• Title, Summary, Keyword: Impact angle control

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Guidance Synthesis to Control Impact Angle and Time

  • Shin, Hyo-Sang;Lee, Jin-Ik;Tahk, Min-Jea
    • International Journal of Aeronautical and Space Sciences
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    • v.7 no.1
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    • pp.129-136
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    • 2006
  • A new guidance synthesis for anti-ship missiles to control impact angle and impact time is proposed in this paper. The flight vehicle is assumed as a 1st order lag system to consider more practical system. The proposed guidance synthesis enhances the survivability of anti-ship missiles because multiple anti-ship missiles with the proposed synthesis can hit the target simultaneously. The control input to satisfy constraints of zero miss distance and impact angle, and the feedforward bias control input to control impact time constitute the guidance law. The former is from trajectory shaping guidance, the latter is from neural network. And particle swarm optimization method is introduced to furnish reference input and output for learning in neural network. The performance of the proposed synthesis in the accuracy of impact time and angle is validated by numerical examples.

OPTIMAL IMPACT ANGLE CONTROL GUIDANCE LAWS AGAINST A MANEUVERING TARGET

  • RYOO, CHANG-KYUNG
    • Journal of the Korean Society for Industrial and Applied Mathematics
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    • v.19 no.3
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    • pp.235-252
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    • 2015
  • Optimal impact angle control guidance law and its variants for intercepting a maneuvering target are introduced in this paper. The linear quadratic(LQ) optimal control theory is reviewed first to setup framework of guidance law derivation, called the sweep method. As an example, the inversely weighted time-to-go energy optimal control problem to obtain the optimal impact angle control guidance law for a fixed target is solved via the sweep method. Since this optimal guidance law is not applicable for a moving target due to the angle mismatch at the impact instant, the law is modified to three different biased proportional navigation(PN) laws: the flight path angle control law, the line-of-sight(LOS) angle control law, and the relative flight path angle control law. Effectiveness of the guidance laws are verified via numerical simulations.

Definition of Impact Angle and Impact Angle Control Law Against Maneuvering Target (기동표적에 대한 입사각 정의와 입사각 제어 유도법칙)

  • Kim, Hyun-Seung;Park, Sang-Sup;Ryoo, Chang-Kyung
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.43 no.8
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    • pp.669-676
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    • 2015
  • In this paper, a guidance law for intercepting maneuvering target with a desired impact angle is proposed. The proposed guidance law is modified from the optimal impact angle control law for a fixed target and given by a biased PN law with the impact angle control term in addition to the conventional PN law. Three different kinds of desired impact angles in the respect of LOS angle, flight path angle, and relative flight path angle to the target are defined. The performance of the proposed guidance law is investigated via numerical simulations for various air-to-air engagement scenarios.

Optimal Waypoint Guidance for Unmanned Aerial Vehicles (UAVs) (무인기를 위한 최적 경로점 유도)

  • Ryoo, Chang-Kyung;Shin, Hyo-Sang;Tahk, Min-Jea
    • Journal of Institute of Control, Robotics and Systems
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    • v.11 no.3
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    • pp.240-245
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    • 2005
  • In this paper, planar waypoint guidance synthesis for UAVs using the LQ optimal impact-angle-control guidance law is proposed. We prove that the energy-optimal control problem with the constraint of passing through the waypoints is equivalent to the problem of finding the optimal pass angles on each waypoint of the optimal impact-angle-control law. The optimal pass angles can be obtained as a numerical solution of the simple pass angle optimization problem that requires neither input parameterization nor constraints. The trajectory obtained by applying the optimal impact-angle-control law with these optimal pass angles becomes energy optimal.

GUIDANCE LAW FOR IMPACT TIME AND ANGLE CONTROL WITH CONTROL COMMAND RESHAPING

  • LEE, JIN-IK
    • Journal of the Korean Society for Industrial and Applied Mathematics
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    • v.19 no.3
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    • pp.271-287
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    • 2015
  • In this article, a more generalized form of the impact time and angle control guidance law is proposed based on the linear quadratic optimal control methodology. For the purpose on controlling an additional constraint such as the impact time, we introduce an additional state variable that is defined to be the jerk (acceleration rate). Additionally, in order to provide an additional degree of freedom in choosing the guidance gains, the performance index that minimizes the control energy weighted by an arbitrary order of time-to-go is considered in this work. First, the generalized form of the impact angle control guidance law with an additional term which is used for the impact time control is derived. And then, we also determine the additional term in order to achieve the desired impact time. Through numbers of numerical simulations, we investigate the superiority of the proposed guidance law compared to previous guidance laws. In addition, a salvo attack scenario with multiple missile systems is also demonstrated.

A Study of Optimal Impact Angle Control Laws (최적 충돌각 제어법칙에 관한 연구)

  • 송택렬;신상진
    • Journal of the Korea Institute of Military Science and Technology
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    • v.1 no.1
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    • pp.211-218
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    • 1998
  • As a part of trajectory modulation to increase system survivability and terminal effectiveness, impact angle control is required in the terminal phase of tactical missile systems. The missile systems are not allowed to have high altitude to reduce probability of detection by sensors of missile defense systems. In this paper, an analytic form of a time-optimal control law is suggested in the case of constrained missile maneuverability and impact angle under the assumption of a zero-lag autopilot. The control law is obtained by establishing optimal missile-target engagement geometry in the vertical plane. Extension of the law for missiles with autopilot response lags requiring a numerical solution is studied by introducing an iterative algorithm for optimal switching time determination of which the initial switching instants are obtained from the analytic solution. Also suggested is a closed-form impact angle control law derived by an energy-optimal approach. The performances of the proposed guidance laws are evaluated by a series of computer runs.

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POLYNOMIAL FUNCTION BASED GUIDANCE FOR IMPACT ANGLE AND TIME CONTROL

  • KIM, TAE-HUN
    • Journal of the Korean Society for Industrial and Applied Mathematics
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    • v.19 no.3
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    • pp.305-325
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    • 2015
  • In this paper, missile homing guidance laws to control the impact angle and time are proposed based on the polynomial function. To derive the guidance commands, we first assume that the acceleration command profile can be represented as a polynomial function with unknown coefficients. After that, the unknown coefficients are determined to achieve the given terminal constrains. Using the determined coefficients, we can finally obtain the state feedback guidance command. The suggested approach to design the guidance laws is simple and provides the more generalized optimal solutions of the impact angle and time control guidance.

Impact Angle Control for Non-maneuvering Target with Look Angle Measurements and Line of Sight (지향각, 시선각 정보를 이용한 이동표적의 충돌각 제어)

  • Park, Jang-Seong;Lee, Dong-Hee;Park, Sang-Hyuk;Kim, Yoon-Hwan
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.47 no.7
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    • pp.508-516
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    • 2019
  • In this paper, we propose a guidance law to control Impact Angle in consideration of look angle limit of the missile with strapdown seeker on the non-maneuvering target. The proposed law is based on sliding mode algorithm and generates acceleration commands using look angle and line of sight information provided by the strapdown seeker and navigation system. And, target velocity and target path angle are provided by like TADS (Target Acquisition and Designation System) at launch time. We can confirm that the target interception and impact angle control are possible through the convergence of the proposed sliding surface. In addition, it is possible to confirm that the sign of derivative result of the look angle at the maximum and minimum look angle is opposite to the sign of the look angle, so the look angle limit is not exceeded.

Guidance Law of Missiles for Control Impact-Time-and-Angle by Flight Path Angle in Three Dimensional Space (3차원 공간에서의 비행 경로각을 이용한 비행시간 및 충돌각 제어 유도법칙)

  • Jin, Sheng-Hao;Lee, Chun-Gi;Yang, Bin;Hwan, Chung-Won;Park, Seung-Yub
    • The Journal of Advanced Navigation Technology
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    • v.16 no.1
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    • pp.8-15
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    • 2012
  • This paper on the assumption that the target is stationary and the velocity of missile is fixed value. In three dimensional space. Using flight path angle to simultaneous control impact-time-and-angle base on a homing guidance law. The independent variable in the nonlinear engagement model is the flight path angle of the missile. The propose homing guidance law can see the controllability of impact-time-and-angle. And also can see the processing of the missile arrive at the target. It is applied to several salvo attack scenarios. The performance of the proposed guidance law is verified by simulations.

Composite Guidance Law for Impact Angle Control Against Moving Targets Under Physical Constraints (이동표적 타격을 위하여 물리적 구속조건을 고려한 충돌각 제어 복합 유도법칙)

  • Park, Bong-Gyun;Kim, Tae-Hun;Kim, Youn-Hwan;Kwon, Hyuck-Hoon
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.43 no.6
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    • pp.497-506
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    • 2015
  • A composite guidance law for impact angle control against nonstationary nonmaneuvering targets is proposed. The proposed law is based on the characteristics of proportional navigation and generates two kinds of guidance commands during the homing phase. The first command is to keep the desired look angle, and the second is to attack the target with impact angle constraint. The switch of guidance phases occurs when the specific light-of-sight(LOS) angle determined from the engagement information is satisfied. The calculation method of the maximum achievable impact angle is also proposed to design easily the desired impact angle within the missile capability. Numerical simulations are performed to investigate the performance and characteristics of the proposed law.