A fast maneuvering method for aircraft attitude based on angular acceleration derivative as sinusoidal curve

Abstract

The invention discloses a fast aircraft attitude maneuvering method based on the fact that angular acceleration derivatives are in a sine curve. The method comprises the steps that an attitude maneuvering path undergoing the three processes of acceleration, constant speed and deceleration is designed according to the moment and angular momentum providing capacity of an actuating mechanism of a control system, in the processes of acceleration and deceleration, it is guaranteed that the derivatives of the angular acceleration are in the standard sine curve, it is guaranteed that moment output in the entire maneuvering process is continuous and first-order derivatives are continuous, so that the moment output is stably changed in the entire maneuvering process, and the trigger effect on a flexural mode in the attitude maneuvering process is small. After aircraft attitude maneuvering is in place, due to the fact that the vibration amplitude value of the flexural mode is small, the attitude of an aircraft can be stable rapidly, and therefore fast maneuvering and fast stable controlling are achieved. The fast aircraft attitude maneuvering method is particularly suitable for aircrafts which are serious in flexural mode coupling for conducting fast maneuvering control, and fast and stable control demands can be met.

Description

Technical field [0001] The invention relates to a fast maneuvering control method for a flexible spacecraft, in particular to a fast maneuvering method for an aircraft attitude based on a sine curve of the angular acceleration derivative, belonging to the field of spacecraft attitude control. Background technique [0002] Modern spacecraft usually have flexible attachments with light structures such as large solar panels. During the flight of flexible spacecraft, it is often necessary to quickly perform large-angle attitude maneuvers to meet mission requirements. Theoretical analysis shows that due to the strong coupling between the central rigid body dynamics of the spacecraft and the vibration of the flexible attachment, the nonlinear dynamic characteristics of the spacecraft are more pronounced when the attitude is maneuvered to a large angle, which often leads to the continuous strong vibration of the flexible attachment. Seriously affect the attitude movement, and even direc...

AI Technical Summary

Problems solved by technology

Since the planning method only considers the continuation of the angular acceleration, the derivative of the angular acceleration will jump at the beginning and end of the planning, and there is still a certain excitation effect on the flexible mode, which is not good for the stability of the attitude maneuver.

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