An Aircraft Overload Tracking Method Using Overload and Angular Velocity as the Outer Loop

A technology of aircraft and outer loop, applied in the field of aircraft control, to achieve the effect of eliminating the problem of insufficient system stability margin, improving stability, and high engineering practical value and economic value

Active Publication Date: 2022-05-27
NAVAL AVIATION UNIV
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Problems solved by technology

[0004] The purpose of the present invention is to provide an aircraft overload tracking method with overload and angular velocity as the outer loop, and then at least to a certain extent overcome the limitations and defects of related technologies that cannot be achieved on the basis of retaining the traditional attitude system. Overload control The problem

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  • An Aircraft Overload Tracking Method Using Overload and Angular Velocity as the Outer Loop
  • An Aircraft Overload Tracking Method Using Overload and Angular Velocity as the Outer Loop
  • An Aircraft Overload Tracking Method Using Overload and Angular Velocity as the Outer Loop

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Embodiment Construction

[0057] Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments, however, can be embodied in various 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 will 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 the embodiments of the present invention. However, those skilled in the art will appreciate that the technical solutions of the present invention may be practiced without one or more of the specific details, or other methods, components, devices, steps, etc. may be employed. In other instances, well-known solutions have not been s...

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Abstract

The invention relates to an aircraft overload tracking method using overload and angular velocity as the outer loop, and belongs to the technical field of aircraft control. It is characterized in that the accelerometer is used to measure the actual overload of the aircraft, and the overload error is obtained by comparing it with the overload command. At the same time, the yaw rate is measured by the gyroscope, and a nonlinear transformation is performed, which is used as the two-way damping signal of the overload outer circuit; Integral and nonlinear integral signals provide two integral signals. Finally, the integrated proportional signal, two integral signals and two differential signals constitute the outer loop signal of overload error. Then the outer loop signal is integrated and nonlinearly integrated, and the yaw rate signal is superimposed to form an attitude stabilization loop for the overload inner loop command to drive the aircraft, so as to achieve the control goal of lateral overload command tracking. This method can realize overload control on the basis of retaining the traditional attitude loop.

Description

technical field [0001] The invention belongs to the field of aircraft control, and in particular relates to a control system design method for aircraft attitude stability and overload stability. Background technique [0002] At present, the design methods of the aircraft control system mainly include two methods: overload stability tracking and attitude stability tracking. The former is called overload control, which is mostly used for unmanned aerial vehicles that emphasize maneuverability, while the latter is called attitude control, which has good performance. Stability margin and reliability, it is widely used in most unmanned and manned aerial vehicles. The traditional overload control generally does not measure the attitude angle of the aircraft, but only measures the overload and the angular velocity. The present invention proposes a composite control method that integrates the overload and the attitude control. The angular velocity is used in the outer loop to provid...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0825G05D1/101
Inventor 雷军委马培蓓孟蕾闫石宫俪铭王玲玲晋玉强
Owner NAVAL AVIATION UNIV
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