CN118090127A - Device and method for measuring longitudinal gravity center and pitching inertia of full-machine wind tunnel test model - Google Patents
Device and method for measuring longitudinal gravity center and pitching inertia of full-machine wind tunnel test model Download PDFInfo
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Abstract
The application provides a device and a method for measuring longitudinal gravity center and pitching inertia of a full-machine wind tunnel test model, wherein the measuring device comprises the following components: the device comprises a rotating shaft support assembly, a model support body, a suspension clamp, a suspension spring and a dynamometer; the rotating shaft support assembly comprises a rotating shaft inner ring and a rotating shaft outer ring, the rotating shaft inner ring is fixedly connected with the rotating shaft support, and the rotating shaft outer ring is fixedly connected with the model support body; the model support body is manufactured into the all-machine wind tunnel test model; the hanging device is provided with a groove which is matched with the symmetrical plane structure of the tail structure of the full-aircraft wind tunnel test model, and is fixedly connected with the symmetrical plane structure of the tail structure of the full-aircraft wind tunnel test model, wherein hooks are respectively arranged on the upper surface and the lower surface of the hanging device; one end of the suspension device or the dynamometer is connected with the base on the top surface of the wind tunnel, and the other end of the suspension device or the dynamometer is connected to the hook of the suspension device. The application can effectively shorten the iterative design and verification period of the quality characteristics of the wind tunnel model.
Description
Technical Field
The application belongs to the field of aeroelastic wind tunnel tests, and particularly relates to a device and a method for measuring longitudinal gravity center and pitching inertia of a full-machine wind tunnel test model.
Background
When dynamic wind tunnel tests such as full-machine flutter tests, gust response tests and wind tunnel free flight are carried out, the mass/inertia characteristics of the full-machine need to be accurately simulated.
After the wind tunnel test model is manufactured, the quality characteristic data of the wind tunnel test model is required to be actually measured, the quality characteristic data is compared and analyzed with a design target, and then the counterweight design of the wind tunnel test model is completed based on the actually measured data, so that the wind tunnel test model and the full-size aircraft are ensured to strictly meet the established quality similarity ratio.
The existing wind tunnel test model mass center measurement is more in use of a suspension method and a multipoint support method. The suspension method is limited to a part wind tunnel test model with smaller size and weight, and has larger limitation on a whole-machine wind tunnel test model with larger size and weight; while the multipoint support method requires at least 3 or more weighing sensors and a special measuring platform, a special site and a measurement acquisition system are needed, and the requirement on the test environment is relatively high.
The inertia measurement of the existing wind tunnel test model mainly uses a torsion pendulum method. For a wind tunnel test model of a component with smaller mass and size, a soft thin wire can be used for suspending a test piece, the suspension direction is the same as the axis direction of the inertia moment of the measured mass, and the inertia of the test piece around a measuring shaft is reversely deduced by measuring the swing period of the test piece; for wind tunnel test models with larger mass and size, the inertia measurement of the wind tunnel test model can be completed only by means of a special test platform, and certain cost and period requirements exist, so that the balance weight iterative adjustment and quick verification of the wind tunnel test model are not facilitated.
Disclosure of Invention
The application aims to provide a device and a method for measuring longitudinal gravity center and pitching inertia of a full-machine wind tunnel test model, which are used for solving or relieving at least one problem in the background technology.
The technical scheme of the application is as follows: full-machine wind tunnel test model vertical focus and every single move inertia measuring device includes: the device comprises a rotating shaft support assembly, a model support body, a suspension clamp, a suspension spring and a dynamometer;
The rotating shaft support assembly comprises a rotating shaft inner ring and a rotating shaft outer ring, the rotating shaft inner ring is fixedly connected with the rotating shaft support, and the rotating shaft outer ring is fixedly connected with the model support body;
the model support body supports the all-machine wind tunnel test model;
The hanging clamp is provided with a groove which is matched with the symmetrical surface structure of the tail structure of the full-machine wind tunnel test model, and is fixedly connected with the symmetrical surface structure of the tail structure of the full-machine wind tunnel test model, wherein hooks are respectively arranged on the upper surface and the lower surface of the hanging clamp;
one end of the suspension spring or the dynamometer is connected with the base, and the other end of the suspension spring or the dynamometer is connected to the hook of the suspension clamp.
Preferably, the upper surface of the model support body is a flexible structure, and the flexible structure is mutually attached to the shape of the wind tunnel test model under the dead weight effect of the wind tunnel test model.
On the other hand, the technical scheme provided by the application is as follows: a measuring method adopting the measuring device for the longitudinal gravity center and the pitching inertia of the full-plane wind tunnel test model comprises the following steps:
Step one, connecting a model support body with an outer ring of a turntable bearing of a rotating shaft support assembly, mounting a suspension clamp on a symmetrical plane structure of a tail structure of a full-machine wind tunnel test model, placing the full-machine wind tunnel test model on the model support body, adjusting the position of the rotating shaft support assembly to enable a structural center line of the model support body to be positioned in the symmetrical plane of the full-machine wind tunnel test model structure, and connecting a dynamometer with a hook of the suspension clamp;
Step two, moving the dynamometer to enable the pitch angle of the full-machine wind tunnel test model to be equal to zero, and vertically fixing the dynamometer on the base;
Step three, obtaining a measured value of a dynamometer, and measuring the horizontal distance between the force line of the dynamometer and the y axis of a measurement coordinate system and the horizontal distance between the center of a rotating shaft support assembly and the y axis respectively;
step four, obtaining an x-axis coordinate of the gravity center of the full-machine wind tunnel test model under a measurement coordinate system according to the measured value of the dynamometer, the mass of the suspension clamp, the horizontal distance between the force line of the dynamometer and the y-axis of the measurement coordinate system and the horizontal distance between the center of the rotating shaft support assembly and the y-axis;
Fifthly, from the appearance digital model of the all-computer wind tunnel test model, measuring the coordinate value of the intersection point of the plumb line passing through the center of gravity and the appearance contour line of the symmetrical plane of the wind tunnel test model under the measuring coordinate system and the center of gravity of the suspension clamp under the measuring coordinate system when the pitch angle of the all-computer wind tunnel test model is zero;
Step six, moving the rotating shaft support assembly to the position right below the gravity center of the wind tunnel test model, connecting a suspension spring with a hook of a suspension clamp, vertically moving a base position of the suspension spring upwards to enable a pitch angle of the full-machine wind tunnel test model to be equal to zero, vertically fixing the suspension spring onto the base, and measuring the vertical distance between the rotating axis of the rotating shaft support assembly and the upper surface of a model support body;
Step seven, enabling the full-aircraft wind tunnel test model to do pitching motion around a rotating shaft of the rotating shaft support assembly, and measuring to obtain a pitching period of the full-aircraft wind tunnel test model;
Placing the whole wind tunnel test model on a model support body after being inverted, adjusting the position of the whole wind tunnel test model to enable a rotating shaft support assembly to be located right below the gravity center of the whole wind tunnel test model, connecting a suspension spring with a suspension clamp hook, vertically moving upwards the base position of the suspension spring to enable the pitch angle of the whole wind tunnel test model to be equal to zero, vertically fixing the suspension spring on the base, and measuring the vertical distance between the rotating shaft axis of the rotating shaft support assembly and the upper surface of the model support body;
step nine, enabling the full-aircraft wind tunnel test model to do pitching motion around a rotating shaft of the rotating shaft support assembly, and measuring to obtain a pitching period of the full-aircraft wind tunnel test model;
And step ten, calculating to obtain the pitching inertia of the full-locomotive wind tunnel test model and the y-direction coordinates of the mass of the full-locomotive wind tunnel test model according to the mass of the full-locomotive wind tunnel test model, the mass of the suspension clamp, the rotational inertia of the rotating shaft support assembly, the rigidity of the suspension spring and the parameters obtained in the step five to step nine.
Preferably, the x-axis coordinate of the gravity center of the all-mechanical wind tunnel test model under the measurement coordinate system is as follows:
Wherein F is a measurement value of a dynamometer;
m t is the mass of the suspension clamp;
m is the mass of the full-machine wind tunnel model;
x t is the horizontal distance between the force line of the dynamometer and the y-axis of the measurement coordinate system;
x h is the horizontal distance between the center of the rotating shaft support assembly and the y axis;
g is gravitational acceleration.
Preferably, the centroid y-direction coordinate of the all-plane wind tunnel test model is:
Wherein,
For measuring the distance between the center of gravity (force measuring meter force line) of the clamp and the center of gravity of the wind tunnel model in the x direction of a measurement coordinate system;
When the wind tunnel model is normally placed (the machine belly is downward), the distance between the rotation axis of the rotating shaft support assembly and the gravity center of the suspension clamp in the y direction of the measurement coordinate system;
when the wind tunnel model is placed upside down (the machine belly is upward), the distance between the rotation axis of the rotating shaft support assembly and the gravity center of the suspension clamp in the y direction of the measurement coordinate system;
k is the rigidity of the suspension spring;
T 1 is a pitching period of pitching motion of the full-machine wind tunnel test model around the rotating shaft of the rotating shaft support assembly;
T 2 is a pitching period of pitching motion of the inverted full-machine wind tunnel test model around the rotating shaft of the rotating shaft support assembly;
d 1 is the vertical distance between the rotating axis of the rotating shaft support assembly and the upper surface of the model support body;
d 2 is the vertical distance between the rotating shaft axis of the inverted rear rotating shaft support assembly and the upper surface of the model support body;
x t、yt is a coordinate value of the gravity center of the measuring suspension clamp under a measuring coordinate system;
y c1、yc2 is the y-direction coordinate of the intersection point of the plumb line passing through the center of gravity and the profile line of the structural symmetry plane of the wind tunnel test model in the measurement coordinate system.
Preferably, the pitch inertia of the all-computer wind tunnel test model is as follows:
Wherein J 0 is the rotational inertia of the rotating shaft support assembly combined by the rotating disc bearing outer ring and the model support body.
The measuring device provided by the application has the advantages of simple and reliable structure, low cost and easy realization, the measuring method has low requirements on the measuring field and the measuring elements, the test can be directly carried out based on the assembling platform after the wind tunnel model is manufactured and assembled, the model transfer and the assembly are not needed, the implementation is convenient, the balance weight parameters can be quickly adjusted on site according to the test result, the re-measurement and the verification are completed, the testing efficiency is high, and the iterative design and the verification period of the quality characteristics of the wind tunnel model can be effectively shortened.
Drawings
In order to more clearly illustrate the technical solution provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are merely some embodiments of the application.
FIG. 1 is a schematic diagram of a test model longitudinal center of gravity and pitch inertia measurement device according to the present application.
Fig. 2 is a schematic diagram of the principle of measuring the gravity center x position of the full-machine wind tunnel test model in the application.
FIG. 3 is a schematic diagram of the measurement mode of gravity center y-direction coordinates and pitching inertia around the gravity center of a normally placed full-machine wind tunnel test model in the application.
FIG. 4 is a schematic diagram of the gravity center y-direction coordinate and the pitching inertia measurement mode around the gravity center of the inverted full-machine wind tunnel test model.
FIG. 5 is a schematic diagram of an embodiment of the application for measuring the x-directional coordinates of the center of gravity of a full-machine wind tunnel test model.
FIG. 6 is a schematic diagram of a measurement implementation of the gravity center y-direction coordinate and the moment of inertia around the gravity center of a normally placed full-locomotive wind tunnel test model according to an embodiment of the present application.
FIG. 7 is a schematic diagram of an embodiment of the application for measuring the gravity center y-direction coordinates and the pitching inertia around the gravity center of an inverted full-machine wind tunnel test model.
Reference numerals:
10-measuring device
11-Spindle support assembly
12-Model support
13-Hanging clamp
14-Suspension spring
15-Dynamometer
20-Full-machine wind tunnel test model
21-Center of gravity
22-Level ground
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
The application provides a measuring method and a measuring device capable of rapidly measuring the longitudinal gravity center position of a full-machine wind tunnel test model with a symmetrical structure and the pitching inertia around the gravity center, which are based on a weight balance principle and a vibration method, the longitudinal gravity center position of the full-machine wind tunnel test model in a structural symmetry plane and the pitching inertia around the gravity center are rapidly calculated, and the measuring method and the measuring device are convenient to implement, simple to operate and high in efficiency and cost ratio.
As shown in fig. 1, the measuring device 10 provided by the application mainly comprises a rotating shaft support assembly 11, a model support body 12, a suspension clamp 13, a suspension spring 14 and a dynamometer 15.
The main body of the rotating shaft support assembly 11 is a rotating disc bearing, an inner ring of the rotating disc bearing is fixedly connected with the rotating shaft base, an outer ring of the rotating disc bearing is fixedly connected with the model supporting body 12, and the inner ring and the outer ring of the rotating disc bearing can rotate relatively.
The upper surface of the model support body 12 is of a flexible structure, the wind tunnel test model 20 is placed on the model support body 12, and the upper surface of the model support body 12 can be mutually attached to the shape of the wind tunnel test model 20 under the action of the dead weight of the wind tunnel test model 20.
The suspension clamp 13 is provided with a groove which is matched with the symmetrical surface structure of the tail structure of the wind tunnel test model, and is fixedly connected with the symmetrical surface structure of the tail structure. The upper and lower surfaces of the hanging clamp 13 are respectively provided with a hook, and the dynamometer 15 or the hanging spring 14 is connected with the hanging clamp 13 through the hooks.
Fig. 2 shows a method for measuring the longitudinal center of gravity and the pitch inertia of a full-machine wind tunnel test model by using the measuring device 10, which comprises the following steps:
Firstly, connecting a model support body 12 with an outer ring of a turntable bearing of a rotating shaft support assembly 11, mounting a suspension clamp 13 on a symmetrical plane structure of a tail structure of a full-machine wind tunnel test model, placing a full-machine wind tunnel test model 20 on the model support body 12, adjusting the position of the rotating shaft support assembly 11 to enable a structural center line of the model support body 12 to be positioned in the symmetrical plane of the full-machine wind tunnel test model structure, and connecting a dynamometer 15 with a hook of the suspension clamp 13;
step two, vertically moving the base position of the dynamometer 15 upwards to enable the pitch angle of the full-machine wind tunnel test model 20 to be equal to zero, and vertically fixing the dynamometer 15 on the base;
Step three, as shown in fig. 2, reading a force value F of the dynamometer 15, and measuring a horizontal distance x t between a force line of the dynamometer 15 and a y axis of a measurement coordinate system and a horizontal distance x h between a rotating shaft center of the rotating shaft support assembly 11 and the y axis respectively;
step four, calculating to obtain the x-axis coordinate of the gravity center 21 of the full-plane wind tunnel test model 20 under the measurement coordinate system according to the mass m of the full-plane wind tunnel test model 20, the mass m t of the suspension clamp 13 and the force value and the horizontal distance obtained in the step three:
Wherein g is gravitational acceleration;
Step five, as shown in fig. 3, from the appearance digital model of the full-plane wind tunnel test model 20, when the pitch angle of the full-plane wind tunnel test model is measured, the y-direction coordinates y c1 and y c2 of the intersection point of the plumb line passing through the center of gravity 21 and the appearance contour line at the structural symmetry plane of the wind tunnel test model are under a measurement coordinate system, and the coordinate value (x t,yt) of the center of gravity of the suspension clamp 13 under the measurement coordinate system is measured;
Step six, moving the rotating shaft support assembly 11 to the position right below the gravity center of the wind tunnel test model, connecting the suspension spring 14 with a hook of the suspension clamp 13, vertically moving the base position of the suspension spring 14 upwards to enable the pitch angle of the full-machine wind tunnel test model 20 to be equal to zero, vertically fixing the suspension spring 14 onto the base, and measuring the vertical distance d 1 between the rotating axis of the rotating shaft support assembly 11 and the upper surface of the model support body 12;
Step seven, enabling the full-automatic wind tunnel test model to perform small-amplitude pitching motion around the rotating shaft of the rotating shaft support assembly 11, and measuring to obtain a pitching period T 1 of the full-automatic wind tunnel test model 20;
Step eight, as shown in fig. 4, placing the whole wind tunnel test model on the model support 12 after being inverted, adjusting the position of the whole wind tunnel test model 20 to enable the rotating shaft support assembly 11 to be located right below the gravity center of the whole wind tunnel test model, connecting the hanging spring 14 with the hanging clamp 13 in a hanging way, vertically moving the base position of the hanging spring 14 upwards to enable the pitch angle of the whole wind tunnel test model 20 to be equal to zero, vertically fixing the hanging spring 14 on the base, and measuring the vertical distance d 2 between the rotating shaft axis of the rotating shaft support assembly 11 and the upper surface of the model support 12;
step nine, enabling the full-aircraft wind tunnel test model 20 to perform small-amplitude pitching motion around the rotating shaft of the rotating shaft support assembly 11, and measuring to obtain a pitching period T 2 of the full-aircraft wind tunnel test model;
Step ten, according to the mass m of the full-plane wind tunnel test model 20, the mass m t of the suspension clamp 13, the rotational inertia J 0 of the rotating shaft combined by the turntable bearing outer ring of the rotating shaft support assembly 11 and the model support body 12, the rigidity K of the suspension spring 14, the data x c obtained in the step four, the data y c1、yc2、xt、yt obtained in the step five, the distance d 1 obtained in the step six, the pitch period T 1 obtained in the step seven, the distance d 2 obtained in the step eighth and the pitch period T 2 obtained in the step nine, the pitch inertia J of the full-plane wind tunnel test model and the mass center y direction coordinate y c thereof are calculated according to the specific calculation formulas:
Barycenter y-coordinate:
pitch inertia:
Wherein:
for measuring the distance between the center of gravity (force measuring meter force line) of the clamp and the center of gravity of the wind tunnel model in the x direction of a measurement coordinate system;
When the wind tunnel model is normally placed (the machine belly is downward), the distance between the rotation axis of the rotating shaft support assembly and the gravity center of the suspension clamp in the y direction of the measurement coordinate system;
When the wind tunnel model is placed upside down (the machine belly is upward), the distance between the rotation axis of the rotating shaft support assembly and the gravity center of the suspension clamp in the y direction of the measurement coordinate system is measured.
The method process of the application is further described below with reference to specific parameters of the full-machine wind tunnel test model and the measuring device.
First, the mass m=80 kg of the fully-mechanical wind tunnel test model 20 symmetrical in structure is known, the mass m t =0.5 kg of the suspension clamp 13, the rotational inertia J 0＝0.0025kgm2 of the rotating shaft around the combination of the turntable bearing outer ring of the rotating shaft support assembly 11 and the model support body 12, and the rigidity k=600n/m of the suspension spring 14.
As shown in fig. 5 to 7, for the convenience of implementation, a three-dimensional model of the test piece is compared before testing, a measurement mark point P1 is arranged at the machine head of the symmetry plane of the whole wind tunnel test model structure, a measurement mark point P3 is arranged on the upper surface of the machine tail of the symmetry plane of the whole wind tunnel test model structure, a measurement mark point P2 is arranged on the lower surface of the machine tail of the symmetry plane of the whole wind tunnel test model structure, and the vertical distance ratio of each measurement mark point P1-P3 relative to a reference horizontal plane is H t1/Ht2/Ht3 =1/0.481/0.712 when the pitch angle of the whole wind tunnel test model is zero through digital-analog measurement.
The measuring method of the application comprises the following steps:
firstly, placing a full-machine wind tunnel test model 20 on a model support body 12, and adjusting the position of a rotating shaft support assembly 11 to enable a structural center line of the model support body to be positioned in a structural symmetry plane of the full-machine wind tunnel test model;
step two, connecting the dynamometer 15 with a hook of the suspension clamp 13 to construct an oxy coordinate system, wherein a round dot o of the coordinate system is positioned at a position 0.2m in front of a machine head of the full-aircraft wind tunnel test model, an x axis is parallel to the horizontal ground 2, a y axis is vertically upwards, a base position of the dynamometer 15 is vertically upwards moved, the distance H t1 = 0.52m between a machine head mark point P1 and the horizontal ground, the distance H t2 = 0.25m between a machine tail mark point P2 and the horizontal ground is achieved, and at the moment, the pitch angle of the full-aircraft wind tunnel test model 20 is zero, and the dynamometer is vertically fixed on the base;
Step three, reading f= 266.2N of the dynamometer 15, and simultaneously measuring the horizontal distance x t =2.2m between the force line of the dynamometer 15 and the y axis of the measurement coordinate system, and the horizontal distance x h =0.7m between the axis of the rotating shaft support assembly 11 and the y axis;
Step four, calculating to obtain the x coordinate value of the gravity center of the full-plane wind tunnel test model under a measurement coordinate system according to the horizontal distance obtained in the steps of the full-plane wind tunnel test model 20 mass m=80 kg, the suspension clamp 13 mass m t =0.5 kg:
Step five, referring to fig. 6, measuring the coordinate value (x t＝2.2m,yt =0.273 m) of the gravity center of the suspension clamp 13 in the measurement coordinate system from the figure digital model of the full-machine wind tunnel test model, when the pitch angle of the full-machine wind tunnel test model is zero, the y-direction coordinate y c1 =0.3 m and y c2 =0.648 m of the intersection point of the plumb line passing through the gravity center and the profile line of the structural symmetry plane of the full-machine wind tunnel test model in the measurement coordinate system;
Step six, moving the rotating shaft support assembly 11 to the position right below the gravity center of the full-machine wind tunnel test model, connecting the hanging spring 14 with the hanging clamp 13 in a hook manner, vertically moving the base position of the hanging spring 13 upwards, enabling the longitudinal coordinate value of the machine head marking point P1 under the measurement coordinate system to be y t7 =0.52 m, enabling the longitudinal coordinate value of the machine tail marking point P2 under the measurement coordinate system to be y t8 =0.25 m, enabling the pitch angle of the full-machine wind tunnel test model to be equal to zero, vertically fixing the hanging spring onto the base, and measuring the vertical distance d 1 =0.053 m between the rotating axis of the rotating shaft support assembly 11 and the upper surface of the support body 12;
Step seven, enabling the full-automatic wind tunnel test model to do a slight pitching motion around the rotating shaft of the rotating shaft support assembly 11, and taking an average value T 1 = 0.9835s of pitching periods of the full-automatic wind tunnel test model obtained by three measurements to reduce test errors;
step eight, referring to fig. 7, placing the full-machine wind tunnel test model on the model support 12 after being inverted, adjusting the position of the full-machine wind tunnel test model, enabling the rotating shaft support assembly 11 to be located right below the gravity center of the full-machine wind tunnel test model, enabling the hanging spring 14 to be connected with a hanging clamp 13 in a hanging mode, vertically moving the base position of the hanging spring 14 upwards, enabling the distance D t3 = 0.63m between a tail marking point P2 and the horizontal ground 22, enabling the distance D t1 = 0.48m between a machine head marking point P1 and the horizontal ground 22, enabling the pitch angle of the full-machine wind tunnel test model to be equal to zero degree, enabling the hanging spring to be vertically fixed on the base, and measuring the vertical distance D 2 = 0.053m between the rotating shaft core line of the rotating shaft support assembly 11 and the upper surface of the model support 12;
Step nine, enabling the full-aircraft wind tunnel test model to do a slight pitching motion around the rotating shaft of the rotating shaft support assembly 11, and taking an average value T 2 = 0.9808s of pitching periods of the full-aircraft wind tunnel test model obtained by three measurements to reduce test errors;
Tenth, the mass m=80 kg of the full-plane wind tunnel test model, the mass m t =0.5 kg of the suspension clamp 13, the moment of inertia J 0＝0.0025kgm2 of the combination of the turntable bearing outer ring of the rotating shaft support assembly 11 and the model support body 12 around the rotating shaft, the rigidity k=600n/m of the suspension spring 13, the data x c＝1.1999m、yc1＝0.3m、yc2＝0.648m、xt＝2.2m、yt =0.273 m and the horizontal distance d 1＝0.053m、d2 =0.053 m obtained in the previous steps, the pitch period T 1＝0.9835s、T2 = 0.9808s, and the pitch inertia J and the mass center y direction coordinate y c of the full-plane wind tunnel test model are calculated:
And finally obtaining the centroid coordinate x c＝1.1999m,yc = 0.4396m of the full-machine wind tunnel test model under the measurement coordinate system, and pitching inertia J= 11.242kgm 2 around the centroid.
The measuring device provided by the application has the advantages of simple and reliable structure, low cost and easy realization, the measuring method has low requirements on the measuring field and the measuring elements, the test can be directly carried out based on the assembling platform after the wind tunnel model is manufactured and assembled, the model transfer and the assembly are not needed, the implementation is convenient, the balance weight parameters can be quickly adjusted on site according to the test result, the re-measurement and the verification are completed, the testing efficiency is high, and the iterative design and the verification period of the quality characteristics of the wind tunnel model can be effectively shortened.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. The utility model provides a full-aircraft wind tunnel test model vertical focus and every single move inertia measuring device which characterized in that includes: the device comprises a rotating shaft support assembly, a model support body, a suspension clamp, a suspension spring and a dynamometer;
The rotating shaft support assembly comprises a rotating shaft inner ring and a rotating shaft outer ring, the rotating shaft inner ring is fixedly connected with the rotating shaft support, and the rotating shaft outer ring is fixedly connected with the model support body;
the model support body supports the all-machine wind tunnel test model;
The hanging clamp is provided with a groove which is matched with the symmetrical surface structure of the tail structure of the full-machine wind tunnel test model, and is fixedly connected with the symmetrical surface structure of the tail structure of the full-machine wind tunnel test model, wherein hooks are respectively arranged on the upper surface and the lower surface of the hanging clamp;
one end of the suspension spring or the dynamometer is connected with the base, and the other end of the suspension spring or the dynamometer is connected to the hook of the suspension clamp.
2. The device for measuring the longitudinal gravity center and the pitching inertia of the full-machine wind tunnel test model according to claim 1, wherein the upper surface of the model support body is of a flexible structure, and the flexible structure is mutually attached to the shape of the wind tunnel test model under the action of the dead weight of the wind tunnel test model.
3. A measurement method using the full-plane wind tunnel test model longitudinal center of gravity and pitch inertia measurement device according to claim 1 or 2, comprising:
Step one, connecting a model support body with an outer ring of a turntable bearing of a rotating shaft support assembly, mounting a suspension clamp on a symmetrical plane structure of a tail structure of a full-machine wind tunnel test model, placing the full-machine wind tunnel test model on the model support body, adjusting the position of the rotating shaft support assembly to enable a structural center line of the model support body to be positioned in the symmetrical plane of the full-machine wind tunnel test model structure, and connecting a dynamometer with a hook of the suspension clamp;
Step two, moving the dynamometer to enable the pitch angle of the full-machine wind tunnel test model to be equal to zero, and vertically fixing the dynamometer on the base;
Step three, obtaining a measured value of a dynamometer, and measuring the horizontal distance between the force line of the dynamometer and the y axis of a measurement coordinate system and the horizontal distance between the center of a rotating shaft support assembly and the y axis respectively;
step four, obtaining an x-axis coordinate of the gravity center of the full-machine wind tunnel test model under a measurement coordinate system according to the measured value of the dynamometer, the mass of the suspension clamp, the horizontal distance between the force line of the dynamometer and the y-axis of the measurement coordinate system and the horizontal distance between the center of the rotating shaft support assembly and the y-axis;
Fifthly, from the appearance digital model of the all-computer wind tunnel test model, measuring the coordinate value of the intersection point of the plumb line passing through the center of gravity and the appearance contour line of the symmetrical plane of the wind tunnel test model under the measuring coordinate system and the center of gravity of the suspension clamp under the measuring coordinate system when the pitch angle of the all-computer wind tunnel test model is zero;
Step six, moving the rotating shaft support assembly to the position right below the gravity center of the wind tunnel test model, connecting a suspension spring with a hook of a suspension clamp, vertically moving a base position of the suspension spring upwards to enable a pitch angle of the full-machine wind tunnel test model to be equal to zero, vertically fixing the suspension spring onto the base, and measuring the vertical distance between the rotating axis of the rotating shaft support assembly and the upper surface of a model support body;
Step seven, enabling the full-aircraft wind tunnel test model to do pitching motion around a rotating shaft of the rotating shaft support assembly, and measuring to obtain a pitching period of the full-aircraft wind tunnel test model;
Placing the whole wind tunnel test model on a model support body after being inverted, adjusting the position of the whole wind tunnel test model to enable a rotating shaft support assembly to be located right below the gravity center of the whole wind tunnel test model, connecting a suspension spring with a suspension clamp hook, vertically moving upwards the base position of the suspension spring to enable the pitch angle of the whole wind tunnel test model to be equal to zero, vertically fixing the suspension spring on the base, and measuring the vertical distance between the rotating shaft axis of the rotating shaft support assembly and the upper surface of the model support body;
step nine, enabling the full-aircraft wind tunnel test model to do pitching motion around a rotating shaft of the rotating shaft support assembly, and measuring to obtain a pitching period of the full-aircraft wind tunnel test model;
And step ten, calculating to obtain the pitching inertia of the full-locomotive wind tunnel test model and the y-direction coordinates of the mass of the full-locomotive wind tunnel test model according to the mass of the full-locomotive wind tunnel test model, the mass of the suspension clamp, the rotational inertia of the rotating shaft support assembly, the rigidity of the suspension spring and the parameters obtained in the step five to step nine.
4. A measurement method according to claim 3, wherein the x-axis coordinate x c of the center of gravity of the all-machine wind tunnel test model in the measurement coordinate system is:
Wherein F is a measurement value of a dynamometer;
m t is the mass of the suspension clamp;
m is the mass of the full-machine wind tunnel model;
x t is the horizontal distance between the force line of the dynamometer and the y-axis of the measurement coordinate system;
x h is the horizontal distance between the center of the rotating shaft support assembly and the y axis;
g is gravitational acceleration.
5. The measurement method of claim 4, wherein the centroid y-direction coordinates of the all-machine wind tunnel test model are:
Wherein,
The distance between the force measuring meter force line and the gravity center of the wind tunnel model in the x direction of a measurement coordinate system is measured;
when the wind tunnel model is normally placed, the distance between the rotating axis of the rotating shaft support assembly and the gravity center of the suspension clamp in the y direction of the measurement coordinate system;
when the wind tunnel model is placed upside down, the distance between the rotating axis of the rotating shaft support assembly and the gravity center of the suspension clamp in the y direction of the measuring coordinate system;
k is the rigidity of the suspension spring;
T 1 is a pitching period of pitching motion of the full-machine wind tunnel test model around the rotating shaft of the rotating shaft support assembly;
T 2 is a pitching period of pitching motion of the inverted full-machine wind tunnel test model around the rotating shaft of the rotating shaft support assembly;
d 1 is the vertical distance between the rotating axis of the rotating shaft support assembly and the upper surface of the model support body;
d 2 is the vertical distance between the rotating shaft axis of the inverted rear rotating shaft support assembly and the upper surface of the model support body;
x t、yt is the coordinate value of the gravity center of the suspension clamp under the measurement coordinate system;
y c1、yc2 is the y-direction coordinate of the intersection point of the plumb line passing through the center of gravity and the profile line of the structural symmetry plane of the wind tunnel test model in the measurement coordinate system.
6. The measurement method of claim 5, wherein the pitch inertia of the all-mechanical wind tunnel test model is:
Wherein J 0 is the rotational inertia of the rotating shaft support assembly combined by the rotating disc bearing outer ring and the model support body.
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