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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
Cooperative near-space interceptor mid-course guidance law with terminal handover constraints:
TL;DR: This paper proposes a novel finite-time cooperative mid-course guidance law with terminal handover constraints which can guarantee an ideal zero effort terminal engagement and numerical simulations of two four-interceptor cooperative scenario are carried out to verify the validity of the proposed cooperative guidance law.
Proceedings ArticleDOI
Blind Evasion by Random-Phase Periodic Maneuvers
TL;DR: The normalized miss distance expressions capture both energy management and miss distance attenuation considerations, and are shown to be a function of guidance system model order, navigation gain, and normalized maneuver frequency.
Proceedings ArticleDOI
Trajectory Estimation for a Ballistic Missile in Ballistic Phase using IR Images
TL;DR: In this article, a trajectory tracking algorithm for the ballistic missile using satellite IR image was proposed to estimate the trajectory of the missile by solving the optimization problem to find the initial value of the midcourse phase.
Proceedings ArticleDOI
Optimal Guidance-to-Collision for an Accelerating Exo-Atmospheric Interceptor Missile
Daniel Reisner,Tal Shima +1 more
TL;DR: In this paper, a guidance-to-collision law that enables imposing a required heading angle is presented, which is derived by using the optimal control methodology, and is dependent on a unique zero-effort heading angle error and also on a variable denoted as zero effort angle of attack.
Proceedings ArticleDOI
Integrated guidance and control of dual missiles considering trade-off between input usage and response speed
Hyeong-Geun Kim,H. Jin Kim +1 more
TL;DR: In this paper, an integrated guidance and control law for agile dual missiles is proposed using sliding mode control for tight integration, engagement kinematics and missile dynamics are combined without linearization, and two sliding surfaces are defined because dual missiles have two degrees of freedom for control.