The performance of the algorithm is verified by simulating the tracking of a highly maneuvering target, the results show that: the target can be tracked effectively with the method presented and the accuracy of the tracking is satisfied.

The performance of the algorithm is verified by simulating the tracking five highly maneuvering targets,the results show that the new algorithm can reduce the number of tracks and computation time,also has the more capability to restrain noises.

(4) A new algorithm, adaptive fuzzy α—β—γ filter, is presented for tracking the high flexible object. The feature of adaptive fuzzy α—β—γ filter is analyzed at the various flexible tacks and various noises.

It is a challengeable problem to track maneuvering targets,especially tracking the high speed and high maneuvering targets,which has both theoretically and practically technical difficulties.

To guarantee capture of an engagement in terminal phase, the nonlinear systems geometry theory are used to design command accelerations of a nonlinear terminal guidance system model for an air to air missile attacking evasive target.

Some simulations were conducted to track a highly maneuvering target in a cluttered environment using two sensors.

The interception scenario of a highly maneuvering target is formulated as a zero-sum pursuitevasion game.

Conventional Proportional Navigation (Pro. Nav.) for tactical missiles is simple, requires minimal computation and therefore is easy to implement. It is, however, not effective against high speed or maneuvering targets. Numerous studies have been made to improve the performance of Pro. Nay. [2,5,7]. The optimal controllers derived in these studies, as compared to Pro. Nay. with a constant navigation ratio, either change the constant ratio to time-varying ones [1,8], or introduce target acceleration into guidance...

Conventional Proportional Navigation (Pro. Nav.) for tactical missiles is simple, requires minimal computation and therefore is easy to implement. It is, however, not effective against high speed or maneuvering targets. Numerous studies have been made to improve the performance of Pro. Nay. [2,5,7]. The optimal controllers derived in these studies, as compared to Pro. Nay. with a constant navigation ratio, either change the constant ratio to time-varying ones [1,8], or introduce target acceleration into guidance laws [4]. Although these modified Pro. Nav. laws have higher accuracy than the original one, they all require bigger missile control power. Furthermore, the authors have not found any report in open literature which investigates the dynamic and static performances of guidance systems (i.e. the interaction between guidance lairs and guidance systems). This paper's main contribution is that an optimal PID type guidance approach is presented; it has higher accuracy, requires lower missile control power than Pro. Nay. and can improve the dynamic and static performances of guidance systems. The optimal controllers obtained by the minimization of generalized line of sight angle error can guarantee quasi-constant-bearing-course. Suboptimality will be attained with linear controllers which are PID type Pro. Nav., but have different structure from those in ref. [3]. Theoretical studies demonstrate that PID type Pro. Nay. also possesses better robustness against the perturbations of guidancc law parameters and missile autopilot parameters than Pro. Nav. Simulation results substantiate the above deductions.

In this paper, the trends of solid rocket propulsion technology are discussed. It isnecessary that the intercontinental missiles be made small scale and are launched on anautomobile, a train or a plane. So the main trend of SRM for intercontinental missile isto improve performance of SRM. In order to make anti-aircraft missiles tackle the high-speed, high-maneuverable target, and to hide the missile site and missile itself, the maintrend of SRM for anti-aircraft missiles is to develop the technology of controlled...

In this paper, the trends of solid rocket propulsion technology are discussed. It isnecessary that the intercontinental missiles be made small scale and are launched on anautomobile, a train or a plane. So the main trend of SRM for intercontinental missile isto improve performance of SRM. In order to make anti-aircraft missiles tackle the high-speed, high-maneuverable target, and to hide the missile site and missile itself, the maintrend of SRM for anti-aircraft missiles is to develop the technology of controlled thrustand smokeless propellants. The main trends of boosters for launch vehicles and SRM forsmall launch vehicles are lower cost and higher reliability. In addition, it is also an im-portant tendency that the technology of SRM is applied to economical construction.

PN(proportional navigation) law is in wide use. After a great deal of careful research, we decided to make PN law a variable structure one in order to make it less difficult to implement while satisfying two stringent requirements: (1) the IR(infrared) homing airtoair missile should be effective against highly maneuverable targets; (2) even large offboresight angle launching can be effective. When implementing ordinary PN law, the assumption of small offboresight angle launching is usually made. The implementation...

PN(proportional navigation) law is in wide use. After a great deal of careful research, we decided to make PN law a variable structure one in order to make it less difficult to implement while satisfying two stringent requirements: (1) the IR(infrared) homing airtoair missile should be effective against highly maneuverable targets; (2) even large offboresight angle launching can be effective. When implementing ordinary PN law, the assumption of small offboresight angle launching is usually made. The implementation of our variable structure PN law has no need of such assumption. In our research we considered target normal acceleration, related to target maneuverability, to be bounded disturbance. We utilized variable structure control to overcome such disturbance by making dq/dt, lineofsight rate, approach zero in a limited time. We derived eq.(10) as the model of our variable structure PN law. Simulation results are presented in Fig.2(a). Fullline curve shows the variation of dq/dt with time for PN law; dottedline curve shows the variation of dq/dt with time for variable structure PN law(dq/dt indistinguishable from zero after only about one second for our numerical xample). The comparison shows that highperformance of IR homing missile appears to be attainable with variable structure PN law. Our method is simple and requires no signals additional to dq/dt; thus it is less difficult to implement.