Aircraft lateral parallel centroid control method based on overload control

A control method and overload control technology, applied in the direction of electric controllers, controllers with specific characteristics, attitude control, etc., can solve the problems of control accuracy, rapidity and stability margin at the same time, and achieve good engineering practical value , measurement is simple, and the effect of improving rapidity

Active Publication Date: 2021-01-15
NAVAL AVIATION UNIV +1
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Problems solved by technology

[0004] The purpose of the present invention is to provide a method for controlling the lateral parallel center of mass of an aircraft based on overload control, and then at least to a certain extent overcome the difficulty of simultaneously taking into account the control accuracy, rapidity and stability margin caused by the limitations and defects of related technologies question

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  • Aircraft lateral parallel centroid control method based on overload control
  • Aircraft lateral parallel centroid control method based on overload control
  • Aircraft lateral parallel centroid control method based on overload control

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Embodiment Construction

[0055] Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete and fully convey the concept of example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. In the following description, numerous specific details are provided in order to give a thorough understanding of embodiments of the invention. However, those skilled in the art will appreciate that the technical solutions of the present invention can be practiced without one or more of the specific details, or other methods, components, devices, steps, etc. can be used. In other instances, well-known technical solutions have not been shown or describ...

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Abstract

The invention relates to an aircraft lateral parallel centroid control method based on overload control. Lateral acceleration, speed and position signals of the aircraft are measured by installing a KY-INS300 optical fiber integrated navigation system. On one hand, an overload signal is obtained by converting an acceleration signal, then nonlinear lag correction and proportional integral are carried out, and an overload comprehensive signal based on a lateral overload error rather than a lateral overload error is obtained and directly transmitted to a yawing rudder system. On the other hand, alateral position error signal is obtained by comparing the lateral position signal with an expected position instruction signal, and then nonlinear advanced correction and nonlinear integration are carried out to obtain a position error comprehensive signal which is directly transmitted to an aircraft yaw rudder system. Through the overload and position error parallel control method, the lateralcentroid control of the aircraft has good rapidity and good damping characteristics due to the introduction of overload signals, and has the advantages of simple scheme and simple measurement.

Description

technical field [0001] The invention relates to the field of aircraft stability and turning control, in particular to a method for controlling the lateral parallel center of mass of an aircraft based on overload control. Background technique [0002] In the lateral center of mass movement of the traditional aircraft, in addition to the unconventional BTT method of sideslip turning, the sideslip turning method with attitude control as the core is generally adopted, that is, the attitude stability loop is used as the inner loop, and then the PID of the center of mass error The loop generates a comprehensive signal for the outer loop to drive the inner loop, which is essentially a series method in which the inner and outer loops are mosaiced. Of course, for some aircraft with strong maneuverability under the overload control system, the lateral center of mass movement also adopts the method of driving the overload stabilization loop by the error of the center of mass. The essen...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B11/42G05B13/04G05D1/10G05D1/08
CPCG05B11/42G05B13/042G05D1/101G05D1/0816
Inventor 雷军委李静李恒梁国强王瑞奇
Owner NAVAL AVIATION UNIV
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