February 10, 2018

Advances in Missile Guidance, Control, and Estimation - download pdf or read online

By S.N. Balakrishnan, A. Tsourdos, B.A. White

ISBN-10: 1420083139

ISBN-13: 9781420083132

Stringent calls for on glossy guided weapon platforms require new methods to counsel, keep watch over, and estimation. There are specifications for pinpoint accuracy, reasonable in step with around, effortless improve paths, more advantageous functionality in counter-measure environments, and the facility to trace low-observable pursuits. Advances in Missile tips, keep watch over, and Estimation brings jointly in a single quantity the newest advancements within the 3 significant missile-control components—guidance, keep an eye on, and estimation—as good as suggestion on implementation. It additionally exhibits how those parts give a contribution to the general missile layout technique. stocks Insights from recognized Researchers and Engineers from Israel, Korea, France, Canada, the united kingdom, and the united states The booklet good points contributions through well known specialists from executive, the safeguard undefined, and academia from the U.S., Israel, Korea, Canada, France, and the uk. It begins from the floor up, constructing equations of missile movement. It stories the kinematics of the engagement and the dynamics of the objective and missile prior to delving into autopilot layout, assistance, estimation, and sensible implementation matters. Covers Nonlinear keep watch over strategies in addition to Implementation concerns The e-book discusses the layout of autopilots utilizing new nonlinear theories and analyzes the functionality over a flight envelope of Mach quantity and altitude. It additionally incorporates a bankruptcy at the fresh integrated-guidance-and-control strategy, which exploits the synergy among the autopilot and suggestions approach layout. The e-book then outlines options utilized to the missile counsel challenge, together with classical tips, sliding mode-based, and differential game-based concepts. A bankruptcy at the use of differential video games integrates the tips legislations with the estimation of the objective maneuver. A bankruptcy on particle filter out describes the most recent improvement in filtering algorithms. the ultimate chapters—written via engineers operating within the protection within the US, Israel, and Canada—consider the layout and implementation problems with a command-to-line-of-sight tips method and autopilots. a useful source at the state-of-the-art of Missile counsel A consultant to complicated themes in missile advice, regulate, and estimation, this beneficial e-book combines state of the art theoretical advancements offered in an instructional shape and distinct sensible insights. It seems to be at how monitoring, tips, and autopilot algorithms combine right into a missile approach and publications keep an eye on method designers in the course of the demanding situations of the layout procedure.

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Additional info for Advances in Missile Guidance, Control, and Estimation

Example text

1. 2. 3. 1 Missile Model Missile autopilots are usually designed using linear models of nonlinear equations of motion and aerodynamic forces and moments [25,26]. The objective of this chapter is robust design of a sideslip (yaw) velocity autopilot for a nonlinear missile model. 1). The aerodynamic parameters in this model are derived from wind-tunnel measurements [20]. 1. Here v and r are incremental forms of the sideslip velocity V and body rate R, ζ is the rudder fin deflection, yv and yζ are semi-nondimensional force derivatives due to lateral and fin angle, respectively, and nv, nζ and nr are semi-nondimensional moment derivatives due to sideslip velocity, fin angle, and body rate, respectively.

While that has given us a good insight of how robust our missile autopilot design is, it was not easily extended to redesign the controller to meet the robustness requirements and guarantee the performance under parametric uncertainty. That is one of the main contributions of this paper. 2 Robust Performance Design The pseudolinearization enables us to attain the desired level of performance through the choice of coefficients K1 and K 2. In this section, the idea is to estimate these coefficients of the pole placement controller according to the desired level of performance by using pole placement criteria.

Since Vo = v 2 + U 2 , the Mach number is a nonlinear function of the incremental sideslip velocity and longitudinal velocity, M = M (v,U). 1 can be interpreted as nonlinear functions of three variables: incremental sideslip velocity v, longitudinal velocity U, and roll angle λ. 2 Taxonomy of Models Missiles are required to operate over an expanded flight envelope to meet the challenge of highly maneuverable targets. In such a scenario, an auto­ pilot derived from linearization about a single flight condition will be unable to achieve suitable performance for the whole envelope.

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Advances in Missile Guidance, Control, and Estimation by S.N. Balakrishnan, A. Tsourdos, B.A. White


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