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Missile

About: Missile is a research topic. Over the lifetime, 12829 publications have been published within this topic receiving 94307 citations. The topic is also known as: guided missile & missiles.


Papers
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Journal ArticleDOI
TL;DR: In this paper, a novel method of adaptive nonsingular terminal sliding mode control is proposed for a class of nonlinear systems subject to disturbances and uncertainties, which is applied to integrated guidance and control design for a missile.
Abstract: A novel method of adaptive nonsingular terminal sliding mode control is proposed for a class of nonlinear systems subject to disturbances and uncertainties. The obtained results are applied to integrated guidance and control design for a missile. Using the Lyapunov stability theory, it is shown that the finite time convergence in both reaching and sliding phase is achieved by virtue of a terminal sliding surface and a switching controller that avoids singularity. With the assumption that the disturbances and uncertainties are bounded and the bounds are unknown, the adaptive method is incorporated with the controller design, which makes the proposed adaptive nonsingular terminal sliding mode control with better robustness. Due to the inherent property of time-scale separation between the translational and rotational dynamics, partial integrated guidance and control with a two-loop controller structure is designed for a missile based on the proposed adaptive nonsingular terminal sliding mode control. The ou...

79 citations

Book
29 Mar 2011
TL;DR: In this paper, the authors present an analysis of the performance of the generalized guidance laws in time domain inertialess PN Guidance System with a three-dimensional engagement model.
Abstract: Basics of Guidance Guidance Process Missile Guidance Guidance of Cruise Missiles and UAVs Representation of Motion Line-of-Sight Longitudinal and Lateral Motions Control of Lateral Motion Parallel Navigation Proportional Navigation: Planar Engagement Proportional Navigation: Three-Dimensional Engagement Augmented Proportional Navigation Proportional Navigation as a Control Problem Augmented Proportional Navigation as a Control Problem When Is the PN law Optimal? Control of Longitudinal and Lateral Motions Guidance Correction Controls Lyapunov Approach to Control Law Design Bellman-Lyapunov Approach: Optimal Guidance Parameters Modified Linear Planar Model of Engagement General Planar Case Three-Dimensional Engagement Model Generalized Guidance Laws Modifies Generalized Guidance Laws Examples Analysis of Proportional Navigation Guided Systems in Time Domain Inertialess PN Guidance System Method of Adjoints Analysis of Proportional Navigation Guided Systems in the Frequency Domain Adjoint Method: Generalized Model Frequency Domain Analysis Steady-State Miss Analysis Weave Maneuver Analysis Example Frequency Analysis and Miss Step Response Bounded Input-Bounded Output Stability Frequency Response of the Generalized Guidance Model Design of Guidance Laws Implementing Parallel Navigation: Frequency-Domain Approach Neoclassical Missile Guidance Pseudoclassical Missile Guidance Example Systems Guidance Law Performance Analysis Under Stochastic Inputs Brief Discussion of Stochastic Processes Random Target Maneuvers Analysis of Influence of Noises on Miss Distance Effect of Random Target Maneuvers on Miss Distance Computational Aspects Examples Filtering Guidance of UAVs Basic Guidance Laws and Vision-Based Navigation Generalized Guidance Laws for UAVs Guidance of a Swarm of UAVs Obstacle Avoidance Algorithms Testing Guidance Laws Performance Forces Acting on Unmanned Aerial Vehicles Reference Systems and Transformations Unmanned Aerial Vehicles Dynamics Autopilot and Actuator Model Seeker Model Filtering and Estimation Kappa Guidance Lambert Guidance Simulation Models of Unmanned Aerial Vehicles Integrated Design Integrated Guidance and Control Model Synthesis of Control Laws Integration and Decomposition Guidance Laws for Boost-Phase Interceptors Launched from UAVs Kill Vehicles for Boost-Phase Defense Development of the Missile Model and Selection of Guidance Law Parameters Endgame Requirements and the Comparative Analysis of Efficiency of Guidance Laws Advanced Guidance Laws Applied to Boost Stage Interceptor's Performance With Axial Control Comparative Analysis with Lambert Guidance Appendices

79 citations

Proceedings ArticleDOI
07 Apr 1999
TL;DR: In this article, an AF atmospheric computer program called PLEXUS is applied to the UV spectral region to obtain the atmospheric transmission along paths extending from the upper atmosphere to the lower atmosphere.
Abstract: The vulnerability of aircraft to missile attacks is briefly sketched. Aircraft and helicopter defensive electronic self- protection systems against missile attacks including passive and active radar and IR countermeasures are summarized. Radar and IR missile threat warnings are outlined. The development of UV missile threat warning is recounted. UV missile warning coverage is defined. UV missile plume photon emission is addressed. Solar UV emission and atmospheric transmission is reviewed. An AF atmospheric computer program called PLEXUS is applied to the UV spectral region to obtain the atmospheric transmission along paths extending from the upper atmosphere to the lower atmosphere. These atmospheric transmission numbers are used to evaluate the number of solar photons propagating through the upper atmosphere to lower tactical altitudes and into a UV missile-warning sensor viewing the sun directly. These numerical evaluations are accomplished in one- nanometer wide wavelength bins. The results are presented in a number of figures, which then serve to define the solar blind UV region. Detector spectral development objectives are then presented based on the results shown in the figures.

79 citations

Journal ArticleDOI
G.E. Forden1
TL;DR: The Airborne Laser (ABL), a high-flying megawatt laser that pinpoints a ballistic missile lifting off hundreds of kilometers away, is an alternative to terminal defenses.
Abstract: The Airborne Laser (ABL), a high-flying megawatt laser that pinpoints a ballistic missile lifting off hundreds of kilometers away, is an alternative to terminal defenses. The utility of the ABL in future regional conflicts, and the consequent policy options the United States can exercise, will be highly dependent on its range. The ABL's range in turn is determined by the accuracy with which the primary laser beam can be pointed, the power density it can deliver, and the structural design of the missile being attacked. This paper's examination of these issues, including all the estimates of the ABL's capabilities, are from the author's own analyses. The findings combine information found in the open literature with the basic physics and engineering involved in propagating intense laser beams through the atmosphere.

79 citations

Proceedings ArticleDOI
23 Jun 2003
TL;DR: In this paper, a generalized formulation of optimal guidance laws for constant speed missiles with a higher order system dynamics is presented, which can be represented by a linear combination of a step and a ramp acceleration response of the missile.
Abstract: Optimal guidance laws and their closed-form solutions for controlling the impact angle as well as terminal miss are investigated in this paper. Generalized formulation of optimal guidance laws for constant speed missiles with a higher order system dynamics can be represented by a linear combination of a step and a ramp acceleration response of the missile. In the case of lag-free system, optimal guidance command is linear time varying and, therefore, the entire missile states can be expressed by polynomial functions in terms of time-to-go. We also proposed practical and precise time-to-go calculation methods in consideration of curved missile trajectory, which can be applied for various impact angle controllers. Basic properties including error analyses for the optimal guidance law for lag-free system are shown by numerical examples.

78 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
20241
2023270
2022639
2021202
2020352
2019451