نتایج جستجو برای: finite time guidance law

تعداد نتایج: 2281944  

Journal: :IEEE Transactions on Aerospace and Electronic Systems 2020

Based on the idea of Continuous Fuzzy Guidance Law (CFGL), a andldquo;three-phase fuzzy guidanceandrdquo; (TFG) law is proposed for the class of surface to air homing missiles. The current approach enables the guidance law to track a maneuvering target from the beginning of the launch phase up to the terminal one while itdynamically attempts to keep miss-distance, flight time and control effort...

2016
V. Behnamgol A. Vali A. Mohammadi

In this paper, a new procedure for designing the guidance law considering the control loop dynamics is proposed. The nonlinear guidance loop entailing a first order lag as the control loop dynamics is formulated. A new finite time and smooth backstepping sliding mode control scheme is used to guarantee the finite time convergence of relative lateral velocity. Also in the proposed algorithm the ...

Journal: :IEEE Transactions on Aerospace and Electronic Systems 2017

2007
Chang-Kyung Ryoo Yoon-Hwan Kim Min-Jea Tahk Keeyoung Choi

In this paper, we propose a nonlinear guidance law for missiles against maneuvering targets. First, we derive the equations of motion described in the line-of-sight reference frame and then we define the equilibrium subspace of the nonlinear system to guarantee target interception within a finite time. Using Sontag’s formula, we derive a nonlinear guidance law that always delivers the state to ...

Journal: :Xibei gongye daxue xuebao 2023

For cooperative mid-course guidance problem of multiple unmanned target drone aircrafts(UTDA), a novel law with impact angle constraints is proposed in this study. Firstly, the relative motion equation UTDAs and target, multiple-UTDA model are constructed. Then, process design divided into two stages. In first stage, acceleration command on LOS direction designed based fixed-time consensus theo...

J. Karimi, M. Shadoud

An advanced guidance law is developed for reentry phase of a reentry vehicle. It can achieve small miss distance and desired impact attitude angle, simultanceously. To meet this requirment a guidance law based on the fuzzy logic approach is developed. It is partitioned into three stages. This guidance law does not require linearization of missile engagement model. Line-of-sight and flight path ...

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