Overweight compensating guidance method and trajectory reshaping guidance method conducting correction based on pseudo-spectral method

Abstract

The invention provides an overweight compensating guidance method and trajectory reshaping guidance method conducting correction based on a pseudo-spectral trajectory optimization result, and belongsto the field of the space technology, the weapon technology and guidance control. The overweight compensating guidance method and trajectory reshaping guidance method specifically comprises the stepsthat firstly, a fight model is established, and guided missile pneumatic parameters and atmosphere model parameters are determined; secondly, a guided missile motion equation is established, and an optimal control problem is established; thirdly, the pseudo-spectral method is used for solving the optimal control problem; fourthly, polynomial fitting and other manners are used for fitting the pseudo-spectral optimal result; and fifthly, according to the pseudo-spectral optimal result, the typical trajectory reshaping guidance rule and the typical gravity compensation guidance rule are corrected. The overweight compensating guidance method and trajectory reshaping guidance method has the advantages that the final velocity of a guided missile is increased, and the attacking effect of the guided missile is greatly improved; through fitting of the pseudo-spectral optimal result, the guidance rule is segmented, the guided missile flight speed is increased in a front section, the guidance parameters are adjusted in a rear section, and the guidance rule conforms to the fall angle constraint; and the black hole phenomenon of the typical gravity compensation guidance rule is avoided, and important significance is achieved for actual application.

Description

technical field [0001] The invention provides an overweight compensation guidance method and a trajectory shaping guidance method corrected based on pseudo-spectral trajectory optimization results, and belongs to the fields of aerospace technology, weapon technology, and guidance control. Background technique [0002] The guidance problem of the dual-pulse medium-range and long-range air-to-air missile needs to solve the problem of energy management. It is necessary to reasonably control the speed curve of the missile, and at the same time increase the flight altitude of the missile so that most of the flight time of the missile is in a high-altitude area with thin air and low density. In order to strike high-value and high-risk targets, modern precision-guided aircraft need to further enhance their combat capabilities. Therefore, higher requirements are put forward in the project, such as limiting the drop angle of missiles. Therefore, it is necessary to study the guidance ...

AI Technical Summary

Problems solved by technology

Due to the comparison of the offline pseudospectral optimal simulation results and the typical guidance law simulation results, it is found that after a certain fall angle constraint is met, the missile gui

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