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Tactical and strategic missile guidance
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In this paper, a three-loop Autopilot is used to provide tactical and strategic guidance for a single-antenna MIMO-BMG system using MATLAB units.Abstract:
Numerical Techniques Fundamentals of Tactical Missile Guidance Method of Adjoints and the Homing Loop Noise Analysis Convariance Analysis and the Homing Loop Proportional Navigation and Miss Distance Digital Fading Memory Noise Filters in the Homing Loop Advanced Guidance Laws Kalman Filters and the Homing Loop Other Forms of Tactical Guidance Tactical Zones Strategic Considerations Boosters Lambert Guidance Strategic Intercepts Miscellaneous Topics Ballistic Target Properties Extended Kalman Filtering and Ballistic Coefficient Estimation Ballistic Target Challenges Multiple Targets Weaving Targets Representing Missile Airframe with Transfer Functions Introduction to Flight Control Design Three-Loop Autopilot. Appendices: Tactical and Strategic Missile Guidance Software Converting Programmes to C Converting Programmes to MATLAB Units.read more
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Journal ArticleDOI
Linear Quadratic Guidance Laws for Imposing a Terminal Intercept Angle
Vitaly Shaferman,Tal Shima +1 more
TL;DR: In this article, the authors derived linear quadratic guidance laws that explicitly enable imposing a predetermined intercept angle for arbitrary-order linear missile dynamics, which are dependent on the well-known zero-effort miss distance and on a new variable denoted zeroeffort angle.
Journal ArticleDOI
Indirect Impact-Angle-Control Against Stationary Targets Using Biased Pure Proportional Navigation
Journal ArticleDOI
Design of Missile Guidance Law via Variable Structure Control
TL;DR: In this article, a variable structure control (VSC) based guidance law was proposed, where the acceleration command input is determined considering the target acceleration as an uncertainty, and the proposed guidance law uses only the information for the estimated target acceleration bound.
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Optimal Cooperative Pursuit and Evasion Strategies Against a Homing Missile
TL;DR: It is shown how the target can lure in the attacker, allowing its defender to intercept the attacking missile even in scenarios in which the defender's maneuverability is at a disadvantage compared with the attacking ballistic missile.
Journal ArticleDOI
Nonsingular Sliding Mode Guidance for Impact Time Control
TL;DR: In this paper, a guidance problem for impact time control applicable to salvo attacks is considered based on the sliding mode control, and a positive continuous nonlinear function of the lead angle is introduced to the guidance command, which makes the Lyapunov stability negative semidefinite.