• Title/Summary/Keyword: 미사일 조종날개

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Aeroelastic Analysis of Deployable Missile Control Fin with Bilinear Nonlinearity (이선형 비선형성을 포함하는 접는 미사일 조종날개의 공탄성 해석)

  • Bae, Jae-Sung;Shin, Won-Ho;Lee, In;Shin, Young-Sug
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.30 no.7
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    • pp.29-35
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    • 2002
  • Aeroelastic characteristics of a deployable missile control fin have been investigated. A deployable missile control fin is modeled by a 2-dimensional typical section. Supersonic Doublet-Point method is used for the computation of supersonic unsteady aerodynamic forces and Karpel's Minimum-State approximation is used for the aerodynamic approximation. Root-locus method and time-integration method are used for the linear and nonlinear flutter analyses. For the nonlinear flutter analysis the deployable hinge is represented by a asymmetric bilinear spring and is linearized by using the describing function method. From the flutter analyses, the effects of nonlinear parameters on the aeroelastic characteristics are investigated.

A Study on the Air to Air Missile Control Fin Optimization Using the Mathematical Modeling Based on the Fluid-Structure Interaction Simulation (수학적 모델링을 이용한 공력-구조 연계 시뮬레이션 기반 공대공 미사일 조종날개 최적화 연구)

  • Lee, Seung-Jin;Park, Jin-Yong
    • Journal of the Korea Society for Simulation
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    • v.25 no.1
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    • pp.1-9
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    • 2016
  • This study focuses on the air to air missile control fin planform optimization for the minimizing hinge moment with the considering phenomena of fluid and structure simultaneously. The fluid-structure interaction method is applied for the fluid and structure phenomena simulation of the control fins. A transient-loosely coupled method is used for the fluid-structure interaction simulation because it is suited for using each fluid and structure dedicated simulation software. Searching global optimization point is required many re-calculation therefore in this study, a mathematical model is applied for rapidly calculation. The face centered central composite method is used for generating design points and the 2nd polynomial response surface is sued for generating mathematical model. Global optimization is performed by using the generic algorithm. An objective function is the minimizing travel distance of the center of pressure between Mach 0.7 and 2.0 condition. Finally, the objective function of optimized planform is reduced 7.5% than the baseline planform with satisfying constrained conditions.

Model Establishment of a Deployable Missile Control Fin Using Substructure Synthesis Method (부구조물 합성법을 이용한 접는 미사일 조종날개 모델 수립)

  • Kim, Dae-Kwan;Bae, Jae-Sung;Lee, In;Han, Jae-Hung
    • Transactions of the Korean Society for Noise and Vibration Engineering
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    • v.15 no.7 s.100
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    • pp.813-820
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    • 2005
  • A deployable missile control fin has some structural nonlinearities because of the worn or loose hinges and the manufacturing tolerance. The structural nonlinearity cannot be eliminated completely, and exerts significant effects on the static and dynamic characteristics of the control fin. Thus, It is important to establish the accurate deployable missile control fin model. In the present study, the nonlinear dynamic model of 4he deployable missile control fin is developed using a substructure synthesis method. The deployable missile control fin can be subdivided Into two substructures represented by linear dynamic models and a nonlinear hinge with structural nonlinearities. The nonlinear hinge model is established by using a system identification method, and the substructure modes are improved using the Frequency Response Method. A substructure synthesis method Is expanded to couple the substructure models and the nonlinear hinge model, and the nonlinear dynamic model of the fin is developed. Finally, the established nonlinear dynamic model of the deployable missile control fin is verified by dynamic tests. The established model is In good agreement with test results, showing that the present approach is useful in aeroelastic stability analyses such as time-domain nonlinear flutter analysis.

Nonlinear Flutter Analysis of Missile Fin considering Dynamic Stiffness of Actuator (구동장치의 동강성을 고려한 미사일 조종날개의 비선형 플러터 해석)

  • Shin, Won-Ho;Bae, Jae-Sung;Lee, In;Han, Jae-Hung;Shin, Young-Suk;Lee, Yeol-Wha
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.33 no.2
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    • pp.54-59
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    • 2005
  • Nonlinear aeroelastic analyses of a missile control fin are performed considering backlash and dynamic stiffness of actuator. Doublet-Hybrid method is used for the calculation of subsonic unsteady aerodynamic forces, and aerodynamic forces are approximated by the minimum-state approximation. For nonlinear flutter analysis backlash is represented by a free-play and is linearized by using the describing function method. Also, dynamic stiffness is function of frequency and is calculated by solving equation of motion for actuator. The linear and nonlinear flutter analyses show that the aeroelastic characteristics are significantly dependent on the backlash and dynamic stiffness. From the nonlinear flutter analysis, various types of limit cycle oscillations are observed in a range of air speeds below the linear divergent flutter boundary. The nonlinear flutter characteristics and the nonlinear aeroelastic responses are also investigated in the time domain.

The stabilization of a missile actuator using fuzzy controller (퍼지제어에 의한 미사일 조종날개용 구동모터의 안정화에 관한 연구)

  • Kim, Sang-Woo;Kwon, Yong-Soo
    • Proceedings of the KIEE Conference
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    • 1998.07a
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    • pp.18-21
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    • 1998
  • A stabilization scheme of a missile actuator using fuzzy controller is proposed. A variable-reluctance stepping motor adopted as a actuator is critically restricted useful operation since pronounced oscillatory behaviour at a certain input frequencies. The previous stabilization scheme. which employs frequency modulation, of the clock-pulse source using derived from the modulation envelope of the total intake current is modified using fuzzy control. The proposed scheme has apparent advantage, particularly in size, mass and flexibility.

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Nonlinear Dynamic Characteristics of Deployable Missile Control Fin (접는 미사일 조종날개의 비선형 동특성)

  • Kim, Dae-Kwan;Bae, Jae-Sung;Lee, In;Shin, Young-Sug;Lee, Yeol-Wha
    • Transactions of the Korean Society for Noise and Vibration Engineering
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    • v.12 no.10
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    • pp.808-815
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    • 2002
  • The nonlinear characteristics for hinge of a deployable missile control fin are investigated experimentally. The nonlinearity is caused by a worn or loose hinge and manufacturing tolerance and cannot be eliminated completely. The structural nonlinearity has an effect on the static and dynamic characteristics of the control fin. Therefore, it is necessary to establish the accurate nonlinear model for the hinge of the control fin. In the present study the existence of nonlinearities in the hinge is confirmed from the frequency response experiments such as tip random excitation and base sine sweep. Using the system identification method. especially, ″Force-state Mapping Technique″, the types of nonlinearities are identified and the nonlinear hinge model of the control fin is established.

Nonlinear Hinge Dynamics Estimation of Deployable Missile Control Fin (접는 미사일 조종날개의 비선형 힌지 동특성 파악)

  • Kim, Dae-Kwan;Bae, Jae-Sung;Lee, In;Woo, Sung-Hyun
    • Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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    • 2002.05a
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    • pp.848-854
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    • 2002
  • The nonlinear characteristics for the hinge of a deployable missile control fin are investigated experimentally. The nonlinearity is caused by a worn or loose hinge and manufacturing tolerance and cannot be eliminated completely. The structural nonlinearity has an effect on the static and dynamic characteristics of the control fin. Therefore, it is necessary to establish the accurate nonlinear model for the hinge of the control fin. In the present study the existence of nonlinearities in the hinge is confirmed from the frequency response experiments such as tip random excitation and base sine sweep. Using the system identification method, especially, “Force-State Mapping Technique”, the types of nonlinearities are identified and the nonlinear hinge model of the control fin is established.

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