In this paper we consider the problem of air to ground missile guidance system using fuzzy controller which uses Proportional Navigation and Pure Pursuit methods. The fuzzy controller’s rules are defined using Tabu Search (TS). The missile model is assumed as three degree of freedom (3DOF) (assuming the analysis in the vertical plane only). This paper presents numerical results for applying the...

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 ...

This paper presents a nonlinear observer design method for acceleration control of tail-controlled Skid-to-Turn missiles. A nonlinear observer for wind angles (angle of attack and sideslip angle) is designed using a parametric affine missile model developed by the authors. Using the estimated wind angles, a desired acceleration tracking performance can be obtained by a nonlinear control based o...

A blended autopilot algorithm is developed using generalized predictive control and adaptive non-singular terminal sliding mode control, for dual control missile steered by combination of aerodynamic fins and reaction jets. The blended algorithm considers the reaction jets control design prior due to its inherent control error, and then treats the aerodynamic fin control on the basis of the rea...

Original scientific paper In this paper, a modified guidance and control sliding mode controller (MGCSMC) method is proposed in a guided missile system. The modified sliding mode controller (MSMC) algorithm is adopted to enable the missile to reach the desired target within a short period of time. The target always makes high manoeuvres when the missile is close to it. This issue has been treat...

The Joint Kill Chain Event (JKCE), designed by the Air Force’s Distributed Mission Operations Center (DMOC), provides an interesting case study for evaluation of simulated military training. JKCE places Army Air Defense Artillery Fire Control Officers (ADAFCOs) into an Air Force Control and Reporting Center (CRC) simulator. From the CRC, the ADAFCO leads an air missile defense scenario, protect...

The traditional three-loop autopilot[11] suffers from coupling in pitch, yaws, roll channel as well as degraded performance due to huge aerodynamic uncertainties. Sliding mode control is applied to design autopilot for skid-to-turn missile (STT) missile systems to overcome the above stated difficulties. The design has two steps. The first step involves feedback linearization and the second stag...

A simple PS adaptive integral sliding mode controller is designed for the pitch channel linear model of supersonic missile firstly. In order to improve the performance of the proposed method, two improvements also proposed. Finally, a hybrid PISS adaptive control is formed which contains proportion control, integration control, the sign function adn soft function. Also nurmerical simulations ar...

Powerful nonlinear approaches for missile autopilot design have recently emerged in the literature, which have the potential to deliver improved missile performance. However, the lack of computational methods has made it difficult for the practicing engineers to exploit these techniques in routine applications. Another factor that has slowed their application is that the missile models are gene...