• Title/Summary/Keyword: Missile Control Fin

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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.

A Singular Perturbation-like Method to Compensate the Effect of Fin Actuator Dynamics in Nonlinear Missile Control (비선형 미사일 제어에서의 핀 구동기 동역학 영향을 보상하는 새로운 유사특이섭동기법)

  • Hong, Jin-Woo;Yeom, Joon-Hyung;Song, Seong-Ho;Ha, In-Joong
    • Proceedings of the KIEE Conference
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    • 2006.04a
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    • pp.219-221
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    • 2006
  • The recently developed autopilot controller can make the input-output (I/O) dynamic characteristics of the nonlinear missile dynamics linear and independent of flight conditions. However, significant fin actuator dynamics can degenerate the I/O dynamic performance of the overall system. In this paper, we propose a singular perturbation-like method to compensate the effect of significant fin actuator dynamics in nonlinear missile control. The proposed compensation method does not require the time derivatives of fin angles but can maintain the linear I/O dynamic characteristics provided by the recently developed autopilot controller.

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A New Approach to Structure of Aerodynamic Fin Control System for STT Missiles

  • Song, Chan-Ho;Lee, Yong-In;Kim, Seung-Hwan;Kim, Pil-Seong
    • 제어로봇시스템학회:학술대회논문집
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    • 2003.10a
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    • pp.537-541
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    • 2003
  • In order to control the missiles by aerodynamics, control surfaces sometime called fins are used. Deflection angles of these fins are the right control variables of the aerodynamics, but aerodynamicists prefer to use analytic variables called aileron, elevator and rudder instead of these physical variables, because these three analytic variables dominantly influence on the roll, pitch and yaw channels of the missile maneuver, respectively, and each can be assumed a linear combination of four fin deflection angles. On that basis, roll, pitch and yaw autopilots for controlling the attitudes or lateral acceleration of the missile are designed, and as a consequence outputs of each autopilot are aileron, elevator and rudder commands, respectively. In the existing fin control scheme for the typical tail-fin controlled cruciform missiles, firstly these outputs are distributed to four fin defection commands, and after that four fins are actuated by fin controllers so that their deflections follow the commands. This paper shows that performance of such control schemes can be degraded significantly when fin actuators have certain physical constraints such as slew rate, voltage or current limit, uncertainty of actuator dynamics, and so on, and propose a new control scheme which alleviates such problems. This scheme can be widely applied to various fin actuation systems. But in this paper, for convenience, tail-fin controlled cruciform missile is taken as an example, and it is shown that a proposed control scheme gives better performance than the existing one.

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Mixed Control of Agile Missile with Aerodynamic Fin and Thrust Vectoring Control (유도탄의 유도명령 추종을 위한 혼합제어기 설계 : 공력 및 추력벡터제어)

  • 이호철;최용석;송택렬;송찬호;최재원
    • Journal of Institute of Control, Robotics and Systems
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    • v.10 no.7
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    • pp.658-668
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    • 2004
  • This paper is concerned with a control allocation strategy using the dynamic inversion and the pseudo inverse control which generates the nominal control input trajectories. In addition, an autopilot design method is proposed by using time-varying control technique which is time-varying version of the pole placement of linear time-invariant system for an agile missile with aerodynamic fin and thrust vectoring control. The control allocation proposed in this paper is capable of extracting the maximum performance by combining each control effector, aerodynamic fin and thrust vectoring control. The adopted time-varying control technique for the autopilot design enhances the robustness of the tracking performance for a reference command. The main results are validated through the nonlinear simulations with aerodynamic data.

Analysis of control characteristics for high speed rolling guided missile with one axis steering fin (1축 날개 조종형 고속회전 유도탄의 조정 특성 해석)

  • Chin, Jong-Sok;Lee, Jae-Hyuk
    • Journal of Institute of Control, Robotics and Systems
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    • v.2 no.2
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    • pp.102-107
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    • 1996
  • It is difficult to analyze the high speed rolling missile with the generally used missile body fixed coordinates. In this study, we formulate the dynamic equations of the high speed rolling missile with the principal axis of inertia, and make the analytical model of one axis steering missile using pitch/yaw symmetry and complex summation method. With this model we analyze the control characteristics and propose the design considerations of high speed rolling missile with one axis control fin using PNG law in conjuntion with a seeker signal.

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Autopilot Design for Agile Missile with Aerodynamic Fin and Thrust Vecotring Control

  • Lee, Ho-Chul;Choi, Yong-Seok;Choi, Jae-Weon
    • 제어로봇시스템학회:학술대회논문집
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    • 2003.10a
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    • pp.525-530
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    • 2003
  • This paper is concerned with a control allocation strategy using the dynamic inversion which generates the nominal control input trajectories, and autopilot design using the time-varying control technique which is time-varying version of pole placement of linear time-invariant system for an agile missile with aerodynamic fin and thrust vectoring control. Dynamic inversion can decide the amount of the deflection of each control effector, aerodynamic fin and thrust vectoring control, to extract the maximum performance by combining the action of them. Time-varying control technique for autopilot design enhance the robustness of the tracking performance for a reference command. Nonlinear simulations demonstrates the dynamic inversion provides the effective nominal control input trajectories to achieve the angle of attack command, and time-varying control technique exhibits good robustness for a wide range of angle of attack.

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Mixed Control of Agile Missile with Aerodynamic Fin and Thrust Vectoring Control (공력 및 추력을 이용한 유도탄의 혼합제어기 설계(I))

  • 이호철;최용석;최재원;송택렬;송찬호
    • Journal of the Korea Institute of Military Science and Technology
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    • v.6 no.3
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    • pp.122-130
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    • 2003
  • This paper is concerned with a control allocation strategy using the dynamic inversion and the pseudo inverse control which generates the nominal control input trajectories, and autopilot design using time-varying control technique which is time-varying version of pole placement of linear time-invariant system for an agile missile with aerodynamic fin and thrust vectoring control. Control allocation of this paper is capable of extracting the maximum performance from each control effector, aerodynamic fin and thrust vectoring control, by combining the action of them. Time-varying control technique for autopilot design enhance the robustness of the tracking performance for a reference command. The main results are validated through the nonlinear simulation.

Disturbance Torque Suppression Control of Servo Motors for Missile Fin Actuators (미사일 Fin 액츄에이터용 서보모터의 외란 토크 억제 제어)

  • Kim, Chang-Hwan
    • Journal of National Security and Military Science
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    • s.1
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    • pp.311-343
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    • 2003
  • In this paper, we propose a generalized disturbance torque suppression control scheme of servo motors for missile fin actuators. Our controller consists of both a model based feed-forward controller and a stabilizing feedback controller. The feed-forward controller is designed such that the output of nominal plant tracks perfectly the reference position command with a desired dynamic characteristics. The feedback controller stabilizes the overall closed loop system. Furthermore, the feedback controller contains a free function that can be chosen arbitrary. The free function can be designed so as to achieve both the suppression of disturbances and the robustness to model uncertainties. In order to illuminate the superior performance of our control scheme to the conventional ones, we present some simulation results.

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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.

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.