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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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Journal ArticleDOI
Proportional Navigation With Delayed Line-of-Sight Rate
TL;DR: It is observed that in the presence of line-of-sight rate delay, increasing the effective navigation constant of the PN guidance law deteriorates its performance.
Journal ArticleDOI
Unified Time-to-Go Algorithms for Proportional Navigation Class of Guidance
TL;DR: Unified time-to-go algorithms that achieve generalizations in several aspects are presented, applicable to the general class of proportional navigation guidance laws in which the navigation gain ranges from negative to positive values.
Journal ArticleDOI
Weapon-Target Assignment for Multi-to-Multi Interception With Grouping Constraint
TL;DR: To provide good engagement conditions for cooperative guidance in the case of multiple missiles against multiple targets, and meanwhile, to ensure that each target is allocated with appropriate interception resources, a fixed grouping strategy and an adaptive grouping strategy based on penalty function are proposed.
Journal ArticleDOI
Optimal Proportional-Integral Guidance With Reduced Sensitivity to Target Maneuvers
Shaoming He,Chang-Hun Lee +1 more
TL;DR: A new optimal guidance law based on the proportional-integral (PI) concept to reduce the sensitivity to unknown target maneuvers is proposed and can provide a point of connection between PI guidance laws and adaptive guidance laws.
Journal ArticleDOI
Algebraic solution of differential geometric guidance command and time delay control
LI KeBo,Chen Lei,Tang Guo-jin +2 more
TL;DR: The algebraic solution is much simpler and better for the further research of the characteristics of DGGC and the numerical simulation of intercepting a high maneuvering target is conducted to demonstrate the effectiveness of ADGGC.