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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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Fuzzy side force control for missile against hypersonic target
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TL;DR: In this paper, an integrated fuzzy-logic-based side force control mechanism is proposed for the interception of ballistic targets in three-dimensional space, where two additional auxiliary thrusters are configured to generate extra transverse acceleration and thereby reinforce the engagement performance.
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Analytical Model and Control Solutions for Unmanned Aerial Vehicle Maneuvers in a Vertical Plane
Dilmurat Azimov,John S. Allen +1 more
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Enhanced extended state observer based control for missile acceleration autopilot.
TL;DR: For the first time, this paper gives a rigorous proof of equivalent input disturbance (EID) for single-input-single-output systems and introduces the concept of EID, which enables the proposed method to handle multiple disturbances.
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A passivity perspective for the synthesis of robust terminal guidance
TL;DR: A robust guidance synthesis based on the passivity approach is applied to missiles whose flight control dynamics are modeled as linear uncertain systems with bounded uncertainties, providing passivation by feedback and feedforward control.
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Geometrical guidance algorithm for soft landing on lunar surface
TL;DR: In this paper, an existing circular guidance law developed for missile guidance is modified to be applied for the fine braking phase of lunar powered descent, and a simple compensation scheme based on comparison of actual velocity from sensors and expected velocity from the algorithm is also proposed to take care of the variation in gravity and initial mass estimate.