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 ...

A new nonlinear sliding mode, which can be expended and used in a large family nonlinear systems , is skillfully constructed for supersonic missile control with unknown control direction. Later, by using of the Nussbaum gain method, the unknown control direction problem is solved and also the appearance of control singularity was avoided. So the nonlinear sliding mode method and Nussbaum gain m...

An adaptive controller for the avoidance of an air combat missile utilizing a guidance law unknown to the target is introduced. The controls of the aircraft are determined at discrete instants using a receding horizon control scheme providing near-optimal feedback controls of the aircraft against a closing missile. The controls are optimized with respect to the expected final distance between t...

Traditionally, missile autopilots have been designed using linear control approaches with gain scheduling. Autopilot design is typically carried out in the frequency domain and the plant is linearized around various operating points on the trajectory. Moreover, three single axis autopilots are usually designed without considering the interaction among the motion axes, i.e., the autopilots in ea...

A novel optimisation framework using an adjoint cost sensitivity calculation, and integrating computer simulations of fluid dynamics, rigid body dynamics and control is proposed. A generic tail-fin steered missile under closed-loop control is used to show that the framework is able to generate a detailed geometrical tail-fin design and tune control performance parameters that are directly relat...

Missile design is often separated into distinct subsystems such as seeker stabilization, target detection and tracking, guidance, and autopilot. The miss distance strongly depends on proper integration of those critical subsystems and the prototyping of visually guided missiles. A low-cost integrated solution based on a PC running Matlab is an attractive option to test new ideas on guidance, co...