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Aircraft overload loop design method for providing damping by adopting angular acceleration

A technology of angular acceleration and design method, applied in the field of aircraft control, can solve the problems of insufficient system damping, overload static error, etc., and achieve the effect of high stability margin and high engineering application value

Active Publication Date: 2020-05-12
NAVAL AVIATION UNIV
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Problems solved by technology

[0004] The object of the present invention is to provide a method of designing an aircraft overload circuit that uses angular acceleration to provide damping, and then at least to a certain extent overcome the problems of static overload or insufficient system damping in traditional overload control methods caused by limitations and defects of related technologies question

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  • Aircraft overload loop design method for providing damping by adopting angular acceleration
  • Aircraft overload loop design method for providing damping by adopting angular acceleration
  • Aircraft overload loop design method for providing damping by adopting angular acceleration

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Embodiment Construction

[0052] 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 may be practiced without one or more of the specific details, or other methods, components, devices, steps, etc. may be adopted. In other instances, well-known technical solutions have not been shown or desc...

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Abstract

The invention relates to an aircraft overload loop design method for providing damping by adopting angular acceleration and belongs to the technical field of aircraft control. According to the method,an angular accelerometer is adopted to measure the yaw angular acceleration of an aircraft to provide damping for an overload outer loop, then an accelerometer is adopted to measure the linear acceleration of the aircraft to obtain lateral overload; the lateral overload is compared with an expected overload instruction, and therefore, an overload error signal is obtained; integration is performedon the overload error signal twice, so that an overload error comprehensive integration signal can be formed, so that a conversion static error problem between the overload instruction and an attitude instruction can be eliminated; the nonlinear transformation signal of an aircraft attitude angular acceleration signal, the proportional signal of a yaw rate and the secondary nonlinear transformation signal of an aircraft angular speed signal are introduced to form the damping signal of the overload loop, and the damping signal is output to an attitude stabilization loop, so that the control objective of overload tracking can be realized. With the method adopted, the problems of static error and insufficient damping of traditional overload control can be solved.

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, mainly using a linear accelerometer and an angular accelerometer as measuring components to measure the aircraft's overload and attitude angular acceleration, thereby providing damping to increase the aircraft System stability. Background technique [0002] Although most of the current aircraft adopt the traditional attitude control system, it is more convenient to use overload control and proportional guidance matching for the guidance of the terminal unmanned aerial vehicle, especially for the unmanned aerial vehicles using proportional guidance. At the same time, for the UAVs for air defense interception, in order to increase their maneuverability and increase the probability of interception, most of them also use overload control. However, the overload control is also divided in...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B11/42
CPCG05B11/42Y02T90/00
Inventor 马培蓓寇昆湖纪军孟蕾孙永芹王玲玲
Owner NAVAL AVIATION UNIV
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