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Tactical and strategic missile guidance
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TLDR
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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Proceedings ArticleDOI
State estimation of spiral maneuvering target and simulation of three-dimensional intercept
TL;DR: In this article, a kalman filter is developed to estimate and extract kinetic information including the relative target-to-interceptor position, velocity and target acceleration, and the associated guidance law is used to generate the command accelerations of the interceptor using the state estimate to finish the simulation of intercept, a comparison is also made between the traditional guidance and the new one to determine the best algorithm, and my aim is to minimize the miss distance.
Proceedings ArticleDOI
NDOB-based three-dimensional guidance law with fast and finite-time convergence
Huijie Li,Yuanli Cai +1 more
TL;DR: In this paper, a three-dimensional finite-time guidance law for both nonmaneuvering and maneuvering targets is proposed for both trajectories and trajectories, where augmented functions are involved to improve the convergence of the guidance system, while the NDOBs are used to compensate the unknown target accelerations and handle the chattering problem.
Proceedings ArticleDOI
Line-of-sight rate analysis for a missile with two-axes gimbal seeker mounted on the nose cone platform
TL;DR: In this article, the Line-of-Sight (LOS) rate of a two-axes gimbal seeker mounted on the nose cone platform of a ballistic missile is derived.
Proceedings ArticleDOI
Observability-Enhancement Optimal Guidance Law
TL;DR: Under certain conditions, it is proved that the guidance law developed gradually switches from retro proportional navigation guidance to classical proportional Navigation guidance as time goes.