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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
Three-loop autopilot design and simulation
Chu Hai-rong,Zhang Yue +1 more
TL;DR: In order to realize missile real-time change flight trajectory, three-loop autopilot is setting up as discussed by the authors, and the structure characteristics, autopilot model, and control parameters design method were researched.
Proceedings ArticleDOI
Guidance law evaluation in highly nonlinear scenarios - Comparison to linear analysis
Josef Shinar,Tal Shima +1 more
Journal ArticleDOI
Guidance Law for Near Space Interceptor based on Block Backstepping Sliding Mode and Extended State Observer
Guo Chao,Liang Xiao-Geng +1 more
TL;DR: In this paper, a novel guidance law based on the block backstepping sliding mode control and extended state observer (ESO), which also takes into account the autopilot dynamic characteristics of the near space interceptor (NSI), and the impact angle constraint of attacking the maneuvering target, was proposed.
Proceedings ArticleDOI
Integrated Guidance/Autopilot Design for Missiles With Impact Angle Constraints
TL;DR: To verify the effectiveness and rightness of the integrated design scheme, the simulation of some missile has been made, and results have shown that high accuracy of hitting target with impact angle constraints can be got.
Journal ArticleDOI
A new observer-based chattering-free sliding mode guidance law
TL;DR: In this article, a new observer-based sliding mode guidance law is proposed to intercept maneuvering targets in terminal phase, which consists of the target acceleration estimation using a new extended state observer.