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Semi-global self-adaptive control method aiming at non-standard nonlinear aircrafts

A technology of adaptive control and adaptive controller, applied in the direction of adaptive control, general control system, control/regulation system, etc., can solve problems such as the inability to expand the aircraft system

Active Publication Date: 2019-08-09
QUFU NORMAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, existing methods mainly focus on standard aircraft systems and cannot be extended to control non-standard aircraft systems

Method used

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  • Semi-global self-adaptive control method aiming at non-standard nonlinear aircrafts
  • Semi-global self-adaptive control method aiming at non-standard nonlinear aircrafts
  • Semi-global self-adaptive control method aiming at non-standard nonlinear aircrafts

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Embodiment

[0108] Below in conjunction with a group of linearized Boeing 737 longitudinal dynamics models and accompanying drawings to demonstrate the proposed control method, the present invention will be described in further detail.

[0109] In this embodiment, the semi-global adaptive control method includes the following steps:

[0110] 1. T-S fuzzy intelligent modeling of non-standard nonlinear aircraft system

[0111] 1) Locally linearized aircraft system model, using three locally linearized Boeing 737 longitudinal dynamic models, covering three modes of aircraft climbing, cruising and descending;

[0112] In the climbing case, the linearization matrix is

[0113]

[0114] In the descending case, the linearization matrix is

[0115]

[0116] In the cruise case, the linearization matrix is

[0117]

[0118] For each operating point (climb, cruise, descent) in this simulation, the system output matrix is ​​chosen as

[0119] C=[0,1,0,0]

[0120] 2) T-S fuzzy intelligen...

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Abstract

The invention provides a semi-global self-adaptive control method aiming at non-standard nonlinear aircrafts. The semi-global self-adaptive control method comprises the steps that (1) a rigid aircraftlongitudinal dynamic system model is given; (2) a stable operating point is determined, and a local linearized system model of an aircraft system is obtained, a T-S fuzzy intelligent approximation technology is utilized to establish a T-S fuzzy intelligent aircraft dynamics model: and (3) the T-S fuzzy intelligent aircraft dynamics model is dynamically reconstructed to derive a T-S fuzzy intelligent aircraft system standard form based on relative degree; and (4) an effective self-adaptive controller is designed, the ideal performance of a controlled system is realized, that is, closed-loop stability and asymptotic output tracking.

Description

technical field [0001] The invention relates to a semi-global self-adaptive control method for non-standard non-linear aircraft, and belongs to the field of self-adaptive control of rigid aircraft longitudinal dynamics systems. Background technique [0002] Aircraft systems usually have large parameter or structural uncertainties due to the large operating range, the influence of external environment changes and system failures. As an important issue of aircraft system, adaptive control has been extensively studied and important progress has been made. [0003] Existing aircraft flight control methods are mainly limited to locally linearized aircraft systems or standard nonlinear systems. For example, in the document "Multivariable adaptive algorithms for reconfigurable flightcontrol", the model reference adaptive control problem of the local linearization model of the F / A-18C / D aircraft is studied. However, this control method using a locally linearized aircraft system mo...

Claims

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Application Information

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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 张言军李冰洁张正强武玉强
Owner QUFU NORMAL UNIV
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