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 ...

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...

The application of fuzzy logic for the development of guidance laws for homing missiles is presented. Fuzzy logic approximation of the well known proportional navigation guidance law is discussed, followed by the development of a blended guidance law using fuzzy logic. The objective of the latter guidance law is to combine desirable features of three homing guidance laws to enhance the intercep...

In this paper we consider the problem of air to ground missile guidance system using fuzzy controller. The missile model is assumed as three degree of freedom (3DOF) (assuming the analysis in the vertical plane only).The homing guidance method is used. This paper presents numerical results for applying the fuzzy controller to the missile in different situations of control parameters in differen...

Guidance of unmanned aerial vehicle (UAV) in three-dimensional space was studied in this paper. We designed a three-dimensional fuzzy neural network guidance law with the fuzzy rules of Takagi-Sugeno that based on proportional guidance principle and put the characteristics of the fuzzy neural network control into use. We decomposed the 3-D tracking trajectory into two two-dimensional planes and...

An integrated fuzzy guidance (IFG) law for a surface to air homing missile is introduced. The introduced approach is a modification of the well-known proportional navigation guidance (PNG) law. The IFG law enables the missile to approach a high maneuvering target while trying to minimize control effort as well as miss-distance in a two-stage flight. In the first stage, while the missile is far ...

driver’s requirement in route guidance system Caixia Li , Sreenatha Gopalarao Anavatti, Tapabrata Ray University of New South Wales @ Australian Defence Force Academy [email protected] Abstract-Route choice mechanism is the key technology of the route guidance system. This paper focuses on the integration of the analytical hierarchy process (AHP) and fuzzy logic theory to realize th...

A fuzzy predictive pursuit guidance is proposed as an alternative to the conventional methods. The purpose of this scheme is to obtain a stable and fast guidance. The noise effects must be reduced in homing missile guidance to get an accurate control. An aerodynamic missile model is simulated first and a fuzzy predictive pursuit control algorithm is applied to reduce the noise effects. The perf...

A fuzzy logic-based guidance design for longer engagement in time and beneficial interception attitudes is investigated and proposed here. The integrated fuzzy logic-based guidance scheme consisting of vertical, midcourse and terminal guidance phases can intercept the target from diverse aspects. The engagement strategy in the vertical guidance phase includes general vertical launch to handle t...