Simulations indicate that the guidance system employing PI guidance law can achieve smaller miss distance for maneuverable targets, especially for highly maneuverable targets, than that with PN guidance law.

The result shows that the evaluation model of lethal effect for air to air missiles comprehensively considering characteristics,miss distance and vulnerability of target aircrafts,accords with reality.

In comparison with the results obtained by direct integration oftrajectory equations the method described in this paper gives a relationerror on miss distance of less than 2% and an absolute error of about30 meters.

It is shown that the interceptor can guarantee an arbitrarily small miss distance without exceeding the control constraints if it has sufficient maneuverability and if the penalty coefficients are chosen properly.

Having a resource of impulse control, the pursuer tries to minimize the miss distance.

The implementation scheme and the effect on miss distance due to errors in guidance are discussed.

Necessary conditions and sufficient conditions are employed to deduce optimal strategies for a simple differential game with state equationd2x/dt2=au+v,a = Const, |u|≤1, |v|≤1, fixed transfer time, and terminal miss distance as payoff.

Initial orbital parameter errors are used to examine the miss distance between a spacecraft and an ensemble of tracked objects by a Monte Carlo-type analysis.

This paper describes guidance problems of the high altitude interception with emphasis on the most effective use of the maneuverability of the interceptors.The method of treatment is based on the so-called predicfive miss distance conception to establish equations of the predictive miss distance, and to invert the guidance problem of the interception into the control problem of the final point miss distance. Application of the principle of the minimum to this simplified equivalent problem gives...

This paper describes guidance problems of the high altitude interception with emphasis on the most effective use of the maneuverability of the interceptors.The method of treatment is based on the so-called predicfive miss distance conception to establish equations of the predictive miss distance, and to invert the guidance problem of the interception into the control problem of the final point miss distance. Application of the principle of the minimum to this simplified equivalent problem gives straightforward the analytical formula of the guidance law. The advantage of this method is clear and simple for the mathematical treatment.This paper discusses two guidance laws for minimum, effort interception and minimum time interception, Moreover the determination of the interception time tp is also presented. The result obtained can be applied to the radio command guidance, and with some modification, could be applied to the terminal homing guidance too.

The problem of optimal intercept guidance laws for missiles have been studied by a lot of authors at home and abroad. But the mathematical models for missiles were assumed too simple, i. e. either as an ideal particle or as a first order delay link.As a primary contribution this paper has made researches on the optimal intercept guidance laws based on a mathematical model with second order charac- teristics. By taking minimum control energy consumption as the performance index, the optimal intercept guidance...

The problem of optimal intercept guidance laws for missiles have been studied by a lot of authors at home and abroad. But the mathematical models for missiles were assumed too simple, i. e. either as an ideal particle or as a first order delay link.As a primary contribution this paper has made researches on the optimal intercept guidance laws based on a mathematical model with second order charac- teristics. By taking minimum control energy consumption as the performance index, the optimal intercept guidance laws have been derived from the minimum principle in the following two cases of terminal state:1. The terminal miss-distance is zero;2. The intercepting curved surface of out-of-control.The conjugate state equations and the state equations have been solved by use of Laplace Transformation. Through considerably complex computation, the optimal intercept guidance laws have been deduced in the following analytical formsThrough appropriate selection of the terminal time lf or the time of lead T, the results obtained above may be transformed into the optimal guidance laws which are composed of the proportional navigation with varied coefficients and the correctional terms associated with acceleration and angular acceleration of sight-line rotation. These results are similar to those of missiles with first order delay link in form and have no need of any additional parameter. However, the computation is more complex and the results are more accurate.Finally, the optimal intercept guidance laws are studied in the case of the proper frequency of a missile ω approaching to infinity, i. e. in the case of an ideal particle. The results are the same as those obtained by the other authors.

In this paper, effect of deflection of vertical on ballistic missileimpact accuracy is discussed. By analysing the effect of deflection of vertical in the powered stepsof flight the perturbations of the cut-off condition are obtained. Onanalysing the miss coefficient we arrived at the conclusion that it isnecessary to use the cut-off parameters taking in account the earthsrotation for computing the miss coefficients. Analytical formulas forobtaining the cut-off parameters taking in account the earth's rotationfrom...

In this paper, effect of deflection of vertical on ballistic missileimpact accuracy is discussed. By analysing the effect of deflection of vertical in the powered stepsof flight the perturbations of the cut-off condition are obtained. Onanalysing the miss coefficient we arrived at the conclusion that it isnecessary to use the cut-off parameters taking in account the earthsrotation for computing the miss coefficients. Analytical formulas forobtaining the cut-off parameters taking in account the earth's rotationfrom those without taking earth's rotation into account are derived.These formulas used to compute the cut-off parameters under any lauchconditions without the integration of the system of differential eq-uations. The cut-off parameters thus obtained can be used to computethe miss coefficients. In comparison with the results obtained by direct integration oftrajectory equations the method described in this paper gives a relationerror on miss distance of less than 2% and an absolute error of about30 meters. Finally, this paper puts formulas for computing the miss distancedue to deflection of the vertical and methods for correcting the missdistance of inertial guidance are briefly discussed.