Optimality of Error Dynamics in Missile Guidance Problems

Design a Guidance Law Considering Approximation of Missile Control Loop Dynamics Using Adaptive Back-Stepping Theory

In this paper, a new guidance law is designed to improve the performance of a homing missiles guidance system in terminal phase. For this purpose first of all, the two dimensions equations of motion are formulated, then the approximation dynamic of missile control loop is added to these equations which are nonlinear whit unmatched uncertainty. Then, a new adaptive back-stepping method is develo...

Guidance Law Evaluation for Missile Guidance Systems

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...

Missile Guidance and Control Systems

The Cruise Missile Guidance Problem

In airframe technology, designs have become progressively more compact, to accommodate internal and external carriage by aircraft, launch tubes on warships or torpedo tubes in submarines. Propulsion has evolved from simple pulse jets, through turbojets and liquid propellant rockets or ramjets to the current mix of: turbojets for subsonic tactical cruise missiles, turbofans for subsonic strategi...

New Principle for Missile Guidance and Control

ted to allow efficient ballistic missiles , the paper describes a recently developed ted estimation/guidance design paradigm n several innovative concepts that provides satisfactory homing performance against ly maneuvering targets. The new paradigm veloped and tested first by using a simplified constant speed interception scenario model. paper the integrated estimation/guidance m is validated ...