Flexible flight dynamics modeling method considering structural nonlinearity

A technology of flight dynamics and modeling method, which is applied in the field of flexible flight dynamics modeling, can solve problems such as difficult to accurately describe the nonlinear relationship of aeroelasticity, so as to improve rationality and accuracy, high simulation calculation efficiency, and build The effect of short mold cycle

Active Publication Date: 2021-12-17
BEIHANG UNIV
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Problems solved by technology

The above methods all have certain limitations in considering structural nonlinear factors, especially rudder su

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  • Flexible flight dynamics modeling method considering structural nonlinearity
  • Flexible flight dynamics modeling method considering structural nonlinearity
  • Flexible flight dynamics modeling method considering structural nonlinearity

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specific Embodiment 1

[0111] Such as figure 1 As shown, this embodiment only considers the aircraft model of the longitudinal plane ( figure 2 ), which is modeled with flexible flight dynamics considering structural nonlinearity.

[0112] The first step is to define the coordinate system of the aircraft. The origin of the body axis system is at the center, and the initial position coincides with the inertial system. The degrees of freedom of the simplified model of the aircraft are determined as follows: , downward is positive; pitch degree of freedom , the aircraft head-up is positive; the deflection degree of freedom of the control surface , down is positive. The distance from the elastic axis of the aircraft to the center of gravity is , the distance from the midpoint of the chord to the elastic axis is ; The distance from the control surface hinge to the midpoint of the wing is , the distance from the center of gravity of the control surface to the hinge of the control surface is ...

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Abstract

The invention discloses a flexible flight dynamics modeling method considering structural nonlinearity. The method comprises the following steps: establishing an aircraft flight dynamics equation containing nonlinear aeroelastic wings by using an unsteady aerodynamic force; fitting the relationship between the hysteresis nonlinear generalized force and the displacement by adopting a rational formula, so as to establish an aircraft flight kinetic equation containing nonlinear rigidity and nonlinear damping at the same time; and finally, solving response characteristics and stability of the nonlinear flight dynamics model by using a numerical method or a harmonic balance method. The unified expression form for describing the nonlinearity of the structure established by the invention can solve the problems of aircraft gap nonlinear dynamic modeling and subsequent dynamic analysis under the conditions of installation gaps between control surface hinges and connecting pieces, aging and loosening of parts and the like, so that a guiding idea is provided for related controller design; and the method has a certain engineering application value.

Description

technical field [0001] The present invention relates to the technical field of aircraft dynamics, in particular to a flexible flight dynamics modeling method considering structural nonlinearity, which can efficiently and accurately solve the structural nonlinearities in the flight dynamics modeling of high-speed aircraft and large-aspect-ratio UAVs. The linear problem and dynamic analysis provide a model basis for the subsequent control design of the aircraft. Background technique [0002] With the continuous advancement of aviation science and technology and the continuous improvement of modern aircraft performance requirements, the classical linear aeroelastic theory can no longer fully meet the needs of aircraft design, and the problem of nonlinear aeroelasticity has gradually attracted people's attention. The nonlinear factors in aeroelastic problems can be divided into two types: aerodynamic nonlinearity and structural nonlinearity. Among them, structural nonlinearity ...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/23G06F30/28G06F113/08G06F119/14
CPCG06F30/15G06F30/23G06F30/28G06F2113/08G06F2119/14Y02T90/00
Inventor 李道春邵浩原阚梓申童姚卓尔赵仕伟向锦武
Owner BEIHANG UNIV
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