Gust mitigation analysis method based on state space form vortex grid method

A state-space equation and state-space technology, applied in the direction of instrumentation, design optimization/simulation, calculation, etc., can solve the problems of decreased accuracy, low calculation efficiency, inconvenient control system design, etc., and achieve good model applicability and accurate calculation.

Active Publication Date: 2021-07-16
BEIHANG UNIV
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Problems solved by technology

[0007] In order to overcome the traditional aeroelastic gust analysis (1) the dipole grid method-rational function fitting method needs to perform rational function fitting, which leads to the decrease of accuracy and cumbersome steps and (2) the low calculation efficiency of the vortex grid method-loosely coupled iterative method , which is not convenient for the lack of control system design

Method used

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  • Gust mitigation analysis method based on state space form vortex grid method
  • Gust mitigation analysis method based on state space form vortex grid method
  • Gust mitigation analysis method based on state space form vortex grid method

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Embodiment 1

[0113] A large spread-chord wing model is adopted, and the main beam of the wing model is a cross beam that increases linearly from the wing tip to the wing root. The main beam position is located at 40% of the chord length. The main beam is simulated by CBEAM beam unit in MSC.Nastran, the wing rib is simulated by high stiffness beam unit, and the mass characteristics are simulated by concentrated mass point. Some parameters of the model are shown in Table 1.

[0114] Table 1 Flying wing model parameters

[0115] parameter name parameter value Wing span length / m 1.542 Chord length of wing root / m 0.261 Wing tip chord length / m 0.069 Torsion angle / Deg -2.0 aspect ratio 9.3 Mass / kg 2.8199 airfoil supercritical airfoil

[0116] S1: calculation initialization;

[0117] Establish an aerodynamic model, divide 5 grids along the chord direction and 40 grids in the span direction on the mid-arc surface of the wing, divide the ...

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Abstract

The invention discloses a gust alleviation analysis method based on a state space form vortex grid method, and the method comprises the following steps: establishing an aerodynamic grid according to a given model, and establishing a relationship among model attachment vortex intensity, trailing vortex intensity and wing surface induced velocity according to the state space form vortex grid method; forming an aeroelastic coupling equation after the relation between the generalized coordinates of the finite element mode and the control surface mode and the wing surface induced velocity is obtained through interpolation, wherein the aeroelastic coupling equation is also in the state space form, a given gust model serves as external excitation, and aeroelastic gust analysis can be conducted; on the basis of the aeroelastic coupling equation, taking the acceleration of a certain point of a wing as system output, forming control surface deflection input signals after the acceleration passes through a controller, building a closed-loop control system, and carrying out aeroelastic gust slowing-down simulation analysis. According to the method, gust analysis precision can be improved, frequency domain and time domain conversion is avoided, and analysis efficiency is improved.

Description

technical field [0001] The invention belongs to the technical field of structural dynamics and aeroelasticity analysis, and in particular relates to a gust mitigation analysis method based on a state space form vortex lattice method. Background technique [0002] As a branch of applied mechanics, aeroelasticity mainly studies the coupling between aerodynamic force, elastic force and inertial force. Under the action of aerodynamic force, the elastic structure vibrates and deforms, and the elastic movement of the structure will in turn cause the magnitude and distribution of aerodynamic force to change. This interaction will bring about a variety of aeroelastic phenomena, including aeroelastic deformation, chatter vibration, gust response, etc. When the aircraft encounters gust disturbances during flight, the body structure will turbulence, which will interfere with the pilot's operation, affect the ride comfort, increase the aeroelastic load, shorten the fatigue life of the ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/23G06F30/28G06F113/08G06F119/14
CPCG06F30/23G06F30/28G06F2113/08G06F2119/14Y02T90/00
Inventor 谢长川安朝杨澜杨超
Owner BEIHANG UNIV
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