• Title/Summary/Keyword: Guidance and control

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A Shelter Guidance System using the PLC Communication (PLC 통신을 이용한 피난구 유도장치 시스템)

  • Lee, Chang-Young;Lee, Kyu-Yun;Lee, Hyun-Kwan;Kim, In-Kook;Eom, Ki-Hwan
    • Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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    • v.9 no.1
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    • pp.583-586
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    • 2005
  • We propose a shelter guidance system using the PLC communication to resolve that a conventional shelter guidance light for underground space has problems. The proposed shelter guidance system is composed of a main control part, a PLC remote control part, a charging part, a sound generation part, a display part, an alarm part and a smoke sensing part.. The efficacy of the proposed system is verified by means of experimental. Experimental results are presented that show the effectiveness and the improvement of noise.

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Design and Control of Levitation and Guidance Systems for a Semi-High-Speed Maglev Train

  • Kim, Min;Jeong, Jae-Hoon;Lim, Jaewon;Kim, Chang-Hyun;Won, Mooncheol
    • Journal of Electrical Engineering and Technology
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    • v.12 no.1
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    • pp.117-125
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    • 2017
  • Research on Maglev (Magnetic Levitation) train is currently being conducted in Korea, concerning Urban Transit (110 km/h of maximum speed), semi-high-speed (200 km/h of maximum speed), and high-speed (550 km/h of maximum speed) trains. This paper presents a research study on the levitation and guidance systems for the Korean semi-high-speed maglev train. A levitation electromagnet was designed, and the need for a separate guidance system was analyzed. A guidance electromagnet to control the lateral displacement of the train and ensure its stable operation was then also designed, and its characteristics were analyzed. The dynamic performance of the designed levitation and guidance electromagnets was modeled and analyzed, using a linearized modeling of the system equations of motion. Lastly, a test setup was prepared, including manufactured prototypes of the designed system, and the validity of the design was verified and examined with performance evaluation tests.

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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A study on integrated guidance scheme for guided weapon system (유도무기를 위한 통합된 유도기법에 관한 연구)

  • 김병수;한형석;이장규;박성희;이재명;김삼수
    • 제어로봇시스템학회:학술대회논문집
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    • 1992.10a
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    • pp.590-595
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    • 1992
  • An integrated guidance scheme for guided weapon system is described in this paper. Against conventional guidance methods, this method combines an autopilot and a guidance law. The controller is designed using LQ regulator whose performance index is different from other optimal guidance laws. Since dynamics of the system is considered in the derivation, the controller performance is improved. By simulation, the suggested method shows better performance in minimum distance sense than conventional guidance schemes such as Bang Bang guidance or Pursuit Guidance. Since the suggested method provides smooth rudder deflection in contrast to the conventional method, the load on a energy source of the system can be greatly lessened.

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Reference Trajectory Optimization of a Launch Vehicle M-3H-3 for Scientific Missions (과학위성 발사체 M-3H-3의 기준궤적 최적화)

  • Lee, Seung-H.;Choi, Jae-W.;Lee, Jang-G.
    • Proceedings of the KIEE Conference
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    • 1991.11a
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    • pp.361-365
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    • 1991
  • The problem being considered here is the determination of optimal guidance laws for a launch vehicle for scientific missions. The optimal guidance commands are determined in the sense that the least amount of fuel is used. A numerical solution was obtained for the case where the position and velocity state variables satisfy a specified constraint at the time of thrust cutoff. The method used here is based on the Pontryagin's maximum principle. This is the method of solving a problem in the calculus of variations. In particular, it applies to the problem considered here where the magnitude of the control is bounded. Simulations for the optimal guidance algorithm, during the 2nd and the 3rd-stage flight of the Japanese rocket M-3H-3, are carried out. The results show that the guided trajectory that satisfying the terminal constraints is optimal, and the guidance algorithm works well in the presence of some errors during the 1st-stage pre-programmed guidance phase.

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Guidance Law to Control Impact-Time-And-Angle Using Time-Varying Gains (시변 이득을 이용한 비행시간 및 충돌각 제어 유도법칙)

  • Lee, Jin-Ik;Jeon, In-Soo
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.35 no.7
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    • pp.633-639
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    • 2007
  • This paper presents a new homing guidance law based on well-known BPN to achieve an impact time constraint as well as an impact angle constraint. The guidance commands are synthesized by introducing an additional command to control impact-time. The structure of the additional command has a BPN-based loop multiplied by time-varying gains being proportional to the time difference between the required time-to-go and the estimated time-to-go by BPN. Moreover, the proposed homing loop converges to BPN as the time-to-go error is reduced. The performance of the proposed guidance law is evaluated by the computer simulations.

Multi-level DVS Guidance and Output-feedback Path-following Control for Marine Surface Vehicles

  • Deng, Ying-Jie;Im, Nam-kyun
    • Proceedings of the Korean Institute of Navigation and Port Research Conference
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    • 2018.11a
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    • pp.256-257
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    • 2018
  • This paper deals with the path-following control for marine surface vehicles with underactuated characteristics. In consideration of practical limitations of actuators, an improved DVS(dynamic virtual ship) guidance algorithm is proposed with the multi-level DVS optionally selected to be tracked. To address the output-feedback control issue, an adaptive FLS(fuzzy logical systems) is devised to online approximate the kinematic states. Based on that observing framework, the path-following control law is thereafter derived. Simulations testify effectiveness of the proposed scheme

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Earliest Intercept Geometry Guidance to Improve Mid-Course Guidance in Area Air-Defence

  • Shin, Hyo-Sang;Tahk, Min-Jea;Tsourdos, A.;White, B.A.
    • International Journal of Aeronautical and Space Sciences
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    • v.11 no.2
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    • pp.118-125
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    • 2010
  • This paper describes a mid-course guidance strategy based on the earliest intercept geometry (EIG) guidance. An analytical solution and performance validation will be addressed for generalized mid-course guidance problems in area air-defence in order to improve reachability and performance. The EIG is generated for a wide range of possible manoeuvres of the challenging missile based on the guidance algorithm using differential geometry concepts. The main idea is that a mid-course guidance law can defend the area as long as it assures that the depending area and objects are always within the defended area defined by EIG. The velocity of Intercept Point in EIG is analytically derived to control the Intercept Geometry and the defended area. The proposed method can be applied in deciding a missile launch window and launch point for the launch phase.

Nonlinear Formation Guidance Law with Robust Disturbance Observer

  • Shin, Hyo-Sang;Kim, Tae-Hun;Tahk, Min-Jea;Hwang, Tae-Won
    • International Journal of Aeronautical and Space Sciences
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    • v.10 no.1
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    • pp.30-36
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    • 2009
  • Many formation guidance laws have been proposed for VAV formation flight. Since most autonomous formation flight methods require various active communication links between the vehicles to know motion information of other vehicles, damage to the receiver or the transmitter and communication delay are critical problem to achieve a given formation flight mission. Therefore, in this point of view, the method that does not need an inter-vehicle communication is preferred in the autonomous formation flight. In this paper, we first summarize the formation guidance law without an inter-vehicle communication using feedback linearization and sliding mode control proposed in previous study. We also propose the modified formation guidance law with robust disturbance observer, which can provide significantly better performance than previously mentioned guidance law in case that other vehicles maneuver with large accelerations. The robust disturbance observer can estimate uncertainties generated by acceleration of leader vehicle. By eliminating the uncertainties using the estimated uncertainties, VAVs are able to achieve the tight formation flight. The performance of the proposed approach is validated by numerical simulations.

Aircraft Collision-Avoidance/Guidance Strategy in Dynamic Environments for Planar Flight (2차원 평면에서 이동장애물에 대한 항공기의 유도/회피기동 연구)

  • Rhee, Ihn-Seok
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.32 no.7
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    • pp.69-75
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    • 2004
  • An avoidance/guidance problem of an aircraft against moving obstacle is considered in two dimensional space. The aircraft is modelled as a point mass flying with constant speed. The lateral acceleration is assumed the control input. Artificial potential functions are applied to the terminal point and moving obstacles in order that repulsive forces and an attractive force are produced by the obstacles and the terminal point respectively. A real time guidance/avoidance law is proposed by using the potential forces and relative velocity. The guidance law for a logarithm potential function results the well-known proportional navigation law. The avoidance control command is inverse proportional to the time-to-go to the obstacle and turns the aircraft toward the negative direction of the line-of-sight change. The performance of the proposed guidance/avoidance law is verified with simulations.