Optimal sliding mode guidance (OSMG) law is proposed for tactical missiles which is pursuing maneuvering targets in three-dimensional space. The most important characteristic of sliding mode control (SMC) is high robustness against parameter variations or external disturbances. By using a Lyapunov function, it is demonstrated that the derived guidance law can stabilize the engagement system. Al...

In missile guidance system, to reduce the interception “miss distance,” it is important to choose a suitable guidance law and navigation constant. This paper investigates and compares the system behavior of guidance laws under different navigation constants. Based on use of the adjoint technique, miss distance sensitivity analyses which consider the system noise, target step maneuver, initial h...

in this paper, a new guidance method for surface to surface ballistic missiles without mandatory engine cut-off will be presented. the complexity of solid fuel engine cut-off demands a comprehensive method for guiding these missiles. in the method presented in this paper, a certain guidance law is applied such that by transmitting appropriate commands to the control system, by changing the miss...

This paper presents a systematic approach to design a Lyapunov based super twisting differentiator. The differentiator will be shown convergent in a finite time whilst the relevant time is accurately estimated.  This differentiator is the main part to establish the sliding surface in higher order sliding mode. The differentiator  is used in the prescribed control structure  to regulate pressure...

Guidance law development for aerospace vehicles can be signi cantly simpli ed by reducing the order of the vehicle dynamic model. Identifying timescale separation in the system dynamics is important in this regard. This paper introduces a systematic means of identifying the time-scale structure in a nonlinear dynamical system by using regional Lyapunov exponents. Regional Lyapunov exponents and...

A near-optimal midcourse trajectory shaping guidance algorithm is proposed for both air and ballistic target engagement mission attributes for generic long range interceptor missile. This guidance methodology is based on the maximum final velocity as the objective function and maximum permissible flight altitude as the in-flight state constraint as well as the head-on orientation as the termina...

In this paper, a novel approach for finite-time stabilization of uncertain affine systems is proposed. In the proposed approach, a fast terminal sliding mode (FTSM) controller is designed, based on the input-output feedback linearization of the nonlinear system with considering its internal dynamics. One of the main advantages of the proposed approach is that only the outputs and external state...