A lateral guidance method applied under the condition of large landing angle

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 lateral guidance method applied under the condition of a large landing angle, and belongs to the field of aircraft guidance and control. Background technique [0002] Uncontrolled and simple-controlled aircraft are affected by various deviations and flight disturbances during actual flight, and their ability to resist interference and deviations is weak, so the range and accuracy of the aircraft are limited accordingly. The application of full-range guidance technology has become a new development direction of 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 angle is to vertical when landing, the more conducive to the realization of the flight mission. Under the condition of a large inclination angle in the longitudin...

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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