• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.2
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• pp.184-191
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• 2012

Aerodynamic analysis(DATCOM) and radar cross section(RCS) analysis(POFACETS) were integrated for the air-to-surface missile concept design using a design framework. The missile geometry was defined based on the CAD(CATIA) for synchronizing the manufacturing with design processes. Aero/RCS analyses were linked with the CAD process under the ModelCenter framework in order to receive the geometry data automatically. The missile design baseline configuration was selected from ROC(requirement of capability). Then the RCS minimization was performed subject to thelargerthebetter constraint of the missile lift-to-drag ratio. This study demonstrated that various design strategies can be performed efficiently about many missile configurations using this design framework in the missile conceptual design phase.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.3
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• pp.26-31
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• 2005

An efficient estimation of the aerodynamic characteristics for missile configurations is essential in the preliminary stage of a missile design. In this study, a Missile DATCOM family code based on the semi-empirical method was utilized for this purpose. In order to check the accuracy and reliability of the code several test cases have been considered: subsonic flow with high angles of attack and supersonic flow with moderate angles of attack. It turned out that the code in general provides prediction in qualitative agreement with the experimental data and results by other works. Finally, the code was applied to a more complicated missile configuration with canard and freely spinning tail fin.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.3
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• pp.228-239
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• 2019

In order to design the conceptual configuration of the short-range ballistic missile, the authors have established an optimization problem considering various aspects such as volume, aerodynamics, propulsion, structure, stability, and flight trajectory. For this purpose, the existing missile cases were analyzed and the design conditions and performance indices were derived. The performance of the whole system was analyzed by integrating each subsystem's model. Through the design example, we analyzed the relationship between various design variables and final performances.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.38-42
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• 2007

In this study, cruise missile configuration is optimal designed by using multidisciplinary analysis. Aerodynamic, weight, performance and mission analysis modules are developed by FORTRAN and integrated with framework. Darwin algorithm, a global optimization tool, is used for optimization. In the result of optimal design, gross weight of designed configuration is reduced about 17% than baseline configuration while satisfying design constraint conditions.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.4 no.4
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• pp.901-905
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• 2000

An elliptical ogive head for a generic missile is proposed to reduce its detectable probability from aground defense radar. Numerical RCS results of a generic missile with an elliptical ogive head are evaluated using the GTD/UTD (Geometrical Theory of Diffraction/uniform GTD). The results are compared with those of a cylindrical ogive head. In the sense of aerodynamics, the performance evaluation of an elliptical ogive head for a generic missile should be followed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.62-63
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• 2002

램젯 엔진을 장착한 미사일은 기존의 터보젯 이나 터보팬 엔진에 비해 압축기와 터빈과 같은 엔진 구성품이 없어 무게가 가볍고 초음속에서 저항도 적으며 고속의 비행영역에서 연료효율과 생존성능이 뛰어나기 때문에 차세대 미사일 추진 시스템으로서 세계 여러 국가에서 개발 및 운용이 이루어지고 있다. 하지만 램젯 엔진은 충분한 램 효과를 얻어야 초기 점화가 가능하기 때문에 현재 개발되고 있는 대부분의 시스템은 최초 발사시 로켓 부스터에 의해 가속하고 로켓연료를 모두 소모하고난 후에 흡입구가 개방되어 램젯 엔진이 점화하는 방식을 취하고 있다.

• Proceeding of EDISON Challenge
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• 2016.11a
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• pp.44-48
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• 2016

물 속에서 고속으로 유영하는 상당수의 어류는 긴 부리 모양의 주둥이를 가진다. 대표적으로 지구상 가장 빠른 물고기인 돛새치가 있다. 이러한 사실은 이 독특한 형상과 고속운동의 상관관계에 대해 학구적 호기심을 자아냈고 그에 따라 본 연구를 수행하였다. 본 연구에서는 돛새치, 청새치들의 2차원 형상을 가지고 부리의 존재 유무가 항력에 미치는 영향을 분석하고 더 나아가 미사일의 spike가 항력에 미치는 영향을 분석하였다. 또한 부리가 방향전환 시 기동성 증진에도 기여하는지를 알아보았다. 해석을 위해 Kflow Edison_13와 2D_Comp_P 해석자를 활용하여 동일 유동조건에서 항력계수를 비교하였다. 그리고 돛새치가 방향 전환할 때 발생하는 모멘트계수를 얻기 위해 2D_Incomp_P 해석자를 활용하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.11
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• pp.755-762
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• 2022

The wind tunnel test data for the missile configuration were compared with analysis results using various semi-empirical code and CFD analysis code. The three types of configurations were used for comparison including 2 types of main wing, inline and interdigitate configuration that the main wing and tail intersect. Additionally, it was confirmed that the vortex flow was accurately predicted by comparing the CFD analysis result with the flow visualization test result.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.4
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• pp.92-98
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• 2002

In this study, maximum launch range and F-pole are evaluated and analyzed for the semi-active radar missile concerning various launch condition, performance limitation and target maneuvers. Furthermore, general evasion maneuvers are considered when shooter approaches to target with head-on conditions. A point-mass target, shooter and missile model is used including aircraft and missile dynamics. More realistic missile motion simulation is conducted using aerodynamic performance data, geometry, performance limitation, radar seeker performance and so on. Maximum launch range, which is the distance for intercept satisfying target and missile motion and performance, is evaluated using root finding method. F-pole, which is the distance between target and shooter when intercept is completed, is evaluated assuming that shooter maneuvers through pursuit guidance to target.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.6
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• pp.519-526
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• 2009

This paper describes a research result of a external shape optimization study to maximize the range of the guided missile with canards and tailfins in atmospheric flight. For this purpose, the external shape optimization program which can enhance the range of a missile was developed, incorporated with the trajectory analysis and the optimization technique. In the trajectory analysis part, Missile DATCOM which utilizes the semi-empirical method was directly connected to the trajectory code to supply the aerodynamic coefficients efficiently at every time step. In the gliding flight trajectory after apogee, a maximum $C_L/C_D$ trim condition calculation module was attached under the assumption of the missile continuously flying at maximum $C_L/C_D$ condition. In the optimization part, a Response Surface Method(RSM) was adopted to reduce the computing time.