- COMMAND LINE OF SIGHT CONTROL SYSTEMS PDF REGISTRATION
- COMMAND LINE OF SIGHT CONTROL SYSTEMS PDF OFFLINE
CLOS guidance has a further limitation of significant increase in normal and This proposed technique is based on constrained nonlinear minimization to optimize Minimize miss distance and improve accuracy of the missile in delivering the warhead, while usingĬLOS guidance. New approach has been proposed for determining the most suitable guidance gains in order to Used as noteworthy criteria for comparison of the two guidance laws. Normal and lateral accelerations and error of missile flight path from direct line-of-sight have been Miss distance, variation of angle-of-attack, Guidance and proportional navigation has been presented. Initially a comparison of command to line-of-sight Increase the effectiveness of surface to air missiles. (CLOS) guidance and proportional navigation (PN) guidance in order to reduce miss distance and to In this paper, a novel approach has been presented to integrate command to line-of-sight The superiority of the proposed globally stabilizing scheme in terms of faster convergence and improved disturbance rejection ability is demonstrated comparing performances of foremost existing solutions in case of a triple integrator chain. In both modes, the well-known extended state observer (ESO) is employed to effectively suppress the external disturbance. The proposed LMI-based state feedback law is applied thereafter (as the second mode) to bring state vector toward the origin with a fast convergence rate. In online implementation, an improved NSF law is adopted (as the first mode) to bring states within the largest invariant set.
COMMAND LINE OF SIGHT CONTROL SYSTEMS PDF OFFLINE
By offline calculations, a set of nested robust invariant attraction regions and their attributed feedback gains are computed respecting the known bound for disturbance. Then, a novel dual-mode control scheme combining an improved NSF law with a linear matrix inequality (LMI)-based model predictive controller (MPC) is developed to overcome the weaknesses of pure NSF. While nested saturated feedback (NSF) is known as the most inspiring existing solution in the literature, we shall highlight the inherent shortcomings of this approach which cause a poor performance in terms of convergence rate. This paper considers the problem of high-performance global stabilization of an integrator chain via a bounded control at the presence of input disturbance. Calculating the Cramer-Rao bound of estimation problem, the effectiveness of proposed scheme is deliberately demonstrated through simulation analyses respecting the momentous practical aspects. The formulation is developed for a typical radar-infrared tracking system, accomplished by elucidating the required points for generalization to a desirable number of heterogeneous sensors. An effective scheme that compensates for the delay with a low computation cost is introduced. The probable performance degradation due to the existence of sensors measurement delay (ignored in all similar studies) is illustrated. A modified iterated extended Kalman filter is suggested as the basis to handle the multi-rate fusion problem.
The details of coping with three common kinds of measurement, attitude, and location biases are explored concentrating on the effects of attitude bias as the main error source from the practical viewpoint.
COMMAND LINE OF SIGHT CONTROL SYSTEMS PDF REGISTRATION
The main novelty of the present work is addressing a new scheme to solve the registration problem in a distributed network along with estimating accurate target acceleration, simultaneously. On the other hand, providing satisfactory target acceleration estimation would enhance the performance of a ground-based air defense system encountering a maneuvering target.
Registration is the most consequential topic to be dealt with in a multi-sensor tracking system. The effectiveness of proposed scheme in comparison with the well‐known augmented proportional navigation law, with the absence and presence of guidance filter, autopilot dynamics and target maneuvers is illustrated through benchmark scenarios. The importance of guidance filter is highlighted in the present work employing a cubature Kalman filter. The second is related to existence of guidance filter which is assumed to be ideal in existing literature. The required conditions to insure the global stability are derived regarding this inevitable constraint. The first is related to existence of pursuer's acceleration saturation which is ignored in all existing solutions. Two momentous practical limitations are considered. Then, a nonlinear control scheme constructed from feed‐forward terms along with a nested saturated feedback strategy is suggested. With the aid of formulating problem in pursuer's line of sight frame, the exact feed‐forward acceleration commands are derived for a general target motion in three‐dimensional engagement geometry. In this paper, a novel scheme of command to line‐of‐sight guidance law regarding the outstanding practical limitations is proposed.
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