Method for rapidly obtaining speed of transonic flutter of composite airfoil surface
A transonic, airfoil technology, applied in special data processing applications, instruments, electrical and digital data processing, etc., can solve problems such as time-consuming and large amount of calculation in the numerical simulation process.
Active Publication Date: 2012-03-21
中国航空工业集团公司科学技术委员会 +1
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Problems solved by technology
Compared with the previous methods, the CFD / CSD coupling for transonic flutter solution is characterized by higher accuracy, but its disadvantage is that the numerical simulation process requires a lot of calculation and takes too long
However, the description method of the conventional composite material plate cannot meet the above requirements.
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[0087] The technical scheme of the present invention will be described in further detail below in conjunction with accompanying drawing and embodiment:
[0088] The following will take a certain type of aircraft composite empennage as an example to introduce the implementation process of the method for quickly obtaining the transonic flutter velocity of the composite airfoil according to the present invention. The steps of the process are:
[0089] 1. Firstly, subsonic flutter optimization is carried out on the aircraft wing skin. The optimization method and process adopt the national defense patent technical scheme previously applied for. The name of the patent application is: Aircraft wing skin subsonic flutter optimization method, patent The application number is: 201110171379.9. The main content of this technical solution is: use each skin element of the airfoil as the optimization object, and at the same time select the layer angle of the skin, the layer thickness incremen...
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The invention relates to a method for rapidly obtaining the speed of transonic flutter of a composite airfoil surface. The method comprises the following steps of: on the basis of the subsonic flutter optimization, selecting a finite number of airfoil surface sensitive areas to be known as sensitive elements, describing mechanical characteristics of the sensitive elements by using three-dimensional rigidity, further establishing three-dimensional rigidity feasible regions of the sensitive elements, selecting characteristic points in the rigidity feasible regions to calculate the unsteady aerodynamic force flutter, and respectively establishing transonic flutter speed response surfaces between each sensitive element and the whole composite airfoil surface according to a calculating result. In the subsequent flutter resolving, analyzing and optimizing process, the transonic flutter speed of the airfoil surface is obtained by inquiring the response surfaces, thus the long-time unsteady aerodynamic force flutter is replaced and the purposes of reducing the calculated amount and shortening the computing time are achieved.
Description
technical field [0001] The invention relates to a method for quickly obtaining the transonic flutter velocity of a composite airfoil, which belongs to the field of aeroelastic tailoring of an aircraft composite airfoil, and is used for the optimization of the transonic flutter velocity in the design of an aircraft composite airfoil. Background technique [0002] Transonic flutter of airfoil is an important aspect of airfoil design. In the process of transonic flutter analysis, it is an important step to obtain the critical velocity of transonic flutter. The general calculation of transonic flutter adopts the unsteady aerodynamic method, which requires a long calculation time and brings great difficulties to the optimization of the airfoil. At present, the optimization and analysis of transonic flutter of aircraft composite wing surfaces at home and abroad has not yet formed a mature technical solution. In the past, the critical velocity of transonic flutter of the airfoil w...
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IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 崔德刚杜海张睿熊青岳钱卫
Owner 中国航空工业集团公司科学技术委员会