• Title, Summary, Keyword: Guidance

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Design of Augmented Guidance Law Considering Geometric Pursuit Angle

  • Kim, You-Dan;Kim, Ki-Seok;Moon, Gwan-Young
    • 제어로봇시스템학회:학술대회논문집
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    • pp.125.5-125
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    • 2001
  • Until now, many guidance laws have been developed. They mainly used the classical tail-pursuit guidance method based on geometric angle information, the proportional navigation method based on the line of sight(LOS) rate, and the optimal guidance law based on optimal control theorem. In the augmented guidance law, target acceleration information and autopilot characteristics are added the guidance command. In this study, new guidance laws considering geometric angle are proposed. Two guidance laws are developed for the midcourse guidance law, and a guidance law is developed for the terminal guidance respectively. The proposed guidance laws utilize the LOS rate and the geometric angle information simultaneously. In the midcourse guidance, the guidance command is ...

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Spacecraft Guidance Algorithms for Asteroid Intercept and Rendezvous Missions

  • Hawkins, Matt;Guo, Yanning;Wie, Bong
    • International Journal of Aeronautical and Space Sciences
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    • v.13 no.2
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    • pp.154-169
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    • 2012
  • This paper presents a comprehensive review of spacecraft guidance algorithms for asteroid intercept and rendezvous missions. Classical proportional navigation (PN) guidance is reviewed first, followed by pulsed PN guidance, augmented PN guidance, predictive feedback guidance, Lambert guidance, and other guidance laws based on orbit perturbation theory. Optimal feedback guidance laws satisfying various terminal constraints are also discussed. Finally, the zero-effort-velocity (ZEV) error, analogous to the well-known zero-effort-miss (ZEM) distance, is introduced, leading to a generalized ZEM/ZEV guidance law. These various feedback guidance laws can be easily applied to real asteroid intercept and rendezvous missions. However, differing mission requirements and spacecraft capabilities will require continued research on terminal-phase guidance laws.

Considerations in Practical Advanced Guidance Law Development (실용적 첨단유도법칙 개발을 위한 고려사항)

  • 조항주
    • Journal of the Korea Institute of Military Science and Technology
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    • v.5 no.1
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    • pp.96-106
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    • 2002
  • Many modern guided weapon systems employ sophisticated target sensors as well as powerful computing systems. Due to such advanced features, they are required to achieve better guidance accuracy, and at the same time other guidance objectives for better weapon effectiveness and survivability. In this paper, we overview some of the technical considerations in such advanced guidance algorithm development, and briefly look at some related research works. More specifically, we discuss impact angle control, time-varying nature of the guidance system, time-to-go estimation, guidance loop stability, effect of autopilot lag and physical limitations in control variables, parasitic paths in guidance loops, etc. We also briefly look at some advanced concepts such as integrated guidance and control loop design, target adaptive guidance, guidance law development based on dual control concept, and terminal evasive maneuver.

Development of side attack guidance law for an underwater vehicle (수중 운동체를 위한 측면 공격 유도 기법)

  • 이보형;이장규;한형석;김병수
    • 제어로봇시스템학회:학술대회논문집
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    • pp.533-539
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    • 1993
  • In this paper, two side-attack guidance laws for an underwater vehicle are considered. In order to find the guidance command, we first make use of the optimal guidance law with terminal impact angle constraint. Secondly, the optimal solution of tracking problem is used. This paper shows some brief theory which is used in deriving the side-attack guidance laws, and the method of computing these guidance laws. Simulations on underwater vehicle for a constant moving target prove that the suggested side-attack guidance laws have enhanced side attack performance over the optimal guidance law with miss distance weighting only. Furthermore, from simulation results. we conclude that the guidance law using the optimal solution of tracking problem is more efficient for the side-attack guidance than the optimal guidance law with terminal impact angle constraint.

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A linearized curvature guidance algorithm for a passive homing missile (수동 유도 미사일 제어를 위한 선형화된 곡률 유도 알고리즘)

  • 신용준;김경근;박진배
    • 제어로봇시스템학회:학술대회논문집
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    • pp.245-248
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    • 1996
  • This paper suggests a new concept for missile guidance control, called linearized common curvature guidance law that enhances the probability to kill a target. The proposed guidance system is composed of two switching modes; one for the midcourse guidance and the other for the terminal guidance, which is switched by a specified critical value (.epsilon.). And the system and the commands are formulated and its simulations are provided in comparison with the conventional commanded line of sight guidance algorithm. Miss distance and angle of attack are denoted as performance of parameters. This new concept, common curvature guidance algorithm, revises the navigation guidance and accompanies, various considerations.

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ANALYSIS ON GENERALIZED IMPACT ANGLE CONTROL GUIDANCE LAW

  • LEE, YONG-IN
    • Journal of the Korean Society for Industrial and Applied Mathematics
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    • v.19 no.3
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    • pp.327-364
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    • 2015
  • In this paper, a generalized guidance law with an arbitrary pair of guidance coefficients for impact angle control is proposed. Under the assumptions of a stationary target and a lag-free missile with constant speed, necessary conditions for the guidance coefficients to satisfy the required terminal constraints are obtained by deriving an explicit closed-form solution. Moreover, optimality of the generalized impact-angle control guidance law is discussed. By solving an inverse optimal control problem for the guidance law, it is found that the generalized guidance law can minimize a certain quadratic performance index. Finally, analytic solutions of the generalized guidance law for a first-order lag system are investigated. By solving a third-order linear time-varying ordinary differential equation, the blowing-up phenomenon of the guidance loop as the missile approaches the target is mathematically proved. Moreover, it is found that terminal misses due to the system lag are expressed in terms of the guidance coefficients, homing geometry, and the ratio of time-to-go to system time constant.

Expected Miss Distance Concept and Its Applications to Aircraft Guidance Law for Arbitrary Flight Trajectory Tracking (기동오차 개념을 이용한 임의형상 비행궤적 추종을 위한 유도법칙에 관한 연구)

  • 민병문;노태수
    • Journal of Institute of Control, Robotics and Systems
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    • v.9 no.6
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    • pp.478-488
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    • 2003
  • A guidance scheme that is suitable for controlling the aircraft flight path is proposed. The concept of miss distance which is commonly used in the missile guidance laws, and Lyapunov stability theorem are effectively combined to obtain the aircraft's trajectory-tracking guidance law. Guidance commands are given in terms of speed and flight path angles, but they perfectly reflect any position and velocity errors between real aircraft trajectory and reference one. The proposed guidance law is easily integrated into the existing flight control system. The new guidance law was extensively tested with various mission scenarios and the fully nonlinear 6-DOF aircraft model. Furthermore, the new guidance law was compared with previous guidance schemes in nonlinear simulation. Results from the numerical simulation show that the proposed guidance law yields better performance than previous ones.

Waypoint guidance using optimal control (최적제어를 이용한 경로점 유도)

  • 황익호;황태원
    • 제어로봇시스템학회:학술대회논문집
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    • pp.1867-1870
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    • 1997
  • Waypoint guidance is a technique used to steer an autonomous vehicle along a desired trajectory. In this paper, a waypoint guidance algorithm for horizontal plane is derived by combining a line following guidance law and a turning guidance law. The line following guidance is derived based on LQR while the turning guidance is designed using rendzvous problem. Through simulation, the proposed method shows a good performance.

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A TUTORIAL ON LINEAR QUADRATIC OPTIMAL GUIDANCE FOR MISSILE APPLICATIONS

  • TAHK, MIN-JEA
    • Journal of the Korean Society for Industrial and Applied Mathematics
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    • v.19 no.3
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    • pp.217-234
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    • 2015
  • In this tutorial the theoretical background of LQ optimal guidance is reviewed, starting from calculus of variations. LQ optimal control is then introduced and applied to missile guidance to obtain the basic form of LQ optimal guidance laws. Extension of LQ optimal guidance methodology for handling weighted cost function, dynamic lag associated with the missile dynamics and the autopilot, constrained impact angle, and constrained impact time is also described with a brief discussion on the asymptotic properties of the optimal guidance laws. Furthermore, an introduction to polynomial guidance and generalized impactangle-control guidance, which are closed related with LQ optimal guidance, is provided to demonstrate the current status of missile guidance techniques.

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.