Ice shape prediction method and system at any moment

A technology of prediction method at any time, applied in the direction of design optimization/simulation, geometric CAD, etc., can solve the problems of icing ice shape at a single time point and the inability to obtain ice shape information during icing process, so as to improve reliability and utilization efficiency effect

Active Publication Date: 2020-07-10
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the problem that the icing wind tunnel test can only obtain the icing ice shape at a single time point, but cannot obtain the ice shape information during the icing process, the present invention provides an ice shape prediction method at any time, according to the evolution of ice shape characteristics during the icing process Combined with the ice shape of the icing wind tunnel test at a certain time, a set of methods for predicting the ice shape of the ice wind tunnel test at other times is established

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  • Ice shape prediction method and system at any moment
  • Ice shape prediction method and system at any moment
  • Ice shape prediction method and system at any moment

Examples

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Effect test

Embodiment 1

[0047] A method for predicting ice shape at any time, such as figure 1 described, including the following steps:

[0048] (1) Perform digital discrete processing on the test ice shape pictures to obtain a set of clean airfoil curve coordinates and ice shape curve coordinates;

[0049] (2) Calculate the characteristic parameters of the test ice shape;

[0050] Among them, the clean airfoil curve refers to the airfoil curve before icing, which represents the interface between the airfoil and the ice shape after icing;

[0051] The digital processing of ice shape pictures generally uses software such as getdata, and uses the ice shape map coordinate system to extract the coordinates of each point of the curve. The principle of extraction is to ensure that the shape of the reconstructed curve does not deform, take more points where the curve changes sharply, and take less points where the change is slow.

[0052] Since the curve is composed of infinite points, and in the proces...

Embodiment 2

[0068] A method for forecasting ice shape at any time, comprising the following steps:

[0069] (1) Perform digital discrete processing on the test ice shape pictures to obtain a set of clean airfoil curve coordinates and ice shape curve coordinates, such as Figure 4a shown;

[0070] (2) Calculate the characteristic parameters of the test ice shape;

[0071] Observed Figure 4a It can be determined that the ice shape is horn ice, and the characteristic parameters of the thickness of horn ice are calculated, such as Figure 4b :

[0072] Step 1: Divide the ice shape curve into upper and lower parts at the point where the ice thickness is smaller in the horn ice angle;

[0073] Step 2: Calculate the distance from each point of the two ice-shaped curves to the clean airfoil curve, the farthest point is the upper and lower ice corner points, and the point with the smallest distance from the airfoil between the two ice corner points is the stagnation point;

[0074] Step 3: C...

Embodiment 3

[0081] A method for forecasting ice shape at any time, comprising the following steps:

[0082] (1) Perform digital discrete processing on the test ice shape pictures to obtain a set of clean airfoil curve coordinates and ice shape curve coordinates, such as Figure 5a shown;

[0083] (2) Calculate the characteristic parameters of the test ice shape;

[0084] Observed Figure 5a It can be determined that the ice shape is the streamlined ice of sheep’s horn ice, and the characteristic parameters of the streamlined ice are calculated, such as Figure 5b :

[0085] Step 1: By calculating the distance from each point on the ice curve to the clean airfoil curve, the distance from the farthest point is the maximum icing thickness, and the corresponding airfoil coordinate point is the maximum icing point;

[0086] Step 2: Calculate the airfoil points corresponding to both ends of the ice shape curve, which are the upper and lower limits of icing;

[0087] (3) Use the icing calcu...

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Abstract

The invention is suitable for the technical field of wind tunnel tests, and discloses an ice shape prediction method and system at any moment, and the method comprises the following steps: (1), carrying out the digitalized discrete processing of a test ice shape image, and obtaining a group of clean airfoil curve coordinates and ice shape curve coordinates; (2) calculating characteristic parameters of the test ice shape; (3) determining a characteristic evolution rule; (4) calculating the ice shape at any moment in the icing process according to the ice shape characteristic evolution rule andthe ice shape curve. By the adoption of the method, the ice shape at any moment in the icing test process can be predicted, detail features of the test ice shape are reserved, the ice shapes at different moments can be rapidly obtained, the method can be used for evaluating aerodynamic characteristic changes in the icing process, and the utilization efficiency of test data is greatly improved.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel tests, in particular to an ice shape prediction method and system at any time. Background technique [0002] When passing through supercooled clouds, icing will occur on the surface of the aircraft, which will lead to performance degradation of the aircraft, control failure, and even flight accidents. In order to ensure flight safety, it is necessary to obtain the icing shape of the aircraft in the icing environment during the aircraft design process, evaluate its harm to the aerodynamic performance of the aircraft, and adopt certain methods to reduce or eliminate this adverse effect. [0003] Research on icing prediction and the effect of ice on aerodynamic characteristics generally includes flight tests under real icing weather conditions, icing numerical simulations and icing wind tunnel tests. The flight test cycle under real icing weather conditions is long and costly, and only limited d...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/20
Inventor 赵献礼易贤郭向东周靓
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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