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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
Impact angle constrained guidance for all-aspect interception with function-based finite-time sliding mode control
TL;DR: In this paper, a function-based finite-time sliding mode control methodology is introduced to design the guidance law, which achieves the desired impact angle exactly at the time of interception, and it is capable of ensuring a continuous and smooth control action.
Proceedings ArticleDOI
Guidance Law Design for Missiles with Reduced Seeker Field-Of-View
TL;DR: In this paper, a closed-form guidance law is obtained by employing the D θ − nonlinear control technique, which is designed to address the reduced seeker field-of-view constraint that is required in the low cost weapon system.
Journal ArticleDOI
Closed-form optimal cooperative guidance law against random step maneuver
Mahdi Nikusokhan,Hadi Nobahari +1 more
TL;DR: The analytical and numerical results show that OCGL is superior to the noncooperative guidance laws such as proportional navigation (PN) and optimal guidance law (OGL), even if the real model differs from the model used in the derivation of the guidance law.
Proceedings ArticleDOI
Evaluation of Two Guidance Laws for Controlling the Impact Flight Path Angle of a Naval Gun Launched Spinning Projectile
TL;DR: In this paper, two guidance laws, the Generalized Explicit (GENEX) and the Forward Integration of Terminal States (FITS), are evaluated for controlling the impact flight path angle (IFPA) of a naval five-inch gun launched GPS guided rocket assisted spinning projectile.
Journal ArticleDOI
Command-Shaping Guidance Law Based on a Gaussian Weighting Function
TL;DR: A new homing guidance law is introduced based on the energy cost weighted by a Gaussian function in order to shape the missile's trajectory and distribute the acceleration command during the engagement.