CN115510694B - Turbulent flow boundary layer aerodynamic optical effect inhibition method based on injection jet flow - Google Patents

Turbulent flow boundary layer aerodynamic optical effect inhibition method based on injection jet flow Download PDF

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CN115510694B
CN115510694B CN202211473071.4A CN202211473071A CN115510694B CN 115510694 B CN115510694 B CN 115510694B CN 202211473071 A CN202211473071 A CN 202211473071A CN 115510694 B CN115510694 B CN 115510694B
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flow
jet flow
boundary layer
injection jet
optical effect
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CN115510694A (en
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武春风
高政旺
李强
姜永亮
胡黎明
韩西萌
王旭锋
李振杰
胡灿
吕亮
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China Space Sanjiang Group Co Ltd
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Abstract

The invention provides a turbulent flow boundary layer pneumatic optical effect inhibition method based on injection jet flow, which comprises three steps of determining an injection jet flow disturbance function form, applying a jet flow disturbance function to a laminar flow section and defining a pneumatic optical inhibition evaluation index.

Description

Turbulent boundary layer aerodynamic optical effect inhibition method based on injection jet flow
Technical Field
The invention relates to the technical field of suppression of turbulent boundary layers of high-speed flow fields of aircrafts, in particular to a method for suppressing aerodynamic optical effects of turbulent boundary layers based on injection jet flow.
Background
When the imaging guidance aircraft flies at a high speed in the atmosphere, because of the high Mach number, the head of the aircraft can form a shock wave structure, and turbulent boundary layers, shearing layers and other phenomena can be generated near a window, so that the flow field near the window becomes extremely complex, interference is caused on an optical imaging detection system, and the target image is deviated, shaken and blurred, and the effect is called as an aerodynamic optical effect. With the development of the requirement of accurate guidance, the accurate guidance equipment has higher and higher requirements on the accuracy and timeliness of target information acquisition, so that the adoption of an optical imaging detection tracking technology becomes an inevitable trend for the development of the accurate guidance equipment in the future. Compared with traditional inertia and wireless terminal guidance and the like, the optical imaging detection method has the advantages of being high in precision, strong in anti-interference capacity and the like.
From the cross view of aerodynamics and optical engineering, the influence of wall flow, mixed layer flow, structure and the like on light deflection and optical path distribution is mainly researched by pneumatic optics. When light rays are transmitted in the air, the temperature field, the density field and the refractive index field in the flow field are not uniformly distributed in space and rapidly change along with time. Of these, the most important n-index and fluid density
Figure 904751DEST_PATH_IMAGE001
Satisfy the Gladstone-Dale formula
Figure 962837DEST_PATH_IMAGE002
And K is a Gladstone-Dale constant determined by the wavelength of light. How to inhibit the pneumatic optical effect and improve the detection precision of optical imaging is an urgent problem to be solved, and has important academic research significance and engineering application value.
In the prior art, in the literature entitled "Aero-optical analysis of a film-cooled optical window based on linear stability analysis" in journal of the American society for aviation and space, vol.57, no. 7, pages 2840-2850, the combined flow of the mixed layer and the wall boundary layer under the laminar flow assumption is simulated by using time and one-dimensional space under the condition that the influence of helium and carbon dioxide on the aerodynamic optical effect is considered, and the method indicates that the pneumatic optical effect is favorably weakened by the gas with lower density, but the efficiency of the method for weakening the aerodynamic optical effect is low. The patent with the application number of CN202110061040.7 discloses a constant blowing and sucking method for weakening the aerodynamic optical effect of a turbulent flow boundary layer, and the technical scheme indicates that the development of a flowing non-constant vortex can be suppressed by adopting constant blowing and sucking disturbance, and the aerodynamic optical effect value of a turbulent flow area is effectively weakened within a large control intensity range. However, the above technical solutions require the construction of extremely complex perturbation functions, and are difficult to implement in practical engineering applications. Generally speaking, the defects of low efficiency, low feasibility and complex disturbance function construction exist in the method of using common wall surface spraying and suction to realize the aerodynamic optical attenuation of the turbulent boundary layer.
In view of the above, there is a need to design an improved method for suppressing the aerodynamic optical effect of a turbulent boundary layer based on an injected jet to solve the above problems.
Disclosure of Invention
The invention aims to provide a turbulent boundary layer aerodynamic optical effect suppression method based on injection jet flow.
In order to achieve the purpose, the invention provides a turbulent boundary layer aerodynamic optical effect inhibition method based on injection jet, which comprises the following steps:
s1, determining an injection jet flow disturbance function form according to the flow direction position and the time effect when jet flow of a flat boundary layer is disturbed;
s2, applying a jet flow disturbance function to a laminar flow section;
and S3, calculating the pulsation speed by utilizing the downstream flow field speed to evaluate the pulsation energy of the mixed flow at the downstream of the laminar flow section, and taking the pulsation energy as an evaluation index of the inhibition of the pneumatic optical effect.
Preferably, in step S1, the form of the disturbance function of the injection jet is as follows:
Figure 680257DEST_PATH_IMAGE003
wherein, in the step (A),
Figure 308422DEST_PATH_IMAGE004
to representThe disturbance speed of the jet flow,
Figure 326057DEST_PATH_IMAGE005
Showing the incoming flow speed,
Figure 86203DEST_PATH_IMAGE006
Is a period time item,
Figure 822077DEST_PATH_IMAGE007
Is the natural frequency of the flow field.
Preferably, the specific steps of step S2 are: applying the jet flow disturbance function to the wall surface of the laminar flow section to ensure that the normal speed of the wall surface of the laminar flow section is equal to the normal speed of the jet flow section after the jet flow disturbance function is applied
Figure 224240DEST_PATH_IMAGE008
Replacing the velocity at the original wall of the laminar flow section
Figure 801108DEST_PATH_IMAGE009
。
Preferably, the signal of the disturbance function of the injection jet flow includes a sine function and a cosine function, and the sine function and the cosine function form a phase difference of the signal of the disturbance function of the injection jet flow.
Preferably, in step S3, the pulsation velocity is obtained by a moving average calculation, and the calculation formula of the pulsation velocity is:
Figure 935417DEST_PATH_IMAGE010
wherein, in the process,
Figure 158588DEST_PATH_IMAGE011
which represents the speed of the pulsation at time t,
Figure 364442DEST_PATH_IMAGE012
the velocity of the flow field at time t is indicated,
Figure 622248DEST_PATH_IMAGE013
represent
Figure 19469DEST_PATH_IMAGE014
Average speed over a moving average time.
Preferably, the
Figure 933198DEST_PATH_IMAGE013
The calculation formula of (c) is:
Figure 677163DEST_PATH_IMAGE015
。
preferably, in step S3, the accumulated pulse energy of the flow for a certain period of time is
Figure 258317DEST_PATH_IMAGE016
。
The beneficial effects of the invention are:
according to the turbulent flow boundary layer aerodynamic optical effect inhibition method based on the injection jet flow, the form of the injection jet flow disturbance function is determined firstly, then the jet flow disturbance function is applied to the laminar flow section, and the aerodynamic optical inhibition evaluation index is further calculated according to the result. The method provided by the invention can realize the purpose of reducing the pneumatic optical effect only by constructing a simple disturbance function, has the characteristics of easy implementation and high efficiency compared with the traditional mode of weakening the pneumatic optical effect by changing the structure and controlling blowing and sucking, and has great application value in academic research and engineering application.
Drawings
FIG. 1 is a flow chart of a turbulent boundary layer aerodynamic optical effect suppression method based on injection jet flow according to the invention;
FIG. 2 is a comparison of the vortex structure change of the turbulent boundary layer of the downstream flow field in a natural state and after the injection jet flow control is applied in the embodiment 1 of the present invention;
fig. 3 is a comparison of the pulse energy accumulated in the same time period for the downstream flow in the natural state and after the injection jet control is applied in example 1 of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in detail with reference to the accompanying drawings and specific embodiments.
It should be noted that, in order to avoid obscuring the present invention with unnecessary details, only the structures and/or processing steps closely related to the aspects of the present invention are shown in the drawings, and other details not closely related to the present invention are omitted.
In addition, it is also to be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Referring to fig. 1, the method for suppressing the aerodynamic optical effect of the turbulent boundary layer based on the injection jet flow, provided by the invention, includes the following steps:
s1, determining an injection jet flow disturbance function form:
the flow direction position and the time effect when the jet flow of the boundary layer of the flat plate is disturbed are given, and the following function is taken as a form of an injection jet flow disturbance function:
Figure 531167DEST_PATH_IMAGE017
wherein the content of the first and second substances,
Figure 179797DEST_PATH_IMAGE004
showing the disturbance velocity of jet flow,
Figure 461873DEST_PATH_IMAGE005
Shows the incoming flow velocity,
Figure 68173DEST_PATH_IMAGE006
Is a periodic time item,
Figure 511924DEST_PATH_IMAGE007
Is the natural frequency of the flow field; it should be noted that the signal of the disturbance function of the injection jet flow includes sine and cosine functions to form phase differences of the signal of the disturbance function of the injection jet flow, and the phase differences can have important influence on a turbulent flow boundary layer;
s2, applying a jet flow disturbance function to a laminar flow section:
applying a jet disturbance function to the wall surface of the laminar flow section to make the normal velocity of the wall surface of the laminar flow section after applying the jet disturbance function
Figure 134666DEST_PATH_IMAGE018
Replacing the original wall velocity
Figure 751592DEST_PATH_IMAGE009
Taking the wall surface speed as a boundary condition, and carrying out periodic updating along with time during calculation;
s3, defining the pulsating energy of mixing the original flow and the jet flow by using the speed of the downstream flow field as an evaluation index of the inhibition of the pneumatic optical effect:
the pulsation energy of mixed flow is evaluated by calculating the pulsation velocity by utilizing the downstream flow field velocity, the pulsation velocity is obtained by moving average calculation, and the calculation formula of the pulsation velocity is as follows:
Figure 543224DEST_PATH_IMAGE010
wherein the content of the first and second substances,
Figure 423455DEST_PATH_IMAGE011
which represents the speed of the pulsation at time t,
Figure 2335DEST_PATH_IMAGE012
the flow field velocity at time t is indicated,
Figure 328012DEST_PATH_IMAGE019
to represent
Figure 207107DEST_PATH_IMAGE020
The average velocity over the moving average time is calculated as:
Figure 54977DEST_PATH_IMAGE015
the cumulative pulse energy of the flow in a certain time T is defined as
Figure 91459DEST_PATH_IMAGE021
In the natural state of the flow field
Figure 722292DEST_PATH_IMAGE022
，
Figure 721472DEST_PATH_IMAGE023
Smaller indicates weaker aerodynamic optical effects.
The method for suppressing the aerodynamic optical effect of the turbulent boundary layer based on the injection jet flow is further described by combining a specific embodiment as follows:
example 1
The embodiment provides a control method based on injection jet flow, which comprises the following steps:
s1, determining an injection jet flow disturbance function form:
given the flow direction position and time effect when the jet flow of the boundary layer of the flat plate is disturbed, the following function is taken as a form of a disturbance function:
Figure 910883DEST_PATH_IMAGE017
wherein the content of the first and second substances,
Figure 995513DEST_PATH_IMAGE024
showing the disturbance speed of jet flow,
Figure 633299DEST_PATH_IMAGE005
Shows the incoming flow velocity,
Figure 191713DEST_PATH_IMAGE006
Is a period time item,
Figure 787910DEST_PATH_IMAGE007
The natural frequency of the flow field, in this embodiment
Figure 592793DEST_PATH_IMAGE025
(ii) a It should be noted that the signal of the disturbance function of the injection jet flow includes sine and cosine functions to form phase differences of the signal of the disturbance function of the injection jet flow, and the phase differences can have important influence on a turbulent flow boundary layer;
s2, applying a jet flow disturbance function to a laminar flow section:
applying a jet disturbance function to the wall surface of the laminar flow section to ensure that the normal speed of the wall surface of the laminar flow section after the jet disturbance function is applied
Figure 565428DEST_PATH_IMAGE018
Replacing velocity at the original wall
Figure 335938DEST_PATH_IMAGE009
Taking the wall surface speed as a boundary condition, and carrying out periodic updating along with time during calculation;
s3, in the downstream of the laminar flow section, defining pulsating energy of mixing of the original flow and the jet flow by using the downstream flow field speed as an evaluation index of the inhibition of the pneumatic optical effect:
the pulsation energy of mixed flow is evaluated by calculating the pulsation velocity by utilizing the downstream flow field velocity, the pulsation velocity is obtained by moving average calculation, and the calculation formula of the pulsation velocity is as follows:
Figure 634195DEST_PATH_IMAGE010
wherein the content of the first and second substances,
Figure 855268DEST_PATH_IMAGE011
which represents the speed of the pulsation at time t,
Figure 162753DEST_PATH_IMAGE012
the velocity of the flow field at time t is indicated,
Figure 522190DEST_PATH_IMAGE019
to represent
Figure 286621DEST_PATH_IMAGE026
The average velocity over the moving average time is calculated as:
Figure 629878DEST_PATH_IMAGE015
in the embodiment, 2 times of the unstable period of the flow field in the natural state is selected as the moving average time; the cumulative pulse energy of the flow in a certain time T is defined as
Figure 741054DEST_PATH_IMAGE027
In this embodiment, T =320s is selected as the time for accumulating the pulsation energy in the flow field, and the flow field is in a natural state
Figure 892680DEST_PATH_IMAGE028
Calculating the pulsating energy of the mixed flow
Figure 595057DEST_PATH_IMAGE029
。
In the embodiment, the vortex structure change of the turbulent boundary layer of the downstream flow field in a natural state and after the injection jet flow control is applied is shown in fig. 2, and it can be seen from fig. 2 that the flow field applied with the jet flow control has no large-scale vortex structure, the flow is more regular, and the result shows that the jet flow disturbance can effectively inhibit the large-scale vortex structure development of the downstream boundary layer. In this embodiment, the pulse energy accumulated in the time of the downstream flow in the natural state and after the injection jet flow control is applied is reduced by 23% from fig. 3 to that after the jet flow can be applied in the natural state, as shown in fig. 3.
In summary, the turbulent boundary layer aerodynamic optical effect suppression method based on injection jet flow provided by the invention comprises three steps of determining an injection jet flow disturbance function form, applying the jet flow disturbance function to a laminar flow section and defining an aerodynamic optical suppression evaluation index.
Although the present invention has been described in detail with reference to the preferred embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the spirit and scope of the present invention.

Claims (6)

1. A turbulent boundary layer aerodynamic optical effect suppression method based on injection jet flow is characterized by comprising the following steps:
s1, determining an injection jet flow disturbance function form according to the flow direction position and the time effect when jet flow of a flat boundary layer is disturbed, wherein the injection jet flow disturbance function form is as follows:
Figure DEST_PATH_IMAGE001
wherein, in the step (A),
Figure 952537DEST_PATH_IMAGE002
showing the disturbance speed of jet flow,
Figure DEST_PATH_IMAGE003
Shows the incoming flow velocity,
Figure 591329DEST_PATH_IMAGE004
Is a periodic time item,
Figure DEST_PATH_IMAGE005
Is the natural frequency of the flow field;
s2, applying a jet flow disturbance function to a laminar flow section;
and S3, calculating the pulsation speed by utilizing the downstream flow field speed to evaluate the pulsation energy of the mixed flow at the downstream of the laminar flow section, and taking the pulsation energy as an evaluation index of the inhibition of the pneumatic optical effect.
2. The turbulent boundary layer aero-optical effect suppression method based on injection jet flow according to claim 1, wherein the step S2 specifically comprises the following steps: applying the jet flow disturbance function to the wall surface of the laminar flow section to ensure that the normal velocity of the wall surface of the laminar flow section is the normal velocity after the jet flow disturbance function is applied
Figure 517697DEST_PATH_IMAGE006
Replacing the velocity at the original wall of the laminar flow section
Figure DEST_PATH_IMAGE007
。
3. The method for suppressing the aerodynamic optical effect of the turbulent boundary layer based on the injection jet flow according to claim 2, wherein the signal of the disturbance function of the injection jet flow comprises a sine function and a cosine function, and the sine function and the cosine function form a phase difference of the signal of the disturbance function of the injection jet flow.
4. The method for suppressing the aerodynamic optical effect of the turbulent boundary layer based on the injection jet flow according to the claim 1, wherein in the step S3, the pulsation velocity is obtained by a moving average calculation, and the calculation formula of the pulsation velocity is as follows:
Figure 627342DEST_PATH_IMAGE008
wherein, in the step (A),
Figure DEST_PATH_IMAGE009
indicating pulsation at time tThe speed of the motor is controlled by the speed of the motor,
Figure 777700DEST_PATH_IMAGE010
the velocity of the flow field at time t is indicated,
Figure DEST_PATH_IMAGE011
represent
Figure 841471DEST_PATH_IMAGE012
Average speed over a moving average time.
5. The method for suppressing aerodynamic optical effects of turbulent boundary layers based on injected jets of claim 4, wherein the method comprises
Figure DEST_PATH_IMAGE013
The calculation formula of (A) is as follows:
Figure 102688DEST_PATH_IMAGE014
。
6. the method for suppressing the aero-optical effect of the turbulent boundary layer based on the injection jet flow according to the claim 1, wherein in the step S3, the accumulated pulse energy of the flow in a certain time T is
Figure DEST_PATH_IMAGE015
。
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