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Design method for improving aerodynamic elastic stability based on beam structure of ultrahigh-speed aircraft

A technology of aeroelasticity and design method, applied in the direction of design optimization/simulation, sustainable transportation, etc., can solve the problems of structural damage, prone to flutter, insufficient flutter boundary, etc.

Active Publication Date: 2020-06-19
HARBIN ENG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to solve the problem that the conventional uniform beam structure of the aircraft in the prior art has insufficient flutter boundaries, is prone to flutter and often leads to catastrophic structural damage, and now provides a beam structure based on an ultra-high-speed aircraft Design method for improving aeroelastic stability

Method used

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  • Design method for improving aerodynamic elastic stability based on beam structure of ultrahigh-speed aircraft
  • Design method for improving aerodynamic elastic stability based on beam structure of ultrahigh-speed aircraft
  • Design method for improving aerodynamic elastic stability based on beam structure of ultrahigh-speed aircraft

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specific Embodiment approach 1

[0019] Specific Embodiment 1: A design method for enhancing the aeroelastic stability of an ultra-high-speed lower beam structure described in this embodiment, the method includes the following steps:

[0020] Step 1. According to the actual use requirements of the beam structure in ultra-high-speed flight, design the basic dimensions of the beam structure; the basic dimensions include the length L, width b, and thickness h of the beam structure, (such as figure 1 shown), and determine the material properties and material parameters at the same time, the material properties are steel (steel is the most commonly used material in aircraft), and the material parameters include elastic modulus E 0 and density ρ 0 ; First determine the corresponding parameters, when E 0 =210GPa, ρ 0 =7860kg / m 3 (This is the inherent property of steel), the beam structure at this time can be called a uniform beam structure (a beam using only steel materials);

[0021] Step 2. After determining t...

specific Embodiment approach 2

[0023] Embodiment 2: On the basis of a uniform beam structure, the aeroelastic stability of the structure is improved by using an additional lumped mass method; the difference between this embodiment and Embodiment 1 is that in the third step, the additional lumped mass method is used Improve the aeroelastic stability of the beam structure; the specific process is:

[0024] Attach lumped masses to beams, such as figure 2 As shown, by changing the mass m of the concentrated mass c and the position x on the beam m To observe the change of its vibration boundary, obtain the influence law of the lumped mass on the flutter behavior of the structure and determine the optimal m c and x m ;Design with additional lumped mass;

[0025] In the MATLAB program, by continuously changing the mass m of the concentrated mass c and the position x of the lumped mass on the beam m From the simulation results, observe the changes in the flutter order and the flutter boundary, and find the m...

specific Embodiment approach 3

[0027] Embodiment 3: On the basis of a uniform beam structure, the method of spring restraint is used to improve the aeroelastic stability of the structure; the difference between this embodiment and Embodiment 1 or 2 is that in step 3, the spring restraint method is used to improve the aeroelastic stability of the structure. The aeroelastic stability of the structure; the specific process is:

[0028] Such as image 3 As shown, respectively by changing the spring coefficient k c and the spring constraint position x s value, observe the change of its flutter boundary, and determine the optimal elastic coefficient k c and the spring constraint position x s ;The entire beam is divided into two self-spans for design using spring constraints:

[0029] By constantly changing the elastic coefficient k in the MATLAB program c and the spring constraint position x s From the simulation results, observe the changes of the flutter order and the flutter boundary, and find the k that...

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Abstract

The invention discloses a design method for improving aerodynamic elastic stability based on a beam structure of an ultrahigh-speed aircraft. The invention aims to solve the problems that flutter boundaries of conventional uniform beam structures of aircrafts in the prior art are insufficient, flutter is prone to occurring, and disastrous structural damage is often caused by flutter. The method comprises the steps that the basic size of a beam structure is designed according to the use requirement of the beam structure in ultra-high-speed flight, and meanwhile material attributes and materialparameters are determined; under the action of the determined aerodynamic force, MATLAB simulation software is used for programming simulation, and the chatter order and the chatter boundary of the uniform beam are obtained; based on the chatter order and the chatter boundary of the uniform beam, the aeroelastic stability of the beam structure is improved through an additional concentrated mass method, a spring constraint method or an axial functionally graded material design method. The invention belongs to the field of aerospace.

Description

technical field [0001] The invention relates to a design method for improving aeroelastic stability based on a beam structure of an aircraft at an ultrahigh speed. Background technique [0002] It is one of the most important problems in aeroelasticity, which is the self-excited vibration of elastic structure with unattenuated amplitude due to the coupling effect of aerodynamic force, elastic force and inertial force in uniform air flow. The structural flutter of aerospace vehicles is a self-excited vibration phenomenon that occurs in high-speed airflow, and this phenomenon is more obvious on supersonic and hypersonic vehicles. When the flutter phenomenon occurs, the structure will vibrate with large nonlinear deflection, which will affect the operational safety of the aircraft and lead to catastrophic structural damage. Contents of the invention [0003] The purpose of the present invention is to solve the problem that the conventional uniform beam structure of the aircr...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20
CPCY02T90/00
Inventor 宋智广孙禹晗李凤明
Owner HARBIN ENG UNIV
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