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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
Integrated guidance and control system design for laser beam riding missiles with relative position constraints
Qian Peng,Jianguo Guo,Jun Zhou +2 more
TL;DR: The proposed FTDO-BLF attenuates the disturbances effectively and is robust against white noise without violating the relative position constraints.
Proceedings ArticleDOI
Improving The High Altitude Performance of Tail -Controlled Endoatmospheric Missiles
TL;DR: In this article, a new guidance law that accounts f or the airframe zeroes is developed numerically and shown to have superior performance to existing guidance laws at the higher altitude.
Journal ArticleDOI
Multiple-input describing function technique applied to design a single channel ON-OFF controller for a spinning flight vehicle:
TL;DR: In this article, the authors investigated the guidance and control problem of a single-channel spinning missile with a single ON-OFF actuator to drive a pair of control surfaces (e.g. elevato...
Journal ArticleDOI
L1 Penalized Sequential Convex Programming for Fast Trajectory Optimization: With Application to Optimal Missile Guidance
TL;DR: Proposed LPSCP method enhances overall versatility of sequential convex method for trajectory optimization, which includes ameliorated robustness toward initial trajectory estimates, and improved stability to state and constraint perturbations.