• Title/Summary/Keyword: Guided missile

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Effect of Evasive Maneuver Against Air to Air Infrared Missile on Survivability of Aircraft (공대공 적외선 위협에 대한 회피기동이 항공기 생존성에 미치는 영향)

  • Bae, Ji-Yeul;Bae, Hyung Mo;Kim, Jihyuk;Jung, Dae Yoon;Cho, Hyung Hee
    • Journal of the Computational Structural Engineering Institute of Korea
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    • v.30 no.6
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    • pp.501-506
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    • 2017
  • An infrared seeking missile does not emit any signal by itself as it is guided by passive heat signature from an aircraft. Therefore, it is difficult for the target aircraft to notice the existence of incoming missile, making it a serious threat. The usage of MAW(missile approach warning) that can notify the approaching infrared seeking missile is currently limited due to its high cost. Furthermore, effectiveness of MAW against infrared seeking missile is not available in open literature. Therefore, effect of evasive maneuver by MAW on the survivability of the aircraft is simulated to evaluate the benefit of the MAW in this research. The lethal range is used as a measure of aircraft survivability. An aircraft flying at an altitude of 5km with Mach 0.9 being tracked by air-launched AIM-9 infrared seeking missile is considered in this research. As a variable for the evasive maneuver, the MAW recognition distance of 5~7km and the G-force of 3~7G that limits maximum directional change of the aircraft are considered. Simulation results showed that the recognition of incoming missile by MAW and following evasive maneuver can reduce the lethal range considerably. Maximum reduction in lethal range is found to be 29.4%. Also, the MAW recognition distance have a greater importance than the aircraft maneuverability that is limited by structural limit of the aircraft.

Heat Source Identification Technique of Aircraft and Flare using 2-color Detectable Infrared Sensors (복수 대역 감지 적외선 센서를 이용한 항공기와 플레어의 열원 식별 기술)

  • Lee, Dong-Si;Lee, Kee-Keun
    • The Transactions of The Korean Institute of Electrical Engineers
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    • v.64 no.7
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    • pp.1031-1039
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    • 2015
  • Present guided missiles are equipped with infrared seeker to find the infrared sources radiating from target plane and then chase, which results in an improvement of the hitting success rate when in striking target objects. To interrupt the chases from the guided missile, the target plane spreads the flare, avoiding the missile attracts. Our research is to develop a 2-color infrared identification technique to discern the flare and real thermal source from target plane. Considering flare radiation properties and EM atmosphere transmission rates, two channels were selected, in which main channel (MC) was in a range of 3.7 μm∼4.8 μm and auxiliary channel (AC) in 1.7 μm∼2.3 μm. A 2500K heat source was used for an artificial flare source, while a 570K heat source was utilized for airplane infrared source in experimental testing. Two infrared sensors detectable only at each chanel were employed in order to measure the voltage ratio from two channels, identifying the flare and real target plane via comparison the voltage ratio. Several experimental conditions were imported in order to prove that our proposed 2-color infrared identification technique is very efficient way to discern heat sources from aircraft and flare, demonstrating that our proposed technique is very promising means for our force’s InfraRed Counter Counter Measure (IRCCM) in order to countermeasure opposite force’s InfraRed Counter Measures (IRCM).

Development of guided weapon systems and the role of satellites (유도무기체계의 발전과 인공위성의 역할)

  • Hyun-seung Son;Kyung-won Oh
    • Journal of Aerospace System Engineering
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    • v.17 no.4
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    • pp.75-86
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    • 2023
  • The guided missiles and decoy systems that have been developed have been likened to a spear and shield. When a new attack system appears, another defense system is developed, and the attack system is once again upgraded to neutralize it. Now, due to the limitations of the decoy system, guided weapons have become the main force of both the defense and attack systems. Also, these systems have been expanded to use Space systems as a means of defending against a guided weapon system that is too fast for terrestrial-based systems. Induced weapon systems started at the sub-sonic level, and have become so important that their speeds have become super-sonic and hyper-sonic. The concept of Space has been included in the range of guided missiles, and satellite systems have become essential elements of guided missiles. Focusing on the correlation between the guided missile system and the satellite system, we analyze the characteristics of modern guided munitions and the direction of development of the guided weapons system.

Analysis of the Combat Effectiveness of FFG with Guided-Rocket on the Threats of Multiple USV (다수 무인수상정 위협에 대한 호위함용 유도 로켓의 전투효과도 분석)

  • MIN, Seungsik;OH, Kyungwon;RYU, Jaekwan
    • Journal of Aerospace System Engineering
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    • v.14 no.5
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    • pp.58-65
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    • 2020
  • In this paper, the combat effectiveness of ship guidance rockets to counter the threat of multiple USV(Unmanned Surface Vehicle) was analyzed in three cases. The probability of sinking a number of USVs approaching by distance was compared using various weapon systems and guided rocket systems installed on the naval vessels. As a result of the analysis, it was found that the combat effectiveness of the guided rocket was improved compared to the close defense system of the anti-ship missile installed on the naval vessels.

A NUMERICAL STUDY ON THE CHARACTERISTICS OF ASYMMETRIC VORTICES AND SIDE FORCES ON SLENDER BODIES AT HIGH ANGLES OF ATTACK (세장형 물체 주위 고앙각 유동의 비대칭 와류 및 측력 특성에 관한 수치적 연구)

  • Jung S.K.;Jung J.H.;Myong R.S.;Cho T.H.
    • Journal of computational fluids engineering
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    • v.11 no.3 s.34
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    • pp.22-27
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    • 2006
  • Flow around a guided missile in high maneuver, i.e. at a high angle of attack, shows complex phenomena. It is well known that even in geometrically symmetric conditions the flow around a missile at high angles of attack can generate unexpected large side forces and yaw moments due to asymmetric vortices. In this paper, a CFD code (FLUENT) based on the Navier-Stokes equations was used for the numerical analysis to find a suitable numerical mechanism for generation of asymmetric vortices. It is shown that a numerical technique of applying different surface roughness to a specific area of the missile nose surface gives the best fit in comparison with the experimental results. In addition, a numerical investigation of variations of side forces and pressure distributions with angle of attack and roll angle was conducted for the purpose of identifying the source of vortex asymmetries.

A Study on the Development of HWIL Simulation Control System for High Maneuver Guided Missile System (고기동 유도무기를 위한 HWIL 시뮬레이션 제어 시스템 개발 연구)

  • Kim, Woon-Sik;Lee, Byung-Sun;Kim, Sang-Ha
    • The Journal of Korean Institute of Communications and Information Sciences
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    • v.35 no.11B
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    • pp.1659-1666
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    • 2010
  • The High maneuver missiles use various interfaces and high speed guidance and control loop. Hardware-in-the-Loop(HWIL) simulation control system, therefore, should have high performance computing power and hardware interface capabilities, and should be developed using IT technology with which real time operating system, embedded system, data communication technology, and real time hardware control are integrated. This paper suggests the control system design techniques, such as a system hardware configuration, a job distribution algorithm for high performance multi-processors, a real time calculation and control mechanism, inter-processor communication mechanism, and a real time data acquisition technique, to perform the HWIL simulation for high maneuver missile system.

Precise Impact Angle Control Using Analytic Solution of Biased Proportional Navigation with Single Dynamic Lag (동적지연을 포함하는 편향 비례항법 유도루프의 해석 해를 이용한 정밀 충돌각 제어)

  • Moon, Han-Bit;Ra, Won-Sang;Whang, Ick-Ho;Kim, Yong-Jung
    • Proceedings of the KIEE Conference
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    • 2011.07a
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    • pp.1736-1737
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    • 2011
  • This paper deals with the problem of precise impact angle control of an actual homing missile guided by biased proportional navigation (BPN). To do this, the BPN guidance loop including dynamic lag is modeled as the confluent hyper-geometric differential equation and its analytic solution is derived. Based on the solution, a systematic way to determine the bias constant is newly devised. Different from the existing BPN solution obtained by ignoring the dynamic lag, the proposed one can exactly describe the behavior missile before target interception. hence it is drastically improved the angle constrained terminal guidance performance.

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Target Adaptive Guidance Using Near-Zone Information from IR Seeker (근접영역에서의 IR 탐색기 정보를 이용한 표적적응유도)

  • 엄태윤;김필성
    • Journal of the Korea Institute of Military Science and Technology
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    • v.5 no.3
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    • pp.113-119
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    • 2002
  • A target adaptive guidance(TAG) algorithm is proposed employing the near-zone signal that can be measured from an infrared seeker. The guidance order is composed of a conventional PNG command and an additional command to be calculable from an additional LOS rate between a hot point of target and a required intercept point. The characteristic of the near-zone signal is similar to that of LOS rate that is inversely proportional to the square of time-to-go. Hence the proposed scheme can be applied to real systems with no estimator for time-to-go. From analysis results on the miss distance with perfect missile and perfect seeker, it follows that the proposed TAG algorithm guarantees missile to be ideally guided to the required intercept point. And it is less affected by the TAG start time and a proportional navigation ratio than other TAG schemes using a LOS rate such as a step bias or a ramp bias.

Performance Analysis of Proportional Navigation Guidance Law against Randomly Maneuvering Targets (임의의 방향조정을 하는 목표물에 대한 비례항법의 성능분석)

  • 하인중;고명삼;허종성;이택렬;안조영;이장규
    • The Transactions of the Korean Institute of Electrical Engineers
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    • v.39 no.2
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    • pp.192-198
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    • 1990
  • The performance of the proportional navigation guidance(PNG) law for a target with constant acceleration has been extensively studied in the prior literature. In this papaer, we consider the performance of the PNG law for a randomly maneuvering target. By means of Lyapunov method, we prove that an ideal missile guided by the conventional PNG law can always intercept a randomly maneuvering target if the initial missile heading error is small and the navigation constant is chosen sufficiently large. To the authors' best knowledge, this is the first analytic result on the performance of the PNG law for a target with time-varying acceleration.

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A Study of Missile Guidance Performance Enhancement using Multi-sensor Data Fusion in a Cluttered Environment (클러터 환경에서 다중센서 정보융합을 통한 유도성능 개선 연구)

  • Han, Du-Hee;Kim, Hyoung-Won;Song, Taek-Lyul
    • Journal of Institute of Control, Robotics and Systems
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    • v.16 no.2
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    • pp.177-187
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    • 2010
  • A MTG (Multimode Tracking and Guidance) system is employed to compensate for the limitations of individual seekers such as RF (Radio frequency) or IIR (Imaging Infra-red) and to improve the overall tracking and guidance performance in jamming, clutter, and adverse weather environments. In the MTG system, tracking filter, data association, and data fusion methods are important elements to maximize the effectiveness of precision homing missile guidance. This paper proposes the formulation of a Kalman filter for the estimation of line-of-sight rate from seeker measurements in missiles guided by proportional navigation. Also, we suggest the HPDA (Highest Probability Data Association) and data fusion methods of the MTG system for target tracking in the adverse environments. Mont-Carlo simulation is employed to evaluate the overall tracking performance and guidance accuracy.