은 조직유지와 활발한 조직활동을 위해 청소년 비행집단의 구성원을 포섭하려한다. 그리고 청소년 비행집단의 구성원은 다양한 이유로 인하여 조직범죄집단에 유입된다. 이는 당해 비행청소년은 물론 그 주변의 청소년들에게도 악영향을 미친다. 이러한 양 집단 간의 연계를 통한 유입현상을 통제하기 위하여 우선 청소년을 대상으로 비행행위에 대한 예방목적의 프로그램 활용은 물론 보다 효과적인 제도의 운용을 위한 구체적 논의가 필요하다. 이에 대해 청소년들이 활동하고 서로를 접하는 공간인 학교와 지역사회에서의 통제는 필수적이며 이러한 이유로 경찰과의 협력을 통한 예방활동에 주목할 필요가 있다.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.21 no.3
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• pp.1-8
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• 2013

An application of adaptive flight controller is required for the non-linear and high uncertain system that configuration of tiltrotor aircraft is dramatically changed from rotary wing mode to fixed wing mode. In this paper, the applicable adaptive controller for the tiltrotor aircraft was designed using Neural Networks and DMI (Dynamic Model Inversion). The performance of the SCAS (Stability and Control Augmentation System) was simulated against manned military specification, using the fullscale model of 'Smart UAV(Unmanned Aerial Vehicle)' developed by Korea Aerospace Research Institute. And Neural Networks based adaptive controller was verified through its whole operating envelope using the established HQ (Handling Quality) criteria.

• Journal of the Institute of Electronics Engineers of Korea TE
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• v.39 no.4
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• pp.350-354
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• 2002

In this paper, we designed an autopilot of the unmanned piloted vehicle to guide to the specific position, and analyzed robustness of the designed autopilot. We divide an aircraft velocity into the three case which are low, cruising and high speed, and designed autopilot gains are gain scheduled. We generated the turbulence for the operational altitudes and proved robustness of the designed autopilot for the turbulence using simulation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.6
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• pp.31-38
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• 2002

This paper presents the analysis of the flight test data measured by the sensors installed on a four-seat canard aircraft. The inherent stall proof characteristics of canard aircraft was verified from the stall test. The dihedral effect, adverse yaw and roll control power were examined and the neutral point that determines the longitudinal stability of the aircraft was investigated. The dynamic characteristics such as dutch roll mode were also examined. Without relying on the parameter identification method, the aerodynamic derivatives or the relations between the aerodynamic derivatives were obtained by analyzing the steady state flight data.

• Journal of the Korea Computer Graphics Society
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• v.19 no.1
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• pp.21-25
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• 2013

In this paper, we consider a physics-based 2D flight simulation game where users can easily control realistic flight of a vehicle equipped with two thrusters that allow vertical takeoff and vertical landing. The flight vehicle can be manipulated by directly controlling the thrusting force at each thruster using a pair of analog input devices such as joysticks. However, it might require too much practice to make aerobatic flying solely with this kind of control. We propose a set of fly-by-wire methods that provide easy-to-use, intuitive control of a VTVL vehicle. Based on PD controllers, the proposed methods allow users to specify the velocity or position of the vehicle directly. Furthermore, they are easy to understand and simple to implement. We expect that the proposed vehicle model and control mechanism could be used in various 2D games.