CN112747893A - Distributed six-component aerodynamic force measurement method - Google Patents
Distributed six-component aerodynamic force measurement method Download PDFInfo
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- CN112747893A CN112747893A CN202011591730.5A CN202011591730A CN112747893A CN 112747893 A CN112747893 A CN 112747893A CN 202011591730 A CN202011591730 A CN 202011591730A CN 112747893 A CN112747893 A CN 112747893A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L11/00—Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group G01L7/00 or G01L9/00
Abstract
The invention provides a distributed six-component aerodynamic force measuring method, which is based on an air floatation or suspension supporting mode, wherein a plurality of sensors are arranged in the directions of normal force, axial force and lateral force, and the axial force, the normal force, the lateral force, the rolling moment, the yawing moment and the pitching moment which are applied to a test model are obtained through calculation.
Description
Technical Field
The invention belongs to the field of aerodynamic force measurement methods for wind tunnel tests, and particularly relates to a distributed six-component aerodynamic force measurement method.
Background
The wind tunnel test is one of three aerodynamic research means and plays an important role in the development process of the aircraft. And the Low-speed wind tunnel (wind tunnel with the wind speed of the test section less than 140 m/s) has a tighter relationship with the national economy construction, and can be widely applied to various aspects such as building design, transportation, sports competition and the like. Particularly, in the aspect of competitive sports, with the rapid advance of the action plan of science and technology winter and technology (2022), the concept of science and technology assisted Olympic games is gradually deepened, and the competitive sports are developed into high-technology competition throughout the stage of the world of the contemporary competitive sports.
Taking the current potential advantage project racing boat in China as an example, the potential advantage project racing boat can obtain better ranking for many times in major competitions such as Olympic games, world championships and the like, shows higher competitive level, but has less times of entering the first three and even capturing gold medals, and the development of the potential advantage project racing boat can meet the bottleneck. Therefore, when the output power of athletes almost reaches the physiological capacity limit and the energy utilization rate almost reaches the extreme of excellent racing boat technology, on the premise of ensuring that the gliding power is not influenced, the reduction of the aerodynamic resistance is an important breakthrough point, and the wind tunnel experiment is one of very important means for researching the aerodynamic drag reduction. In addition to other racing sports such as field bikes, short track speed skating, snow and rudder racing, the difference in performance between high-level athletes is sometimes only on the order of milliseconds. The air resistance experienced by sports equipment and athletes in these sports has a non-negligible effect on athletic performance. By means of wind tunnel experiment tests, theoretical basis and data support can be provided for instrument shape optimization and guidance of athlete training and competitive actions, so that air resistance is reduced through optimization design, and achievement is improved finally.
As the precision requirement on resistance measurement data in low-speed wind tunnel experiments of various sports equipment is high, and the load measurement range is small, the requirements cannot be met by adopting conventional test equipment, and a mature test device does not exist in China.
Disclosure of Invention
The invention aims to overcome the defects and provides a distributed six-component aerodynamic force measuring method, which utilizes a plurality of force sensors distributed in the normal direction, the axial direction and the lateral direction to calculate the axial force, the normal force, the lateral force, the rolling moment, the yawing moment and the pitching moment of a test model, meets the test requirements of a large-scale heavy model and a small-load high-precision force measuring test, and can be applied to the small-load aerodynamic force measurement of a low-speed wind tunnel force measuring test.
In order to achieve the above purpose, the invention provides the following technical scheme:
a distributed six-component aerodynamic force measuring method is realized by adopting an air floatation wind tunnel test device, wherein the air floatation wind tunnel test device comprises a fixed frame, a floating frame and an air floatation supporting device;
the floating frame floats above the fixed frame through the air floating support device, the test model is fixed on the floating frame, and the aerodynamic force acting on the test model is transmitted to the sensor through the movement of the floating frame to realize measurement;
the air floatation supporting device comprises a platform assembly, an air floatation block and an air floatation screw rod;
the platform assembly is fixedly arranged on the upper surface of the fixed frame and comprises a horizontal adjusting structure at the lower part and an air floatation supporting platform at the upper part, the horizontal adjusting structure is used for adjusting the levelness of the air floatation supporting platform, and the air floatation supporting platform is used for converting air injection pressure into supporting force for an air floatation block;
the air floatation block is arranged above the air floatation supporting platform, and the lower surface of the air floatation block is in contact with the upper surface of the air floatation supporting platform;
the lower surface of the air floatation block is provided with an air outlet, the inside of the air floatation block is provided with a ventilation channel, the ventilation channel is connected with an external compressed air inlet and the air outlet, and compressed air is sprayed downwards through the air outlet so as to enable the air floatation block to float upwards;
the lower end of the air floatation screw is connected with the upper surface of the air floatation block through a spherical hinge, so that the air floatation screw has three rotational degrees of freedom; the floating frame is fixed on the air floating screw, and the floating frame is driven to float upwards when the air floating block floats upwards;
the method comprises the following specific steps:
s1, mounting a normal force sensor, an axial force sensor and a lateral force sensor in the air floatation wind tunnel test device;
s2 reading the measurement result of each sensor;
s3, calculating the axial force, the normal force, the lateral force, the roll moment, the yaw moment and the pitch moment of the test model according to the measurement result of each sensor.
Further, in step S1,
the normal force sensors are divided into four groups and are fixed on the floating frame, and the positions between the normal force sensor group y1 and the normal force sensor group y2, and between the normal force sensor group y3 and the normal force sensor group y4 are symmetrical about a symmetry axis passing through the center Z direction of the floating frame; symmetry is achieved between the normal force sensor group y1 and the normal force sensor group y4, between the normal force sensor group y2 and the normal force sensor group y3 with respect to a symmetry axis passing through the center X of the floating frame;
the axial force sensors are divided into two groups and are simultaneously connected with the fixed frame and the floating frame, and the axial force sensor group x1 and the axial force sensor group x2 are symmetrical about a symmetrical axis in the Z direction of the center of the fixed frame;
the lateral force sensors are divided into four groups and are simultaneously connected with the fixed frame and the floating frame, and the positions between the lateral force sensor group Z1 and the lateral force sensor group Z2, and between the lateral force sensor group Z3 and the lateral force sensor group Z4 are symmetrical about a symmetrical axis passing through the center Z direction of the floating frame; the symmetry axes between the lateral force sensor group z1 and the lateral force sensor group z4, and between the lateral force sensor group z2 and the lateral force sensor group z3 are symmetrical with respect to the symmetry axis passing through the center X of the floating frame;
in step S2, reading the measurement results Y1, Y2, Y3, Y4 of the normal force sensor group, the measurement results X1 and X2 of the axial force sensor group, and the measurement results Z1, Z2, Z3 and Z4 of the lateral force sensor group;
in step S3, the method for calculating the axial force, the normal force, the lateral force, the roll moment, the yaw moment and the pitch moment applied to the test model includes:
axial force a ═ X1-X2;
normal force N ═ Y1+ Y2+ Y3+ Y4;
the lateral force Z is Z1+ Z2-Z3-Z4;
roll torque MX ═ L2 × (Y1+ Y2-Y3-Y4);
yaw moment MY ═ L1 × (Z1+ Z4-Z2-Z3);
a pitching moment MZ ═ L1 × (Y1+ Y4-Y2-Y3);
the L2 is the distance between each group of normal force sensors in the Z direction, and the L1 is the distance between each group of lateral force sensors in the X direction;
and the X, Y and Z directions are the directions of X, Y and Z axes in the coordinate system of the air floatation wind tunnel test device.
The coordinate system of the air floatation wind tunnel test device takes the central point of the floating frame 2 as the original point, the axial force direction of the test model is the X axis, the normal force direction of the test model is the Y axis, and the lateral force direction of the test model is the Z axis.
Further, in step S1, each of the normal force sensor group, the axial force sensor group and the lateral force sensor group includes at least one corresponding sensor; the measurement results of each group of normal force sensor group, axial force sensor group and lateral force sensor group are the synthesis of the measurement results of all sensors included in each group of normal force sensor group, axial force sensor group and lateral force sensor group.
Furthermore, the horizontal adjusting structure is a supporting rod; the lower end of the support rod is fixedly arranged on the upper surface of the fixed frame, and the upper end of the support rod is fixedly connected with the lower surface of the air floatation support platform.
Further, in step S1, a mold connecting member is provided at an upper portion of the normal sensor for fixing the test mold.
Furthermore, the model connecting piece is provided with threads and is fixedly connected with the test model through the threads.
Furthermore, the floating frame floats above the fixed frame through the air floating support device, and the height of the floating frame is 20-50 mu m.
Furthermore, the height of the floating frame floating above the fixed frame through the air floating supporting device is kept unchanged in the testing process.
Further, in step S1, the axial force sensor group and the lateral force sensor group are fixed on the fixed frame and connected to the floating frame through the steel wire rope.
Furthermore, the length of the steel wire soft rope is more than or equal to 0.5m, and the diameter is more than or equal to 0.5 mm.
Compared with the prior art, the invention has the following beneficial effects:
(1) in the distributed six-component aerodynamic force measuring method, the sensors are convenient to install in the distribution mode of the normal force direction sensor, the axial force direction sensor and the lateral force direction sensor, the processing amount is small, and the cost is low;
(2) the measuring method is based on an air floatation or suspension supporting mode, avoids interference on aerodynamic force, improves the aerodynamic force measuring precision of a measured object, and can effectively improve the testing capability of the low-speed wind tunnel.
(3) The invention can match the test model according to the measured load, the measuring range of the sensor can be selected according to the requirement, and the application range is wide.
(4) The invention obtains the axial force, the normal force, the lateral force, the rolling moment, the yawing moment and the pitching moment which are applied to the test model through calculation based on utilizing a plurality of sensors distributed in the directions of the normal force, the axial force and the lateral force, has simple calculation method, can meet the test model with the magnitude of 10m and the range of 1000kg, and can accurately measure the resistance within the range of 100N.
Drawings
FIG. 1 is a sensor profile for a distributed six-component aerodynamic force measurement method of the present invention;
FIG. 2 is a schematic view of an air floatation support device according to the present invention;
FIG. 3 is a schematic diagram of an air-flotation wind tunnel test device according to the present invention.
Detailed Description
The features and advantages of the present invention will become more apparent and appreciated from the following detailed description of the invention.
The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. While the various aspects of the embodiments are presented in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
A distributed six-component aerodynamic force measuring method is realized by adopting an air-flotation wind tunnel test device, as shown in figure 3, the air-flotation wind tunnel test device comprises a fixed frame 1, a floating frame 2 and an air-flotation supporting device 16;
the floating frame 2 floats above the fixed frame 1 through the air floating supporting device 16, the test model is fixed on the floating frame 2, and the aerodynamic force acting on the test model is transmitted to the sensor through the movement of the floating frame 2 to realize measurement;
as shown in fig. 2, the air supporting device 16 comprises a platform assembly 18, an air block 4 and an air floating screw 5;
the platform assembly 18 is fixedly arranged on the upper surface of the fixed frame 1 and comprises a horizontal adjusting structure 3 at the lower part and an air floatation supporting platform 17 at the upper part, the horizontal adjusting structure 3 is used for adjusting the levelness of the air floatation supporting platform, and the air floatation supporting platform 17 is used for converting air injection pressure into supporting force for the air floatation block 4;
the air floatation block 4 is arranged above the air floatation supporting platform 17, and the lower surface of the air floatation block 4 is contacted with the upper surface of the air floatation supporting platform 17;
the lower surface of the air floating block 4 is provided with an air outlet, the inside of the air floating block is provided with a ventilation channel, the ventilation channel is connected with an external compressed air inlet and an air outlet, and compressed air is sprayed downwards through the air outlet so as to enable the air floating block 4 to float upwards;
the lower end of the air floatation screw rod 5 is connected with the upper surface of the air floatation block 4 through a spherical hinge, so that the air floatation screw rod 5 has three rotational degrees of freedom relative to the upper surface of the air floatation block 4; the floating frame 2 is fixed on the air floating screw 5, and the floating block 4 drives the floating frame 2 to float upwards when floating upwards;
the method comprises the following specific steps:
s1, mounting a normal force sensor, an axial force sensor and a lateral force sensor in the air floatation wind tunnel test device;
s2 reading the measurement result of each sensor;
s3, calculating the axial force, the normal force, the lateral force, the roll moment, the yaw moment and the pitch moment of the test model according to the measurement result of each sensor.
Further, as shown in fig. 1, the normal force sensors are divided into four groups and fixed on the floating frame 2, and the groups between the normal force sensors y1 and y2, and between the normal force sensors y3 and y4 are symmetrical with respect to the symmetry axis passing through the center Z direction of the floating frame; symmetry is achieved between the normal force sensor group y1 and the normal force sensor group y4, between the normal force sensor group y2 and the normal force sensor group y3 with respect to a symmetry axis passing through the center X of the floating frame;
the axial force sensors are divided into two groups and are simultaneously connected with the fixed frame 1 and the floating frame 2, and the axial force sensor group x1 and the axial force sensor group x2 are symmetrical about a symmetrical axis in the Z direction of the center of the fixed frame;
the lateral force sensors are divided into four groups and are simultaneously connected with the fixed frame 1 and the floating frame 2, and the groups between the lateral force sensors Z1 and the lateral force sensors Z2 and between the lateral force sensors Z3 and the lateral force sensors Z4 are symmetrical about a symmetrical axis passing through the center Z direction of the floating frame; the symmetry axes between the lateral force sensor group z1 and the lateral force sensor group z4, and between the lateral force sensor group z2 and the lateral force sensor group z3 are symmetrical with respect to the symmetry axis passing through the center X of the floating frame;
in step S2, the test model applies a load to the floating frame 2 to cause the signals of the sensors in each group to change, and reads the measurement results Y1, Y2, Y3, Y4 of the normal force sensor group, the measurement results X1, X2 of the axial force sensor group, and the measurement results Z1, Z2, Z3, Z4 of the lateral force sensor group;
in the step S3, the axial force, the normal force, the lateral force, the roll moment, the yaw moment and the pitch moment, which are applied to the test model, are calculated respectively:
axial force a ═ X1-X2;
normal force N ═ Y1+ Y2+ Y3+ Y4;
the lateral force Z is Z1+ Z2-Z3-Z4;
roll torque MX ═ L2 × (Y1+ Y2-Y3-Y4);
yaw moment MY ═ L1 × (Z1+ Z4-Z2-Z3);
a pitching moment MZ ═ L1 × (Y1+ Y4-Y2-Y3);
the L2 is the distance between each group of normal force sensors in the Z direction, and the L1 is the distance between each group of lateral force sensors in the X direction;
and the X, Y and Z directions are the directions of X, Y and Z axes in the coordinate system of the air floatation wind tunnel test device.
The coordinate system of the air floatation wind tunnel test device takes the central point of the floating frame 2 as the original point, the axial force direction of the test model is the X axis, the normal force direction of the test model is the Y axis, and the lateral force direction of the test model is the Z axis.
Further, in step S1, each of the normal force sensor group, the axial force sensor group and the lateral force sensor group includes at least one corresponding sensor; the measurement results of each group of normal force sensor group, axial force sensor group and lateral force sensor group are the synthesis of the measurement results of all sensors included in each group of normal force sensor group, axial force sensor group and lateral force sensor group.
Further, as shown in fig. 2, the horizontal adjusting structure 3 is a support rod; the lower end of the support rod is fixedly arranged on the upper surface of the fixed frame 1, and the upper end of the support rod is fixedly connected with the lower surface of the air floatation support platform 17.
Furthermore, in the air floatation supporting device, the number of the supporting rods is more than or equal to 3; the air-floating supporting platform 17 is of a plate-shaped structure, the levelness of the upper surface is less than or equal to 1', and the roughness is less than or equal to 1.6 um; the air-floating supporting platform 17 is made of marble or steel plate; the support rod is a positive and negative thread support rod.
Further, as shown in fig. 2, the floating frame 2 is fixed on the floating screw rod 5 by using a floating nut 6 and a connecting screw 7, and is fastened and positioned below by using a fastening nut 8. Before the air supporting block 4 is installed, the fastening nut 8 is screwed in from the top end of the air supporting screw rod 5, the lower end of the air supporting screw rod 5 is fixedly connected with the air supporting block 4 through a spherical hinge, the air supporting screw rod 5 is driven by the air supporting block 4 to be screwed in from the lower end of the air supporting nut 6, the lower surface of the air supporting block 4 is in contact with the upper surface of the marble platform assembly 3, and the air supporting block is not ventilated.
Further, as shown in fig. 2, the platform assembly 18 is fixed to the fixed frame 1 using the connection bolt 9.
Further, as shown in fig. 2, the floating frame 2 is placed on a marble table by an air floating block 4. When high-pressure air is introduced into the air floating block, the air floating block 4 drives the floating frame 2 to float at a certain height H, and in the state, the floating frame 2 and the fixed frame 1 are not mechanically connected in the lifting force direction. Since the air friction coefficient is very small, the disturbance of the lateral forces is greatly reduced.
Further, as shown in fig. 1, a model connecting member 19 is provided at an upper portion of the normal sensor for fixing the test model.
Furthermore, the model connecting piece 19 is provided with threads and is fixedly connected with the test model through the threads.
Further, in step S1, the floating frame 2 floats above the fixed frame 1 by the air floating support device 16 to a height of 20-50 μm.
Further, the height of the floating frame 2 floating above the fixed frame 1 by the air supporting means 16 is kept constant during the test. The only guarantee in the test process is that the floating frame 2 and the fixed frame 1 are kept relatively static, the suspension height is kept unchanged, and the floating height of the floating frame 2 is very small, so that the steel wire rope can be considered to be in a horizontal state, and the floating frame 2 and the fixed frame 1 are guaranteed to be relatively static, so that the measurement precision can be improved.
Further, in step S1, the axial force sensor group and the lateral force sensor group are fixed to the fixed frame 1 and connected to the floating frame 2 through a wire rope.
Furthermore, the length of the steel wire soft rope is more than or equal to 0.5m, and the diameter is more than or equal to 0.5 mm.
In a wind tunnel test, the air floatation supporting devices are arranged at four peripheral corners of a wind tunnel test force measuring device, so that the floating frame 2 and the fixed frame 1 are supported.
During force measurement, high-pressure air (namely compressed air, the pressure is more than or equal to 4 atmospheric pressures) is introduced into the air floating block 4, the air flow sprayed downwards from the air floating block 4 enables the air floating block 4 and the floating frame 2 to be suspended together at a micro height H (about 20-50 micrometers), the air floating block 4 is separated from the surface of the platform assembly 18, a thin air film is formed in the middle, due to the fact that the friction coefficient of the air is small, a heavy object generates a small interference force in the transverse direction, almost all loads of the air flow acting on the test model are transmitted to the sensor group through the movement of the floating frame 2, and the axial force, the normal force, the lateral force, the rolling moment, the yawing moment and the pitching moment of the test model can be accurately obtained through different combinations of the sensor group.
When the force is not measured, the high-pressure air valve is cut off, the lower surface of the air floatation block 4 is contacted with the platform assembly 18, the weight of the measured object is transmitted to the fixed frame 1 through the platform assembly 18, the stability of the wind tunnel test force measuring equipment and the test model is ensured, and the state returns to the state before the air floatation work.
The invention has been described in detail with reference to specific embodiments and illustrative examples, but the description is not intended to be construed in a limiting sense. Those skilled in the art will appreciate that various equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its embodiments without departing from the spirit and scope of the present invention, which fall within the scope of the present invention. The scope of the invention is defined by the appended claims.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (10)
1. A distributed six-component aerodynamic force measuring method is characterized by being realized by adopting an air-flotation wind tunnel test device, wherein the air-flotation wind tunnel test device comprises a fixed frame (1), a floating frame (2) and an air-flotation supporting device (16);
the floating frame (2) floats above the fixed frame (1) through the air floating supporting device (16), the test model is fixed on the floating frame (2), and the aerodynamic force acting on the test model is transmitted to the sensor through the movement of the floating frame (2) to realize measurement;
the air floatation supporting device (16) comprises a platform assembly (18), an air floatation block (4) and an air floatation screw rod (5);
the platform assembly (18) is fixedly arranged on the upper surface of the fixed frame (1) and comprises a horizontal adjusting structure (3) at the lower part and an air floatation supporting platform (17) at the upper part, the horizontal adjusting structure (3) is used for adjusting the levelness of the air floatation supporting platform (17), and the air floatation supporting platform (17) is used for converting air injection pressure into supporting force for the air floatation block (4);
the air floating block (4) is arranged above the air floating supporting platform (17), and the lower surface of the air floating block (4) is in contact with the upper surface of the air floating supporting platform (17);
the lower surface of the air floating block (4) is provided with an air outlet, the inside of the air floating block is provided with a ventilation channel, the ventilation channel is connected with an external compressed air inlet and the air outlet, and compressed air is sprayed downwards through the air outlet so as to enable the air floating block (4) to float upwards;
the lower end of the air floatation screw rod (5) is connected with the upper surface of the air floatation block (4) through a spherical hinge, so that the air floatation screw rod (5) has three rotational degrees of freedom; the floating frame (2) is fixed on the air floating screw (5), and the air floating block (4) drives the floating frame (2) to float upwards when floating upwards;
the method comprises the following specific steps:
s1, mounting a normal force sensor, an axial force sensor and a lateral force sensor in the air floatation wind tunnel test device;
s2 reading the measurement result of each sensor;
s3, calculating the axial force, the normal force, the lateral force, the roll moment, the yaw moment and the pitch moment of the test model according to the measurement result of each sensor.
2. A distributed six-component aerodynamic force measurement method according to claim 1, wherein, in step S1,
the normal force sensors are divided into four groups and are fixed on the floating frame (2), and the symmetry axes between the normal force sensor group (y1) and the normal force sensor group (y2) and between the normal force sensor group (y3) and the normal force sensor group (y4) in the Z direction passing through the center of the floating frame are symmetrical; symmetry is carried out between the normal force sensor group (y1) and the normal force sensor group (y4), between the normal force sensor group (y2) and the normal force sensor group (y3) about a symmetry axis passing through the center X direction of the floating frame;
the axial force sensors are divided into two groups and are simultaneously connected with the fixed frame (1) and the floating frame (2), and the axial force sensor group (x1) and the axial force sensor group (x2) are symmetrical about a symmetrical axis in the Z direction of the center of the fixed frame;
the lateral force sensors are divided into four groups and are simultaneously connected with the fixed frame (1) and the floating frame (2), and the lateral force sensor group (Z1) is symmetrical to the lateral force sensor group (Z2), and the lateral force sensor group (Z3) is symmetrical to the lateral force sensor group (Z4) about a symmetry axis passing through the center Z direction of the floating frame; the symmetry axis between the lateral force sensor group (z1) and the lateral force sensor group (z4), and between the lateral force sensor group (z2) and the lateral force sensor group (z3) in the X direction of the center of the floating frame is symmetrical;
in step S2, reading the measurement results Y1, Y2, Y3, Y4 of the normal force sensor group, the measurement results X1 and X2 of the axial force sensor group, and the measurement results Z1, Z2, Z3 and Z4 of the lateral force sensor group;
in step S3, the method for calculating the axial force, the normal force, the lateral force, the roll moment, the yaw moment and the pitch moment applied to the test model includes:
axial force a ═ X1-X2;
normal force N ═ Y1+ Y2+ Y3+ Y4;
the lateral force Z is Z1+ Z2-Z3-Z4;
roll torque MX ═ L2 × (Y1+ Y2-Y3-Y4);
yaw moment MY ═ L1 × (Z1+ Z4-Z2-Z3);
a pitching moment MZ ═ L1 × (Y1+ Y4-Y2-Y3);
the L2 is the distance between each group of normal force sensors in the Z direction, and the L1 is the distance between each group of lateral force sensors in the X direction;
and the X, Y and Z directions are the directions of X, Y and Z axes in the coordinate system of the air floatation wind tunnel test device.
The coordinate system of the air floatation wind tunnel test device takes the central point of the floating frame 2 as an original point, the axial force direction of the test model is an X axis, the normal force direction of the test model is a Y axis, and the lateral force direction of the test model is a Z axis.
3. A distributed six-component aerodynamic force measurement method according to claim 2, wherein in step S1, each of the normal force sensor set, the axial force sensor set and the lateral force sensor set includes at least one corresponding sensor; the measurement results of each group of normal force sensor group, axial force sensor group and lateral force sensor group are the synthesis of the measurement results of all sensors included in each group of normal force sensor group, axial force sensor group and lateral force sensor group.
4. A distributed six-component aerodynamic force measurement method according to claim 1, characterized in that the level adjustment structure (3) is a support bar; the lower end of the supporting rod is fixedly arranged on the upper surface of the fixed frame (1), and the upper end of the supporting rod is fixedly connected with the lower surface of the air floatation supporting platform (17).
5. A distributed six-component aerodynamic force measurement method according to claim 2, wherein in step S1, a model connecting member (19) is provided at an upper portion of the normal sensor for fixing the test model.
6. A distributed six-component aerodynamic force measuring method according to claim 5, wherein the model connecting piece (19) is provided with threads and fixedly connected with the test model through the threads.
7. A distributed six-component aerodynamic force measurement method according to claim 1, characterized in that the floating frame (2) floats above the fixed frame (1) by the air supporting device (16) at a height of 20-50 μm.
8. A distributed six-component aerodynamic force measurement method according to claim 1, characterized in that the height of the floating frame (2) floating above the fixed frame (1) by the air supporting means (16) is kept constant during the test.
9. A distributed six-component aerodynamic force measurement method according to claim 2, wherein in step S1, the axial force sensor set and the lateral force sensor set are fixed on a fixed frame (1) and connected to a floating frame (2) through a steel wire rope.
10. The distributed six-component aerodynamic force measuring method according to claim 9, wherein the length of the steel cord is greater than or equal to 0.5m, and the diameter of the steel cord is greater than or equal to 0.5 mm.
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