Method for designing aircraft automatic flight control system rolling attitude control structure based on signal flow graphs

A technology of signal flow diagram and flight control system, which is applied in attitude control and other directions, and can solve problems such as complex motion equations of aircraft

Inactive Publication Date: 2016-01-20
AIR FORCE UNIV PLA
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Problems solved by technology

[0005] In the prior art, although many restrictive assumptions are made and

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  • Method for designing aircraft automatic flight control system rolling attitude control structure based on signal flow graphs
  • Method for designing aircraft automatic flight control system rolling attitude control structure based on signal flow graphs
  • Method for designing aircraft automatic flight control system rolling attitude control structure based on signal flow graphs

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Embodiment Construction

[0026] In order to make the objects and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the examples. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0027] The embodiment of the present invention provides a method for designing a roll attitude control structure of an aircraft automatic flight control system based on a signal flow diagram, including the following steps:

[0028] S1. Select r, β, p, and φ as the aircraft lateral motion state quantities respectively, and ζ and ξ as the aircraft lateral motion control quantities. Each state quantity is configured with an integrator, according to the aircraft lateral motion state equation

[0029]

[0030] Determining the differential expressions of r, β, p, φ state variables, that is, the input signals of each integrator, constitutes the over...

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Abstract

The invention discloses a method for designing an aircraft automatic flight control system rolling attitude control structure based on signal flow graphs. The method comprises the steps of firstly approximately separating local signal flow graphs of a Dutch roll motion mode and a rolling motion mode from a general signal flow graph of aircraft lateral motions; secondly, selecting a forward channel with the minimum number of integrators to act as a control transmission channel of each mode, and determining an optimal feedback loop so as to improve damping and natural frequency characteristics; and finally, configuring the determined feedback control loop to the general signal flow graph of the lateral motions, and determining a lateral rolling attitude control structure. The method disclosed by the invention overcomes a defect that an automatic flight control system rolling attitude optimal control structure cannot be determined because a feedback control loop is selected according to design experience in the prior art.

Description

technical field [0001] The invention relates to the design of a flight control system, in particular to a method for designing a roll attitude control structure of an aircraft automatic flight control system based on a signal flow graph. Background technique [0002] The roll attitude control of the aircraft automatic flight control system is the inner control loop of the aircraft's lateral motion, and is the basic controller of the lateral track control. Roll attitude control should be able to effectively improve the inherent damping characteristics, especially to improve the damping characteristics of the Dutch roll motion, stabilize the spiral motion, and improve the inherent characteristics according to the flight quality requirements, and create conditions for the external control loop; The influence of small gusts; stabilize the flight attitude, or control the roll angle as the control variable of the flight path; suppress the sideslip in the curved flight, etc. The d...

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Application Information

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IPC IPC(8): G05D1/08
Inventor 董新民陈勇薛建平孔星炜刘娇龙
Owner AIR FORCE UNIV PLA
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