Abstract
Impact time control guidance (ITCG) is an important approach to achieve saturation attack on targets. With the increasing complexity of warfare requirements for missiles, an ITCG with field-of-view (FOV) constrained for antiship missiles is proposed based on equivalent sliding mode control. Firstly, in view of the accuracy of the calculation of remaining impact time for guidance law, the large initial lead angle is taken into consideration in the estimation of remaining flying time in which there is no need for the assumption of small angle approximation. Besides, for the sake of promoting the practical application value of the proposed guidance law, FOV is considered so that it can satisfy the actual working performance of the seeker. Then, combined with the concept of predicted interception point (PIP), the proposed guidance law is applied to attack a moving target. Numerical analysis is carried out for different initial lead angles, various impact time, different methods of estimating remaining flying time, and cooperative attack conditions. Compared with proportion navigation guidance (PNG), the feasibility and effectiveness of the guidance law are verified. Simulation results demonstrate that the proposed guidance law can guarantee the constraints of both impact time and FOV effectively.
Highlights
In recent years, in the development of weapon equipment, antiship operations are faced with an unprecedented environment and presenting unprecedented new characteristics
In order to achieve the tactical effect of such saturate attack, it is necessary to realize the impact time control guidance (ITCG) for missiles so that each missile can independently or cooperate with each other to complete the attacking mission according to the specified impact time [1, 2]
An estimation of remaining flying time which is suitable for a large initial lead angle is adopted so as to allow more applicability in achievement of desired impact time
Summary
In the development of weapon equipment, antiship operations are faced with an unprecedented environment and presenting unprecedented new characteristics. As for the mentioned guidance schemes, there are some disadvantages in the estimation of the remaining flight time at a large initial lead angle or in specific attack time control guidance law design. (1) In view of the actual working characteristics of the seeker, an ITCG law is proposed under the premise of satisfying the constraint of the seeker’s FOV, which improves the practical application value of the proposed guidance law (2) The large initial lead angle is taken into consideration in the process of calculating the remaining flying time so that there is no need to adopt the concept of the assumption of small angle approximation, which results in the fact that the calculation accuracy of impact time can be guaranteed (3) Based on the equivalent sliding mode control algorithm, the guidance law is designed by selecting the error of impact time.
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