• Title/Summary/Keyword: Bank-to-turn Missile

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A New Approach to Motion Modeling and Autopilot Design of Skid-To-Turn Missiles

  • Chanho Song;Kim, Yoon-Sik
    • Transactions on Control, Automation and Systems Engineering
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    • v.4 no.3
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    • pp.231-238
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    • 2002
  • In this paper, we present a new approach to autopilot design for skid-to-turn missiles which may have severe aerodynamic cross-couplings and nonlinearities with angle of attack. The model of missile motion is derived in the maneuver plane and, based on that model, pitch, yaw, and roll autopilot are designed. They are composed of a nonlinear term which compensates for the aerodynamic couplings and nonlinearities and a linear controller driven by the measured outputs of missile accelerations and angular rates. Besides the outputs, further information such as Mach number, dynamic pressure, total angle of attack, and bank angle is required. With the proposed autopilot and simple estimators of bank angle and total angle of attack, it is shown by computer simulations that the induced moments and some aerodynamic nonlinearities are properly compensated and that the performance is superior to that of the conventional ones.

The Body-Coupling Compensation in the 2-Gimbaled Seeker for the Homing Guidance of Bank-to-Turn Missile (Bank-to-Turn 유도탄의 호밍유도를 위한 2축 김발형 탐색기 동체운동 상관 보상)

  • Jeong, Sang-Keun;Kim, Eul-Gon
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.30 no.6
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    • pp.101-106
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    • 2002
  • In a bank-to-turn(BTT) missile, if a 2-gimbaled seeker was stabilized using a 2-axis rate gyro mounted along its primary axis, the change of line of sight(LOS) measured by the seeker would be induced by rolling effects due to bank-to-turn(BTT) steering as well as an actual change. It is observed that the body-coupled effects in a homing loop of BTT missile are mainly concerned with the spurious target maneuver and the coupling due to the rate gyro misalignments. In this paper, we formulate a simple linear BTT homing loop model with seeker model including each body-coupling. With the model, we analyze the effects of the couplings on the homing loop stability, and propose a direct linear compensator for the coupling to recover the stability.

A Gain-Scheduled Autopilot Design for a Bank-To-Turn Missile Using LMI Optimization and Linear Interpolation

  • Shin, Myoung-Ho;Chung, Myung-Jin;Lee, Chiul-Hwa
    • 제어로봇시스템학회:학술대회논문집
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    • 2001.10a
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    • pp.48.3-48
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    • 2001
  • A gain-scheduled autopilot design for a bank-to-turn (BTT) missile is developed by using the Linear Matrix Inequality (LMI) optimization technique and a state-space lineal interpolation method. The missile dynamics are brought to a quasilinear parameter varying (quasi-LPV) form. Robust linear control design method is used to obtain state feedback controllers for the LPV systems with exogenous disturbances at the frozen values of the scheduling parameters. Two gam-scheduled controllers for the pitch axis and the yaw/roll axis are constructed by linearly interpolating the robust state-feedback gains. The designed controller is applied to a nonlinear six-degree-of-freedom (6-DOF) simulations.

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Robust missile autopilot design using a generalized singular optimal control technique (최적 제어 기법을 사용한 자동조종장치의 설계)

  • 백운보;이만형
    • 제어로봇시스템학회:학술대회논문집
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    • 1986.10a
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    • pp.498-502
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    • 1986
  • A generalized singular linear quadratic control technique is developed to design an optimal trajectory tracking system. The output feedback control law is designed using this technique. The feedback gain matrix is synthesized to minimize tracking errors with pole placement capability to satisfy the control activity requirements. An applications to a bank-to-turn missile coordinated autopilot system design is presented.

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Design of an Autopilot for the Bank-to-Turn Missile using Wiener-Hopf Methods (위너-호프 제어기법을 이용한 BTT 유도탄의 자동조종장치 설계)

  • Min, Deuk-Gi;Park, Ki-Heon
    • Journal of the Korean Institute of Telematics and Electronics S
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    • v.36S no.6
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    • pp.45-56
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    • 1999
  • This paper presents a method for designing an autopilot of the BTT missile using 2DOF Wiener-Hopf control technique to improve tracking performance. Linear controllers are designed based on the linearized models which are obtained from the nonlinear missile dynamic equations at various operating points. The gain scheduling technique is used to implement the final autopilot. A simulation on the flight of missiles is carried out through the use of 6DOF equation program including exact nonlinear equations of the missile and the variations of aerodynamic variables in order to check applicability of the suggested method in real situation.

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Compensation for the Body-Coupling in the 2-Gimballed Seeker Homing Loop on BTT Missile

  • Sangkeun Jeong;Kim, Eulgon;Chanho Song;Hangju Cho
    • 제어로봇시스템학회:학술대회논문집
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    • 2001.10a
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    • pp.156.1-156
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    • 2001
  • It is observed that if the 2-gimballed seeker is stabilized using rate gyros mounted along its primary axis, line of sight change measured in the seeker is induced by the rolling due to the bank-to-turn(BTT) steering as well as the actual change. This body-coupling within BTT homing includes the spurious target maneuver effect and the coupling loop due to the rate gyro misalignment. In this paper we formulates the linear BTT homing loop model with a 2-gimballed seeker including those body-coupling effects. With the model, we analyze the effects of the couplings, and show that the roll rate coupling to the rate gyro for the stabilztion of gimbal could seriously deteriorate the homing loop stability. And we propose a direct linear compensator for the coupling to recover the stability.

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Model Following flight Control System Design (준 슬라이딩 모드 제어 기법을 이용한 모델 추종 비행제어 시스템 설계)

  • Choe, Dong-Gyun;Kim, Shin;Kim, Jong-Hwan
    • Journal of Institute of Control, Robotics and Systems
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    • v.6 no.12
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    • pp.1133-1145
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    • 2000
  • In this paper a model following flight control system design using the discrete time quasi-sliding mode control method is described. The quasi-sliding mode is represented as the sliding mode band, not as the sliding surface. The quasi-sliding mode control is composed of the equivalent control for the nominal system without uncertainties and disturbances and the additive control compensating the uncertainties and disturbances. The linearized plant on the equilibrium point is used in designing a flight control system and the stability conditions are proposed for the model uncertainties. Pseudo-state feedback control which uses the model variables for the unmeasured states is proposed. The proposed method is applied to the design of the roll attitude and pitch load factor control of a bank-to-turn missile. The performance is verified through the nonlinear six degrees of freedom flight simulation.

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A Study on Polar Converting Logic of BTT Missiles (BTT 유도탄의 하중계수 분배논리 연구)

  • Lee, Yong-In;Kim, Eul-Gon
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.32 no.10
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    • pp.77-82
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    • 2004
  • This paper presents polar converting logic(PCL) of BTT missiles against slowly moving or stationary targets. A guidance commands expressed in rectangular coordinates must be converted in the form of polar coordinates for BTT control. Since conventional PCL has nonlinear and discontinuous function, the missiles may lose controllability when pitch acceleration command equals to zero. Further, roll coupling may have a serious unstabilizing influence on homing guidance with two gimbals seeker. In this paper, a linear homotopy equation is introduced to improve the controllability and a command following performance at midcourse phase. We also design a PCL which is less sensitive to pitch acceleration command so that it may improve the stability of the homing loop. To substantiate our conclusion, results of the computer simulation have been illustrated.

Investigation of the Intake Stability of Bank-to-Turn Supersonic Missile under Sideslip Angle Based on CFD Analysis (CFD 해석 기반 종축기동 초음속 비행체의 옆미끄럼각에 따른 흡입구 안정성 분석)

  • Park, Jungwoo;Park, Iksoo;Jin, Sangwook;Park, Keunhong;Hwang, Kiyoung
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.3
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    • pp.8-16
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    • 2014
  • This paper analyzes the effects of sideslip angle(SA) on the buzz margin of supersonic intake. The buzz margin is assumed to be stabilized by a controller which generates command depending only on the longitudinal sensor measurements. The analysis is performed based on three dimensional CFD results with which the sensor measurements can be simulated. In such a control system based on the longitudinal measurements, unexpected lateral flow perturbation results in the increase in the total angle of attack(TAoA), that causes the degradation of the engine intake performance. As a consequence, it is shown that the control stability is reduced such that additional control margin needs to be secured.