Lateral guidance method applied on large landing inclination angle condition

Abstract

A lateral guidance method applied on a large landing inclination angle condition enables the influence of a large landing inclination angle on the lateral guidance instructions to be reduced and the strike precision to be improved effectively, reasonably distributes and plans the lateral guidance instructions, avoids the larger tail-segment guidance amount, solves the lateral guidance instruction calculation problem of an aircraft on the large landing inclination angle condition, and satisfies the demands at the aspects, such as the large landing inclination angle condition, the lateral guidance precision, etc.

Description

Technical field [0001] The invention relates to a guidance method, in particular to a side guidance method applied under the condition of a large landing angle, and belongs to the field of aircraft guidance control. Background technique [0002] Uncontrolled and simply controlled aircraft are affected by various deviations and various flight disturbances during actual flight, and their ability to resist interference and deviations is relatively weak, so the range and accuracy of the aircraft are correspondingly limited. The application of full-course guidance technology has become a new development direction for current aircraft. From the perspective of system performance index requirements, there are also different requirements for the final landing attitude of the aircraft. Generally speaking, the closer the ballistic inclination to vertical when landing, the more beneficial the realization of the flight mission. Under the condition of large inclination in the longitudinal pla...

AI Technical Summary

Problems solved by technology

Using this guidance method, the guidance command in the initial stage is small, resulting in slow maneuvering speed, which is likely to cause a large amount of guidance to remain in the guidance process of the latter stage, which affects the strike accuracy.

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