阅读说明：本技术 一种高速抖振试验模型脉动压力测点布置方法 (Method for arranging pulsating pressure measuring points of high-speed buffeting test model ) 是由 张来 王永恩 管德会 陈振龙 闫盼盼 于 2021-08-05 设计创作，主要内容包括：本申请属于航空航天技术领域,特别涉及一种高速抖振试验模型脉动压力测点布置方法。包括：步骤一、获取飞机抖振迎角范围,飞机抖振迎角范围包括起始迎角以及失速迎角；步骤二、在飞机表面布置脉动压力测点；步骤三、从飞机抖振迎角范围中选取包括起始迎角以及失速迎角在内的多个典型迎角点,进行数值仿真,获取飞机表面动态压力特性曲线；步骤四、根据飞机表面动态压力特性曲线,筛选出压力脉动能量集中区域,作为风洞试验中抖振试验模型脉动压力测点布置位置。本申请的高速抖振试验模型脉动压力测点布置方法,能够准确覆盖特征位置、全面高效获取抖振特性,减少使用45％的脉动压力传感器,保证试验质量的同时,降低试验损耗,降低试验成本。(The application belongs to the technical field of aerospace, and particularly relates to a method for arranging pulsating pressure measuring points of a high-speed buffeting test model. The method comprises the following steps: the method comprises the following steps of firstly, obtaining a buffeting attack angle range of an airplane, wherein the buffeting attack angle range of the airplane comprises a starting attack angle and a stalling attack angle; secondly, arranging pulsating pressure measuring points on the surface of the airplane; selecting a plurality of typical attack angle points including an initial attack angle and a stall attack angle from the buffeting attack angle range of the airplane, carrying out numerical simulation, and obtaining a dynamic pressure characteristic curve of the surface of the airplane; and step four, screening out a pressure pulsation energy concentration area according to the dynamic pressure characteristic curve of the surface of the airplane, and using the pressure pulsation energy concentration area as the arrangement position of pulsating pressure measuring points of the buffeting test model in the wind tunnel test. The method for arranging the pulsating pressure measuring points of the high-speed buffeting test model can accurately cover the characteristic positions, comprehensively and efficiently obtain the buffeting characteristics, reduce the use of 45% of pulsating pressure sensors, reduce the test loss and reduce the test cost while ensuring the test quality.)

1. A method for arranging pulsating pressure measuring points of a high-speed buffeting test model is characterized by comprising the following steps:

the method comprises the following steps of firstly, obtaining a buffeting attack angle range of an airplane, wherein the buffeting attack angle range of the airplane comprises a starting attack angle and a stalling attack angle;

secondly, arranging pulsating pressure measuring points on the surface of the airplane;

selecting a plurality of typical attack angle points including an initial attack angle and a stall attack angle from the buffeting attack angle range of the airplane, carrying out numerical simulation, and obtaining a dynamic pressure characteristic curve of each pulsating pressure measuring point on the surface of the airplane;

and step four, screening out a pressure pulsation energy concentration area according to the aircraft surface dynamic pressure characteristic curve, and using the pressure pulsation energy concentration area as the arrangement position of pulsating pressure measuring points of a buffeting test model in a wind tunnel test.

2. The method for arranging pulsating pressure measuring points of a high-speed buffeting test model according to claim 1, wherein in the step one, the obtaining of the buffeting attack angle range of the airplane comprises the following steps:

obtaining typical Mach number and corresponding height of high-speed flight according to the flight envelope;

and determining the deviation of the longitudinal aerodynamic coefficient of the whole airplane from the original regular attack angle through numerical simulation to obtain the buffeting attack angle range of the airplane.

3. The method as claimed in claim 2, wherein the range of the buffeting attack angle of the airplane comprises the attack angle of the limited streamline separation zone on the surface of the airplane, the sharp change attack angle of the upper airfoil at 80% of the semi-span, the sharp change attack angle of the local chord at 95% of the local chord length, and the forward shift attack angle of the shock wave position at 60% of the semi-span.

4. The method for arranging the pulsating pressure measuring points of the high-speed buffeting test model according to claim 3, wherein in the second step, the arranging the pulsating pressure measuring points on the surface of the airplane comprises the following steps:

spreading and point distributing are carried out at the interval of 10% semi-span at the inner side of the fuselage;

carrying out spanwise distribution at intervals of 10% of half span at the inner side of the wing, and carrying out spanwise distribution at intervals of 5% of half span at the outer side of the wing;

carrying out axial distribution on a connecting line corresponding to the interval of 10% of the wing root at the local chord length;

and carrying out axial distribution on the engine body on a corresponding connecting line of 10 percent of the wing tip at the interval of the local chord length.

5. The method for arranging pulsating pressure measuring points of the high-speed buffeting test model according to claim 1, wherein in the fourth step, the step of screening out a pressure pulsation energy concentration area according to the aircraft surface dynamic pressure characteristic curve as the arrangement position of the pulsating pressure measuring points of the buffeting test model in the wind tunnel test comprises the following steps:

and extracting the root mean square of the pulsating pressure of each pulsating pressure measuring point from the dynamic pressure characteristic curve of the surface of the airplane, and taking the pulsating pressure measuring points with the root mean square of the pulsating pressure being larger than a first threshold value as the arrangement positions of the pulsating pressure measuring points of the buffeting test model in the wind tunnel test.

6. The method for arranging pulsating pressure measuring points of the high-speed buffeting test model according to claim 1, wherein in the fourth step, the step of screening out a pressure pulsation energy concentration area according to the aircraft surface dynamic pressure characteristic curve as the arrangement position of the pulsating pressure measuring points of the buffeting test model in the wind tunnel test comprises the following steps:

and extracting the power spectral density of each pulsating pressure measuring point from the aircraft surface dynamic pressure characteristic curve, and taking the pulsating pressure measuring points with the power spectral density being greater than a second threshold value as the arrangement positions of pulsating pressure measuring points of a buffeting test model in the wind tunnel test.

7. The method for arranging pulsating pressure measuring points of the high-speed buffeting test model according to claim 1, wherein in the fourth step, the step of screening out a pressure pulsation energy concentration area according to the aircraft surface dynamic pressure characteristic curve as the arrangement position of the pulsating pressure measuring points of the buffeting test model in the wind tunnel test comprises the following steps:

and extracting the sound pressure frequency spectrum of each pulsating pressure measuring point from the aircraft surface dynamic pressure characteristic curve, and taking the pulsating pressure measuring points with the sound pressure frequency spectrum larger than a third threshold value as the arrangement positions of the pulsating pressure measuring points of the buffeting test model in the wind tunnel test.

Technical Field

The application belongs to the technical field of aerospace, and particularly relates to a method for arranging pulsating pressure measuring points of a high-speed buffeting test model.

Background

In the process of high-speed flight of a real airplane, the surface airflow separation of the airplane, the interference of a shock wave boundary layer and other complex flow states often cause local pressure pulsation of the surface of the airplane, and buffeting is caused by a pulsating load action structure. When buffeting occurs, the aerodynamic characteristics of the airplane are seriously nonlinear, and the buffeting characteristics are difficult to find out through numerical simulation and theoretical analysis.

The wind tunnel test and the flight test result have good correlation, and the method is a better means for researching the buffeting phenomenon, and the conventional method is usually that a designer arranges a large number of pulsating pressure measuring points on wings and vertical tails according to experience to grope the buffeting characteristic, but the method has a plurality of defects: 1) characteristic points with intense pulsating pressure may be omitted; 2) the pulsating pressure sensor is easy to damage and expensive, which brings extra expenditure; 3) the layout is changed, and the traditional experience is not necessarily still instructive. In addition, the design space of the measuring points of the high-speed buffeting wind tunnel test model is small, the use cost of the pulsation pressure sensor is high, the strength requirement of the test model is high, and the number of the pulsation pressure measuring points is limited by the factors. How to accurately cover the characteristic position and comprehensively and efficiently acquire the buffeting characteristic by designers does not have a set of reasonable flow method at present.

Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.

Disclosure of Invention

The application aims to provide a method for arranging pulsating pressure measuring points of a high-speed buffeting test model so as to solve at least one problem in the prior art.

The technical scheme of the application is as follows:

a method for arranging pulsating pressure measuring points of a high-speed buffeting test model comprises the following steps:

the method comprises the following steps of firstly, obtaining a buffeting attack angle range of an airplane, wherein the buffeting attack angle range of the airplane comprises a starting attack angle and a stalling attack angle;

secondly, arranging pulsating pressure measuring points on the surface of the airplane;

selecting a plurality of typical attack angle points including an initial attack angle and a stall attack angle from the buffeting attack angle range of the airplane, carrying out numerical simulation, and obtaining a dynamic pressure characteristic curve of each pulsating pressure measuring point on the surface of the airplane;

and step four, screening out a pressure pulsation energy concentration area according to the aircraft surface dynamic pressure characteristic curve, and using the pressure pulsation energy concentration area as the arrangement position of pulsating pressure measuring points of a buffeting test model in a wind tunnel test.

In at least one embodiment of the present application, in step one, the obtaining the buffeting angle of attack range of the aircraft includes:

obtaining typical Mach number and corresponding height of high-speed flight according to the flight envelope;

and determining the deviation of the longitudinal aerodynamic coefficient of the whole airplane from the original regular attack angle through numerical simulation to obtain the buffeting attack angle range of the airplane.

In at least one embodiment of the present application, the range of buffeting angles of attack includes an angle of attack at the extreme streamline separation zone of the aircraft surface, a pressure sharp angle of attack at 80% of the semi-span of the upper airfoil surface, a pressure sharp angle of attack at 95% of the local chord length, and a forward angle of attack at the shock location at 60% of the semi-span.

In at least one embodiment of the present application, in step two, the arranging the pulsating pressure measuring points on the surface of the aircraft includes:

spreading and point distributing are carried out at the interval of 10% semi-span at the inner side of the fuselage;

carrying out spanwise distribution at intervals of 10% of half span at the inner side of the wing, and carrying out spanwise distribution at intervals of 5% of half span at the outer side of the wing;

carrying out axial distribution on a connecting line corresponding to the interval of 10% of the wing root at the local chord length;

and carrying out axial distribution on the engine body on a corresponding connecting line of 10 percent of the wing tip at the interval of the local chord length.

In at least one embodiment of the present application, in step four, the screening out a pressure pulsation energy concentration region according to the aircraft surface dynamic pressure characteristic curve, and the step of arranging, as a pulsating pressure measurement point arrangement position of a buffeting test model in a wind tunnel test, includes:

and extracting the root mean square of the pulsating pressure of each pulsating pressure measuring point from the dynamic pressure characteristic curve of the surface of the airplane, and taking the pulsating pressure measuring points with the root mean square of the pulsating pressure being larger than a first threshold value as the arrangement positions of the pulsating pressure measuring points of the buffeting test model in the wind tunnel test.

In at least one embodiment of the present application, in step four, the screening out a pressure pulsation energy concentration region according to the aircraft surface dynamic pressure characteristic curve, and the step of arranging, as a pulsating pressure measurement point arrangement position of a buffeting test model in a wind tunnel test, includes:

and extracting the power spectral density of each pulsating pressure measuring point from the aircraft surface dynamic pressure characteristic curve, and taking the pulsating pressure measuring points with the power spectral density being greater than a second threshold value as the arrangement positions of pulsating pressure measuring points of a buffeting test model in the wind tunnel test.

In at least one embodiment of the present application, in step four, the screening out a pressure pulsation energy concentration region according to the aircraft surface dynamic pressure characteristic curve, and the step of arranging, as a pulsating pressure measurement point arrangement position of a buffeting test model in a wind tunnel test, includes:

and extracting the sound pressure frequency spectrum of each pulsating pressure measuring point from the aircraft surface dynamic pressure characteristic curve, and taking the pulsating pressure measuring points with the sound pressure frequency spectrum larger than a third threshold value as the arrangement positions of the pulsating pressure measuring points of the buffeting test model in the wind tunnel test.

The invention has at least the following beneficial technical effects:

the method for arranging the pulsating pressure measuring points of the high-speed buffeting test model can accurately cover the characteristic positions, comprehensively and efficiently obtain the buffeting characteristics, reduce the use of 45% of pulsating pressure sensors, reduce the test loss and reduce the test cost while ensuring the test quality.

Drawings

FIG. 1 is a schematic diagram of a pulse pressure measurement point arrangement according to an embodiment of the present application;

FIG. 2 is a schematic view of an exemplary selection of an angle of attack point according to an embodiment of the present application;

FIG. 3 is a plot of survey point pulse pressure versus time for one embodiment of the present application;

FIG. 4 is a root mean square pressure diagram of the pulsating pressure measurement points according to one embodiment of the present application.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.

In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.

The present application is described in further detail below with reference to fig. 1 to 4.

The application provides a method for arranging pulsating pressure measuring points of a high-speed buffeting test model, which comprises the following steps:

the method comprises the following steps of firstly, obtaining a buffeting attack angle range of an airplane, wherein the buffeting attack angle range of the airplane comprises a starting attack angle and a stalling attack angle;

secondly, arranging pulsating pressure measuring points on the surface of the airplane;

selecting a plurality of typical attack angle points including an initial attack angle and a stall attack angle from a buffeting attack angle range of the airplane, carrying out numerical simulation, and obtaining a dynamic pressure characteristic curve of each pulsating pressure measuring point on the surface of the airplane;

and step four, screening out a pressure pulsation energy concentration area according to the dynamic pressure characteristic curve of the surface of the airplane, and using the pressure pulsation energy concentration area as the arrangement position of pulsating pressure measuring points of the buffeting test model in the wind tunnel test.

According to the method for arranging the pulsating pressure measuring points of the high-speed buffeting test model, the mode for determining the buffeting attack angle range of the airplane can be as follows: acquiring typical Mach number and corresponding height of high-speed flight according to a flight envelope of the airplane; and (3) determining that the longitudinal aerodynamic coefficient of the whole airplane deviates from the original regular attack angle through numerical simulation, thereby obtaining the buffeting attack angle range of the airplane. In one embodiment of the present application, the range of buffeting angles of attack may include: the aircraft surface limit streamline separation area has an attack angle, the pressure of the upper airfoil surface at 80% of the semi-span changes the attack angle greatly, the pressure of the upper airfoil surface at 95% of the local chord length changes the attack angle greatly, and the shock wave position at 60% of the semi-span shifts the attack angle forward.

According to the method for arranging the pulsating pressure measuring points of the high-speed buffeting test model, the upper surface pulsating pressure measuring points of the airplane are arranged by comprehensively considering the upper surface separation area and the shock wave position change area of the airplane. In a preferred embodiment of the present application, as shown in fig. 1, the pulsating pressure measuring points arranged on the surface of the aircraft comprise:

spreading and point distributing are carried out at the interval of 10% semi-span at the inner side of the fuselage;

carrying out spanwise distribution at intervals of 10% of half span at the inner side of the wing, and carrying out spanwise distribution at intervals of 5% of half span at the outer side of the wing;

carrying out axial distribution on a connecting line corresponding to the wing root (symmetrical plane) at an interval of 10% of the local chord length;

and carrying out axial distribution on the connecting line corresponding to the wing tip (90% semi-span) at the interval of 10% of the local chord length.

According to the method for arranging the pulsating pressure measuring points of the high-speed buffeting test model, a plurality of typical attack angle points are selected according to the range of the buffeting attack angles determined in the step one, the typical attack angle points comprise a buffeting starting attack angle and a stalling attack angle, and a curve of the pulsating pressure of each pulsating pressure measuring point along with the change of time is obtained through numerical simulation. In this embodiment, taking a lift coefficient curve as an example, a typical angle of attack point selection scheme is given as shown in fig. 2, and fig. 3 is a curve of the change of the pulsating pressure of a typical pulsating pressure measurement point with time.

According to the method for arranging the pulsating pressure measuring points of the high-speed buffeting test model, after the dynamic pressure characteristic curve of each pulsating pressure measuring point is obtained, the pressure pulsation energy concentrated area is screened, and therefore the measuring points required by the buffeting test model in the wind tunnel test are obtained. In a preferred embodiment of the application, the root mean square of the pulsating pressure of each pulsating pressure measuring point is extracted from a dynamic pressure characteristic curve of the surface of the airplane, and the pulsating pressure measuring points with the root mean square of the pulsating pressure being greater than a first threshold value are taken as the arrangement positions of the pulsating pressure measuring points of the buffeting test model in the wind tunnel test. FIG. 4 shows the measured point curve of the energy concentration region screened by the root mean square characteristic of the pulsating pressure. In another preferred embodiment of the application, the power spectral density of each pulsating pressure measuring point is extracted from the dynamic pressure characteristic curve of the aircraft surface, and the pulsating pressure measuring points with the power spectral density larger than the second threshold value are used as the arrangement positions of the pulsating pressure measuring points of the buffeting test model in the wind tunnel test. In a third preferred embodiment of the application, a sound pressure spectrum of each pulsating pressure measuring point is extracted from an aircraft surface dynamic pressure characteristic curve, and the pulsating pressure measuring points with the sound pressure spectrum larger than a third threshold value are used as the arrangement positions of the pulsating pressure measuring points of a buffeting test model in a wind tunnel test.

The method for arranging the pulsating pressure measuring points of the high-speed buffeting test model is a reasonable method for arranging the pulsating pressure measuring points of the high-speed buffeting test model according to a flow mechanism, can accurately cover characteristic positions and comprehensively and efficiently obtain buffeting characteristics, can be applied to a buffeting characteristic wind tunnel test of a high-stealth flying wing layout unmanned aerial vehicle, reduces the use of 45% of pulsating pressure sensors, reduces test loss while ensuring test quality and reduces test cost.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.