Unmanned aerial vehicle gust load spectrum quick compiling method

A technology of load spectrum and wind gust, applied in design optimization/simulation, sustainable transportation, special data processing applications, etc., can solve the problems of large manpower and material resources, cumbersome process, etc.

Active Publication Date: 2021-03-19
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 frequen

Method used

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  • Unmanned aerial vehicle gust load spectrum quick compiling method
  • Unmanned aerial vehicle gust load spectrum quick compiling method
  • Unmanned aerial vehicle gust load spectrum quick compiling method

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Embodiment Construction

[0037] Taking a certain type of unmanned aerial vehicle 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, wing average aerodynamic chord length, wing reference area, wing lift line slope, dynamic aerodynamic derivative, and use the two-degree-of-freedom rigid body analysis method that ignores the elastic mode to calculate Gust response characteristic frequency, these parameters and frequencies are used as "reference state parameters" and "reference characteristic frequency".

[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) Construct a linear regression equation

[0042] Select 20 groups of aircraft state parameters, respectively use continuous turbulenc...

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Abstract

The invention belongs to the field of aircraft structure fatigue life design, and relates to an unmanned aerial vehicle gust load spectrum quick compiling method. A group of reference state parametersof the unmanned aerial vehicle are selected, continuous turbulence analysis is adopted to calculate gust response reference characteristic frequency only once, and for the flight state of any task section, a multiple linear regression method is directly adopted to obtain gust response characteristic frequency of the task section. Finally, the transcendental number of each gust speed is calculatedaccording to each task section time in one life cycle so as to finish the quick compilation of the gust load spectrum. According to the method, the multivariate regression equation of the key state parameter ratio and the gust response characteristic frequency ratio only needs to be constructed once, and quick compilation of the design load spectrum, the actual measurement load spectrum and the single-machine load spectrum can be realized, so that the compilation period is shortened; The method is simple and efficient in system, has good engineering applicability, and can be popularized to various aviation aircraft.

Description

technical field [0001] The invention belongs to the field of aircraft structure fatigue life design, and relates to a method for quickly compiling a gust load spectrum of an unmanned aerial vehicle. Background technique [0002] The gust load caused by atmospheric turbulence has a great influence on the fatigue life of the UAV body structure, especially for cruise-based UAVs, the gust load is a fatigue load source that cannot be ignored in causing fatigue damage / destruction of the aircraft structure. [0003] Using continuous turbulent flow 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 turbulent flow, and it is related to the dynamic response characteristics of the aircraft structure. Combined, the method of stochastic process theory is used to determine the aircraft loads gener...

Claims

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Application Information

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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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