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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
Citations
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Journal ArticleDOI
Field-of-View and Impact Angle Constrained Guidance Law for Missiles With Time-Varying Velocities
Bojun Liu,Mingshan Hou,Yajun Li +2 more
TL;DR: A novel nonlinear non-switching guidance strategy is proposed for missiles with time-varying velocities intercepting stationary targets, considering impact angle, seeker’s field-of-view, and input saturation constraints, simultaneously.
Journal ArticleDOI
Intercept Guidance for Cooperative Aircraft Defense against a Guided Missile
TL;DR: In this paper, a novel guidance law for the missile-to-missile intercept is developed using two lines of sight: one line of sight is constructed from the protected aircraft to the threat missile, and the other is from the protecting aircraft to a threat missile.
Proceedings ArticleDOI
New Logic-Based Estimation/Guidance Algorithm for Improved Homing Against Randomly Maneuvering Targets
TL;DR: In this article, a new, logic-based estimation/guidance algorithm that explicitly uses the time-to-go in the estimation process is presented. But the accuracy of the new approach is limited.
Proceedings ArticleDOI
Exo-atmospheric intercept using modified proportional guidance with gravity correction for coast phase
TL;DR: In this paper, the authors developed a form of proportional oavigation for exoatmospheric guidance in which the coast phase must be considered, which is equivalent to applying a variable bias to the actual line-of-sight (L.0S) rate during hum.
Journal ArticleDOI
Robust Control Algorithm for a Rotorcraft Disturbed by Crosswind
TL;DR: A nonlinear stabilization of vertical take-off and landing aircrafts exposed to wind is presented and is based on a robust control Lyapunov function approach and rejects disturbances without knowledge of them.