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A Rapid Compilation Method of UAV Gust Load Spectrum

A load spectrum and wind gust technology, applied in design optimization/simulation, sustainable transportation, special data processing applications, etc., can solve the problems of cumbersome process, costly manpower and material resources, etc., to achieve a simple and efficient system and shorten the spectrum compilation period , the effect of good engineering applicability

Active Publication Date: 2022-07-12
CHENGDU AIRCRAFT DESIGN INST OF AVIATION IND CORP OF CHINA
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AI Technical Summary

Problems solved by technology

The traditional spectrum compilation method is to use continuous turbulence analysis to calculate the size and frequency of gust loads in all task segments. The process is cumbersome and will cost a lot of manpower and material resources

Method used

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  • A Rapid Compilation Method of UAV Gust Load Spectrum
  • A Rapid Compilation Method of UAV Gust Load Spectrum
  • A Rapid Compilation Method of UAV Gust Load Spectrum

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Embodiment Construction

[0037] Taking a certain type of UAV as an example, the specific implementation steps of the method of the present invention are as follows:

[0038] 1) Calculate the reference eigenfrequency

[0039] Select a set of aircraft state parameters, including aircraft weight, height, Mach, average aerodynamic chord length of the wing, reference area of ​​the wing, slope of the wing lift line, dynamic aerodynamic derivative, and use the two-degree-of-freedom rigid body analysis method that ignores the elastic mode to calculate The gust responds to the eigenfrequencies, and uses these parameters and frequencies as "reference state parameters" and "reference eigenfrequencies".

[0040] The four key benchmark state parameters are: M a =0.3, 1 / μ g =0.031, 1 / c=0.808, 1 / A R =0.055, the reference characteristic frequency is: N 0 =1.305.

[0041] 2) Build a linear regression equation

[0042] Select 20 sets of aircraft state parameters, and use continuous turbulence analysis to calculat...

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Abstract

The invention belongs to the field of fatigue life design of aircraft structures, and relates to a rapid compiling method for a gust load spectrum of an unmanned aerial vehicle; a set of "reference state parameters" of an unmanned aerial vehicle are selected, and continuous turbulence analysis is used to calculate only one gust response "reference characteristic" For the flight state of any mission segment, the multiple linear regression method is directly used to obtain the gust response characteristic frequency of the mission segment. Finally, according to the time of various tasks in a life cycle, the surpassing number of gust speeds at all levels is calculated, and then the rapid compilation of the gust load spectrum is completed. The invention only needs to construct a multiple regression equation of the ratio of the key state parameter and the characteristic frequency of the gust response, and can realize the rapid compilation of the designed load spectrum, the measured load spectrum and the single-machine load spectrum, thereby shortening the spectrum compilation period; the method system is simple and efficient, and And it has good engineering applicability and can be extended to various types of aircraft.

Description

technical field [0001] The invention belongs to the field of aircraft structure fatigue life design, and relates to a rapid spectrum compilation method for a gust load spectrum of an unmanned aerial vehicle. Background technique [0002] The gust load caused by atmospheric turbulence has a great impact on the fatigue life of the UAV airframe structure, especially for cruise-based UAVs, the gust load is a source of fatigue load that cannot be ignored that causes fatigue damage / destruction of the aircraft structure. [0003] Using continuous turbulence analysis to compile the UAV gust load spectrum is a method generally recognized at home and abroad. The power spectral density function and the root mean square gust velocity distribution are used to characterize the random process of continuous turbulence, and it is related to the dynamic response characteristics of the aircraft structure. Combined, the methods of stochastic process theory are used to determine the aircraft loa...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/20
CPCG06F30/20Y02T90/00
Inventor 兑红娜王勇军董江王强廖宇聂凯
Owner CHENGDU AIRCRAFT DESIGN INST OF AVIATION IND CORP OF CHINA
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