Guidance law analysis method with attack time and seeker view field constraint

Abstract

The invention discloses a guidance law analysis method with attack time and seeker view field constraint. The method comprises the following steps: establishing a guidance equation of intercepting a static target in a two-dimensional horizontal plane by a missile; designing an intermediate variable related to the missile preposition angle, and converting the guidance equation into a differential equation based on the intermediate variable to obtain a guidance law expression; designing a quadratic function based on the intermediate variable as an expected relative distance curve; realizing theview field angle constraint of the seeker through the condition that the first derivative of the expected curve is greater than zero; and based on boundary conditions and attack time constraints, unknown parameters of the expected curve are solved, and a guidance law and an attack time reachable domain in an analysis form are obtained. The method adopts an analysis method based on relative distance remodeling, does not need to linearize the model, does not depend on estimation of remaining time, is suitable for guidance tasks with attack time constraint and limited strapdown seeker field of view, and has the characteristics of simple design, high reliability, strong applicability and the like.

Description

technical field [0001] The invention belongs to the field of missile guidance system design, and in particular relates to an analysis method of a guidance law with constraints of attack time and seeker field of view. Background technique [0002] In general, the main task of the guidance system is to guide the missile to the desired target point, that is, the flight constraint is zero miss. This type of task has a single indicator, a relatively simple design, and a mature method. However, it is somewhat conservative to consider only zero off-target amount as a guidance constraint. For example, for targets with regional electronic countermeasures, detection interference, and strong defense, a guidance method that simply considers the constraint of zero misses may cause the missile to be intercepted by the enemy, resulting in mission failure or failure to achieve the best strike effect. At present, an effective solution to this problem is to adopt a guidance method with atta...

AI Technical Summary

Problems solved by technology

Most of the existing attack time-constrained guidance methods need to rely on the estimated information of the remaining time, or need to linearize the mathematical model of the missile and the target, or need to design multiple guidance parameters, which will cause serious problems for the designed guidance method. A certain degree of conservatism, but also reduces the applicability of the guidance system

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