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A Modeling Method Based on Online Identification for Large Flexible Aircraft

A modeling method and aircraft technology, applied in the field of aircraft modeling, can solve problems such as model uncertainty, time variation, and obvious nonlinear characteristics, and achieve the effect of improving reliability

Active Publication Date: 2020-04-17
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0005] Purpose of the invention: In order to overcome the problems of high model order, obvious nonlinear characteristics, uncertain and time-varying models encountered in the design of large flexible aircraft controllers, this invention proposes a modeling method based on online identification for large flexible aircraft

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  • A Modeling Method Based on Online Identification for Large Flexible Aircraft
  • A Modeling Method Based on Online Identification for Large Flexible Aircraft
  • A Modeling Method Based on Online Identification for Large Flexible Aircraft

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Embodiment Construction

[0032] The present invention will be further described below in conjunction with the accompanying drawings.

[0033] Step 1: The large aspect ratio wing structure of the large flexible aircraft is greatly deformed, resulting in geometrically nonlinear phenomena, and the nonlinear structural model of the wing is established using the geometrically nonlinear beam theory; in order to analyze the continuous vibration system for which no analytical solution can be found, the Discretize the overall structure of the large-aspect-ratio wing of a large flexible aircraft to obtain a unit structure model; the aerodynamic load generated by the movement of the wing is affected, and the unsteady aerodynamic model is established using the unsteady aerodynamic theory; the aerodynamic force and other external forces The model is brought into the unit structure model to establish a unit aeroelastic mechanism model describing the unit aeroelastic dynamics behavior.

[0034] The specific steps ar...

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Abstract

The invention relates to a modeling method of a large-flexibility flight vehicle based on online identification. The modeling method comprises the four steps of building of a unit mechanism model, parameterization of the unit model, building of an overall flight dynamic model and online identification. According to the fact that when the large-flexibility vehicle is on flight, wings can be subjected to geometric nonlinearity deformation, and a structural model of flexible wings is built based on a nonlinear beam theory; a continuous vibration system is discretized to obtain a unit structure model; aiming at the feature that aerodynamic force is unsteady, an unsteady aerodynamic theory is utilized to build an aerodynamic force model; the aerodynamic force model and external forces like gravity are substituted into the structural model to obtain a unit gas bomb mechanism model; according to needs, variables capable of being measured by proper sensors are selected as parameters, and parameteriztion of the unit model is conducted; moreover, the parameters are utilized to achieve connection among units; a many-body dynamic theory is utilized to build the overall dynamic model of the flight vehicle; finally, a proper sensor is selected to achieve parameter online identification to obtain the large-flexibility flight vehicle real-time dynamic model.

Description

technical field [0001] The invention relates to a method for constructing a real-time dynamic model of a large flexible aircraft, in particular to a modeling method for a large flexible aircraft based on online identification, belonging to the field of aircraft modeling. Background technique [0002] High-altitude and long-endurance aircraft is currently a research hotspot in the field of aviation at home and abroad, and it has important application value for various high-altitude flight missions. This type of aircraft generally adopts flexible wings with large aspect ratios. When maneuvering or being disturbed by the outside world, large geometric nonlinear deformations will occur, which will change the lift and moment distribution of the entire aircraft and affect the rigid body motion of the aircraft. In addition, due to the low frequency of structural vibration, there is coupling between the flight dynamics and structural dynamics of this type of aircraft. Therefore, it...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B17/02
CPCG05B17/02
Inventor 雷灏何真刘燕斌陈柏屹陆宇平
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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