This Course is available in the following format:
Tactical & Strategic Missile Guidance Course Description
This two-day Tactical & Strategic Missile Guidance Training will help you understand and appreciate the unique challenges of both tactical and strategic missile guidance. So everyone can clearly understand the principles of missile guidance, concepts are derived mathematically, explained from a heuristic perspective, and illustrated with numerical examples and computer animations. Course mathematics and examples are non-intimidating. Computer source code is included so interested participants and duplicate the examples presented and explore issues beyond the scope of the course.
• We can adapt this Tactical & Strategic Missile Guidance Training course to your group’s background and work requirements at little to no added cost.
• If you are familiar with some aspects of this Tactical & Strategic Missile Guidance Training course, we can omit or shorten their discussion.
• We can adjust the emphasis placed on the various topics or build the Tactical & Strategic Missile Guidance Training course around the mix of technologies of interest to you (including technologies other than those included in this outline).
• If your background is nontechnical, we can exclude the more technical topics, include the topics that may be of special interest to you (e.g., as a manager or policy-maker), and present the Tactical & Strategic Missile Guidance Training course in manner understandable to lay audiences.
Tactical & Strategic Missile Guidance Training – Course Content:
• Numerical Techniques. Review of all numerical techniques used in the course so that all material will be easy to understand. Simulation examples, with source code.
• Fundamentals of Tactical Missile Guidance. How proportional navigation works and why it is an effective guidance law. Illustration of important closed-form solutions and their utility. Development of simplified engagement simulation and computer animation illustrating effectiveness of proportional navigation.
• Method of Adjoints and the Homing Loop. Show how to construct an adjoint and how method of adjoints are used to analyze missile guidance systems and develop system error budgets
• Noise Analysis. Illustrating computerized numerical techniques for simulating noise. Using the Monte Carlo technique for getting statistical performance projections by making many computer runs. How to use stochastic adjoints to get statistical performance projections in one computer run
• Proportional Navigation and Miss Distance. Developing useful design relationships for rapid guidance system sizing. Showing how system dynamics, acceleration saturation and radome effects limit system performance.
• Digital Noise Filters in the Homing Loop. Properties of simple digital noise filters (i.e., alpha-beta and alpha-beta gamma filters) and how they can work in a missile guidance system. How target maneuver can be estimated with range and line-of-sight information.
• Advanced Guidance Laws. Deriving optimal guidance laws without optimal control theory. How missile acceleration requirements can be relaxed with augmented proportional navigation. How to compensate for system dynamics with optimal guidance.
• Kalman Filters and the Homing Loop. Introducing the Kalman filter and showing how it is related to alpha-beta and alpha-beta gamma filters. Combining Kalman filters with optimal guidance. Showing how radome effects and time to go errors limit system performance.
• Endoatmospheric Ballistic Targets. The importance of speed, re-entry angle, and ballistic coefficient in determining the deceleration of a ballistic target. Why decelerating targets are difficult to hit and guidance laws for dealing with them.
• Extended Kalman Filtering. Performance comparisons of linear, linearized, and extended Kalman filters for estimating the ballistic coefficient of a decelerating ballistic target.
• Tactical Zones. Introduction to the rocket equation and how drag limits system performance.
• Strategic Considerations. Why the flat earth, constant gravity approximation is not appropriate for long range missiles. How Newton’s law of universal gravitation can be used and it’s impact on performance. Useful closed-form solutions for the required velocity and time of flight for strategic missiles.
• Boosters. Using the rocket equation for booster sizing and an introduction to gravity turn steering for boosters
• Lambert Guidance. Why the solution to Lambert’s problem is fundamental to steering a booster so that it will arrive at a desired location at a certain time. How to guide liquid fueled boosters with Lambert guidance and solid fueled boosters with GEM guidance.
Theater Missile Defense. Why ballistic targets are challenging- even if they don’t maneuver. How guidance laws can be developed to shape the trajectory and influence the impact angle.
Paul Zarchan has more than 40 years of experience designing, analyzing, and evaluating missile guidance systems. He has worked as Principal Engineer for Raytheon Missile Systems Division, has served as Senior Research Engineer with the Israel Ministry of Defense (Rafael), was a Principal Member of the Technical Staff for C.S. Draper Laboratory and was also a Member of the Technical Staff at MIT Lincoln Laboratory where he worked on problems related to missile defense. He is the author of Tactical and Strategic Missile Guidance, Sixth Edition, the co-author of Fundamentals of Kalman Filtering: A Practical Approach, Fourth Edition, and is an Associate Editor for the Journal of Guidance, Control and Dynamics.