Abstract
To explore the influence of the trace point step-jump behavior on a terminal guidance system, an analysis is performed from the line-of-sight rate (LOS rate) and guidance accuracy views for designing an anti-step-jump guidance law. First, the linear terminal guidance model under the trace point jump circumstance is constructed, and then the fundamental reason for the miss distance is investigated by deriving the upper bound of the LOS rate at the initial step-jump moment. Following this, the novel proposed analytical differential adjoint model is established with the adjoint method, and its validity is demonstrated comparing with the numeric derivative model. Based on the adjoint model, the effects of the ratio coefficient, the time constant, and the jump amplitude on the guidance accuracy are explored. Finally, a novel anti-step-jump guidance law is designed to shorten the recovery time of the overload. The simulations have shown that the faster recovery time and higher accuracy are achieved in comparison with the proportional navigation guidance, optimal guidance, and adaptive sliding mode guidance.
Highlights
Discriminating and localizing the interest points, steadily tracking the target, and processing with good timeliness are the main properties of optical detecting systems [1,2,3]
One is from the flare coming into the field of view (FOV) at the recognition moment, and the other starts from the recognition moment to the time that the missile body recovers to the stable tracking state
In contrast with [32], we find the results are the same, which implies that the upper bound of the normalized initial LOS rate is only associated with the time constant of the guidance system and total flight time when no first-order function exists
Summary
Discriminating and localizing the interest points, steadily tracking the target, and processing with good timeliness are the main properties of optical detecting systems [1,2,3]. We know that there are a lot of factors that can mitigate the striking capabilities and increase the likelihood of successful evasion, aside from IR flares, such as various target maneuvers, possible disturbances, and measurement noise [10,11,12] They all perform as a kind of persistent excitation and result in a continuous disturbance to the missile system. As the imperative parameter of the guidance system, little attention has been devoted to abnormal change of the LOS rate variable Cognizant of this problem, this paper analyzes the effects of flares from the LOS rate caused by the step-jump behavior and designed a novel anti-step-jump guidance law, the main contributions of which can be summarized as follows. The reason for the step-jump behavior is revealed and its influence on the LOS rate and miss distance is analyzed with the proposed analytic derivative adjoint model, respectively.
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