An Iterative Guidance Method Applicable to Launch Vehicle Orbit Correction

Abstract

The invention relates to an iteration guidance method applicable to carrier rocket orbit injection correction. The method includes: acquiring the current position, current speed and apparent acceleration of a carrier rocket; using a repeated iteration method to calculate the pitch angle and yaw angle needed by rocket orbit injection according to the current position, the current speed and the current apparent acceleration; correcting the attitude of the carrier rocket according to the pitch angle and the yaw angle. The method has the advantages that the method has the high-precision control feature of traditional iteration guidance and the small calculation quantity feature of traditional perturbation guidance, required speed increment can be determined by predicting the orbit parameter partial derivative of a power off orbit injection point, and closed-loop control of the main orbit parameters of the rocket can be achieved.

Description

technical field [0001] The invention belongs to the technical field of launch vehicles, and in particular relates to an iterative guidance method suitable for launch correction of launch vehicles. Background technique [0002] At present, most launch vehicles use iterative guidance method or perturbation guidance method for guidance control. Among them, the basic idea of ​​perturbation guidance is to first determine a standard trajectory from the launch point to the target point, relying on this standard trajectory for guidance and shutdown control, the purpose is to make the actual flight trajectory as close as possible to the standard trajectory. In the perturbation guidance method, when deriving the guidance equation, the high-order terms above the second order of the Taylor series expansion are ignored, which will cause large method errors, and the calculation of its elements is more complicated. [0003] The realization of iterative guidance is actually an optimal cont...

AI Technical Summary

Problems solved by technology

[0004] However, the calculation process of the traditional iterative guidance method involves more coordinate transformations and matrix operations, and the amount of iterative calculation is relatively large; the traditional perturbation guidance method uses binding to track the standard trajectory and applies transverse normal guidance to guide the rocket. , although the calculation amount is simple, it needs to bind standard ballistics, so it is not flexible

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