الفهرس 
Differential geometric guidance and control systems of tactical homing missiles and air defense systems
SummaryOnly 14 pages are availabe for public view
 |  | from | 140 |  |  |
| | | from | 140 | | |
Abstract
Nowadays, the homing missiles are utilized in the existed or under development air defense systems (ADS) to effectively intercept the targets. The targets became smarter and capable to fly and maneuver professionally and the tendency to design missiles with a small warhead became greater, thus there is a pressure and need to produce a more precise and accurate missile guidance system based on astute algorithms so that ensure efficiently intercept highly maneuverable targets. The concepts of differential geometric control theory provide useful tools for modelling, analysis and design the nonlinear guidance and control systems. In order to obtain better control, precise accuracy and flexibility for the intercept and engagement trajectories for homing missiles guidance and control systems, geometrical approach is used. The differential geometric guidance approach considered as a more generalized guidance algorithm, which deals with curved and straight-line trajectories as well as the linear and nonlinear systems.The missile seeker and homing tracking system including the tracking servo, uncertainty, disturbance and the possible noise are modeled and briefly considered.The intercept geometry and kinematics of the engagement for both maneuvering and non-maneuvering targets are developed and expressed in differential geometric terms. The intercept conditions are then determined using two-dimensional geometry, which is performed based on direct intercepting the targets. The unified guidance law is then developed for both cases, and it shown that, the system is globally stable using Lyapunov theory, the guidance capture is guaranteed for any initial condition. On the other hand, the analysis and design of the guidance law does not subject to any simplification or linearization, and it is shown that, the well-known proportional navigation (PN) guidance law is a subset of this approach.An optimization algorithm for the missile guidance is developed considering the missile{u2019}s necessary latax, time-to-go, and the pursuit velocity.The lateral acceleration autopilot is then designed, considering the missile dynamics and aerodynamic derivatives with a qualitative study for five different autopilot{u2019}s configurations.The thesis terminated with a 2D engagement simulation to demonstrate the convergence, properties, and features of the differential geometry approach in the homing missiles guidance and air defense systems