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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
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Proceedings ArticleDOI
Trajectory tracking and backfitting techniques against theater ballistic missiles
TL;DR: In this paper, the authors focus on track initiation and backfitting techniques, as well as extending some earlier results on tracking a TBM during boost phase cutoff, and show that Kalman techniques are superior to third order polynomial extrapolations in estimating the launch point, and that some knowledge of missile parameters, especially thrust is extremely helpful in track initiation.
Proceedings ArticleDOI
Backstepping guidance law design for missile against maneuvering targets
Abstract: A Backstepping guidance (BSG) law with saturating actuator is proposed for nonlinear kinematics of missile-target motion in the three-dimensional (3D) spherical coordinates system. The most important characteristic of Backstepping control (BSC) is high robustness. The proposed guidance law can reduce interception time and increase robustness in comparison with other guidance laws. In the proposed guidance outline, a Backstepping guidance law is designed to eliminate the effect of external perturbation. Then, it is illustrated that derived guidance law stabilize system. Some scenarios are considered for the engagement and simulated. Simulation results confirm above pretensions.
Journal ArticleDOI
Performance comparison of the notable acceleration- and angle-based guidance laws for a short-range air-to-surface missile
TL;DR: Pro proportional navigation, velocity pursuit, and augmented proportional navigation guidance laws, whose resulting guidance commands take the form of lateral acceleration, are applied to a short-range air-to-surface missile against both stationary and maneuvering ground targets.
Second Order Sliding Mode Control With Finite Time Convergence
TL;DR: In this paper, a modified form of Super Twisting algorithm is proposed to guarantee the finite time stability of nonlinear systems with matched structured uncertainty, which is able to reach to sliding surface with high precision without chattering in control signal.
Proceedings ArticleDOI
Robust zero miss distance guidance for missiles with parametric uncertainties
TL;DR: A robust guidance law is presented, which renders zero miss distance (ZMD) against deterministically or randomly maneuvering targets for all missile parametric uncertainties.