阅读说明：本技术 一种吸气式进气道飞行器通气模型气动力测量装置和方法 (Aerodynamic force measurement device and method for air breathing model of air breathing type air inlet aircraft ) 是由 魏忠武 张江 付增良 董金刚 谢峰 于 2021-06-07 设计创作，主要内容包括：本发明公开了一种吸气式进气道飞行器通气模型气动力测量装置和方法,飞行器模型按照中心左右对称面分为左右两个模型,其中一个模型为测量半模型,另一个模型为映像半模型,测量天平安装于测量半模型内,天平座分别连接测量天平及映像支撑杆,映像半模型与映像支撑杆固连,天平座末端与侧支撑臂连接,侧支撑臂与侧窗固连,通过侧窗绕其自身的转动实现飞行器攻角的变化。试验中通过测量半模型的测量结果及模型的对称关系可得到飞行器全模型的气动力,实现飞行器模型无支撑干扰的气动特性测量。(The invention discloses an aerodynamic force measuring device and method for an air breathing type air inlet channel aircraft ventilation model, wherein the aircraft model is divided into a left model and a right model according to a central bilateral symmetry plane, one model is a measuring semi-model, the other model is an image semi-model, a measuring balance is arranged in the measuring semi-model, a balance seat is respectively connected with the measuring balance and an image supporting rod, the image semi-model is fixedly connected with the image supporting rod, the tail end of the balance seat is connected with a side supporting arm, the side supporting arm is fixedly connected with a side window, and the change of an aircraft attack angle is realized through the rotation of the side window around the side window. In the test, the aerodynamic force of the full model of the aircraft can be obtained by measuring the measurement result of the half model and the symmetric relation of the model, and the aerodynamic characteristic measurement of the aircraft model without support interference is realized.)

1. The utility model provides a formula of breathing in air intake duct aircraft model aerodynamic measurement device that ventilates, its characterized in that is including measuring half model (4), image half model (5), measuring balance (7), image bracing piece (8), side brace arm (3), side window (2), balance seat (6), wherein:

the air breathing model of the air breathing type air inlet channel aircraft is used for simulating the air breathing type air inlet channel aircraft and is divided into two half models by a longitudinal symmetry plane, the measuring half model (4) is one of the half models, and the mapping half model (5) is the other half model;

a mounting groove of a measuring balance and a balance seat (6) is arranged in the middle of the measuring half model (4) and at a position avoiding an air inlet, and in the mounting groove, one end of the measuring balance (7) is fixedly connected with the measuring half model (4) while the other end is fixedly connected with the balance seat; the other half of the balance seat penetrates through a through hole on the mapping half model (5) and is fixedly connected with one end of the side supporting arm (3);

in the installation groove, one end of the mapping support rod (8) is fixedly connected with the mapping half model (5), and the other end of the mapping support rod is fixedly connected with the balance seat in the through hole of the mapping half model (5);

the measuring balance (7) and the imaging support rod (8) have the same structural characteristics and are opposite in installation position; gaps are reserved among the balance seat, the measurement half model (4) and the mapping half model (5); the measurement half model (4) is sealed and isolated from the mapping half model (5), and a gap is reserved between the measurement half model and the mapping half model;

the other end of the side supporting arm (3) is fixedly connected with the wind tunnel side window (2), the side supporting arm (3), the balance seat, the measuring half model (4) and the mapping half model (5) are driven to rotate through the rotation of the wind tunnel side window (2), the change of the aircraft model along with the attack angle is realized, the aerodynamic force and aerodynamic moment of the measuring half model (4) along with the change of the attack angle are measured through the measuring balance (7), and the aerodynamic force and aerodynamic moment of the full model along with the change of the attack angle can be measured through measuring the symmetrical relation between the half model and the full model.

2. The aerodynamic force measuring device of the air intake channel aircraft ventilation model according to claim 1, characterized in that a side slider (11) is arranged at the joint of the balance seat and the side support arm (3), and aerodynamic force and aerodynamic moment measuring tests of the aircraft under different side slip angles are realized by replacing the side sliders (11) with different angles.

3. The aerodynamic force measurement device of an air breathing model of an air breathing channel aircraft according to claim 1, characterized in that a gap of not less than 2mm is left between the balance seat and the measurement half model (4) and the mapping half model (5).

4. An aerodynamic force measurement device according to claim 1, characterised in that the clearance between the measurement half-model (4) and the mapping half-model (5) is not more than 1% of the transverse maximum dimension of the air breathing model of the air breathing aircraft.

5. The aerodynamic force measuring device of the air intake channel aircraft ventilation model according to claim 1, characterized in that the side support arms (3) are designed into a V-shaped structure, so that the center of the air intake channel aircraft ventilation model is on the extension line of the rotation axis of the wind tunnel side window (2), and the model is always in the central area of the wind tunnel flow field when the window tray rotates to change the attack angle.

6. The aerodynamic force measurement device of the air intake channel aircraft ventilation model of claim 1, characterized in that the measurement half model (4) is provided with a first labyrinth seal (9) near the whole air intake channel aircraft ventilation model symmetry plane, and the first labyrinth seal (9) is fixedly connected with the measurement half model but not in contact with the measurement balance (7) and the balance seat.

7. The aerodynamic force measurement device of the air intake channel aircraft ventilation model of claim 1, characterized in that the mapping half model (5) is provided with a second labyrinth seal (10) near the whole air intake channel aircraft ventilation model symmetrical surface, and the second labyrinth seal (10) is fixedly connected with the mapping half model but not contacted with the mapping support rod (8) and the balance seat.

8. The method for measuring the aerodynamic force of the air breathing type air inlet aircraft ventilation model based on the device of claim 1 is characterized by comprising the following steps:

s1-1, acquiring aerodynamic force and aerodynamic moment of the measurement half model (4) which is measured by the measurement balance (7) and changes along with the attack angle;

and S1-2, calculating to obtain aerodynamic force and aerodynamic moment of the whole model of the air intake type air inlet aircraft ventilation model by measuring the measurement result of the half model (4) and the symmetry relation of the model.

9. The method for measuring aerodynamic force of the air breathing channel aircraft ventilation model according to claim 8, wherein in step S1-2, the calculation formulas of aerodynamic force and aerodynamic moment of the full model of the air breathing channel aircraft ventilation model are as follows:

wherein, F_x、F_y、F_zFor aerodynamic force component, M, of three directions under the body coordinate system of the air breathing type air inlet channel aircraft ventilation model_x、M_y、M_yFor the aerodynamic moment of three directions under the air intake type air inlet channel aircraft ventilation model body coordinate system, the upper and lower limits define as follows:representing the aerodynamic force of the whole model of the air breathing model of the air intake channel aircraft when the sideslip angle is 0 degrees and the attack angle is alpha,representing that aerodynamic force of the half model is measured when the sideslip angle is 0 degrees and the attack angle is alpha;indicates a slip angle ofThe aerodynamic moment of the whole model of the air intake channel aircraft ventilation model when the angle of attack is alpha is 0 degrees,the aerodynamic moment of the half model is measured when the sideslip angle is 0 degrees and the attack angle is alpha.

10. An aerodynamic force measurement method for an air breathing model of an air breathing channel aircraft based on the device of claim 2, characterized by comprising the following steps:

s2-1, adjusting the ventilation model of the air-breathing type air inlet channel aircraft to be in a positive sideslip state, and carrying out a primary aerodynamic force measurement test to obtain the aerodynamic force and the aerodynamic moment of the measurement half model (4) which are measured by the measurement balance (7) and change along with the positive sideslip angle;

s2-2, adjusting the ventilation model of the air-breathing type air inlet channel aircraft to be in a negative sideslip state, and carrying out a primary aerodynamic force measurement test to obtain the aerodynamic force and the aerodynamic moment of the measurement half model (4) which is measured by the measurement balance (7) and changes along with the negative sideslip angle;

and S2-3, according to the positive sideslip angle and the negative sideslip angle, measuring the aerodynamic force and aerodynamic moment of the half model (4) changing along with the positive sideslip angle and the negative sideslip angle, and the symmetric relation of the model, and obtaining the aerodynamic force and aerodynamic moment of the whole model of the air intake type air inlet aircraft ventilation model.

11. The method for measuring aerodynamic force of the air breathing channel aircraft ventilation model according to claim 10, wherein in step S2-3, the calculation formulas of aerodynamic force and aerodynamic moment of the full model of the air breathing channel aircraft ventilation model are as follows:

in the formula, F_x、F_y、F_zIs the aerodynamic force component in three directions under the coordinate system of the aircraft body, M_x、M_y、M_yThree in the coordinate system of the aircraft bodyThe aerodynamic moment in direction, the upper and lower limits, is defined as follows:represents the aerodynamic force of the whole model of the air breathing model of the air-breathing type air inlet aircraft when the sideslip angle is beta and the attack angle is alpha,the aerodynamic force of the half model is measured when the sideslip angle is-beta and the attack angle is alpha,aerodynamic force of a measurement semi-model representing a sideslip angle beta;represents the aerodynamic moment of the whole model of the air breathing model of the air-breathing type air inlet aircraft when the sideslip angle is beta and the attack angle is alpha,the aerodynamic moment of the half model is measured when the sideslip angle is beta and the attack angle is alpha,the aerodynamic moment of the semi-model is measured with a sideslip angle of-beta and an attack angle of alpha.

Technical Field

The invention relates to a device and a method for measuring aerodynamic force of an air breathing model of an air breathing type air inlet aircraft, and belongs to the fields of high-speed wind tunnel test technology and aircraft flight mechanics.

Background

For an aircraft with an air-breathing inlet, an aerodynamic force measurement test of a ventilation model is required when aerodynamic characteristic measurement is performed in a wind tunnel. The traditional ventilation model test method is that a balance is placed in a model, the balance is connected with an attack angle mechanism through a tail support rod, and the pneumatic characteristic of the model is measured through the balance. For an aircraft model with a large-size air suction type air inlet channel, the size of a tail nozzle of the air inlet channel is large, the model is often a thin-wall nozzle, the tail nozzle of the air inlet channel is not symmetrical in shape, a tail support rod has large interference on flow of the air inlet channel and cannot be corrected, the test precision is poor when a traditional ventilation model test method is used, and the aerodynamic characteristics of the aircraft cannot be completely reflected.

The conventional aircraft is a bilateral symmetry model, the conventional half-module supporting test is to fixedly connect the half-model to a wind tunnel side window through a balance and a balance seat, the change of the attack angle of the model is realized through the rotation of the side window, the supporting mode can avoid the conventional supporting interference, but the interference of the side wall of the wind tunnel can be brought, in addition, the supporting mode can only carry out the measurement of the change of the attack angle direction attitude of the bilateral symmetry model, and when the attitude of the sideslip angle direction is changed, the precision of the measurement result is poor. For an aircraft model with a large-size air suction type air inlet channel, when a conventional half-mode test is carried out, the central plane of the air inlet channel is the wall surface of a side window of a wind tunnel, so that the difference between the central plane flow of the air inlet channel and the actual condition is increased and cannot be corrected in the test, and the aerodynamic characteristics of the aircraft cannot be accurately measured.

Disclosure of Invention

The technical problem to be solved by the invention is as follows: the device and the method are used for realizing the test measurement of the internal and external flow complete simulation of the aircraft model with the large-size air suction type air inlet channel in a high-speed wind tunnel test, and improving the measurement precision.

The technical scheme of the invention is as follows: the utility model provides a formula of breathing in air inlet aircraft model aerodynamic force measuring device that ventilates, measuring device is including measuring half model, image half model, measuring balance, image bracing piece, side brace arm, side window, balance seat, wherein:

the air breathing model of the air breathing type air inlet channel aircraft is used for simulating the air breathing type air inlet channel aircraft and is divided into two half models by a longitudinal symmetry plane, the measuring half model is one of the half models, and the mapping half model is the other half model;

a mounting groove for a measuring balance and a balance seat is arranged in the middle of the measuring semi-model and avoids the position of the air inlet, and in the mounting groove, one end of the measuring balance is fixedly connected with the measuring semi-model, and the other end of the measuring balance is fixedly connected with the balance seat; the other half of the balance seat penetrates through a through hole on the mapping half model and is fixedly connected with one end of the side supporting arm;

the middle part of the image half model is provided with an installation groove of an image support rod avoiding the position of the air inlet channel, the installation groove is communicated with a through hole for placing a balance seat, one end of the image support rod is fixedly connected with the image half model in the installation groove, and the other end of the image support rod is fixedly connected with the balance seat in the through hole of the image half model;

the measuring balance and the imaging support rod have the same structural characteristics and are opposite in installation position; gaps are reserved among the balance seat, the measurement half model and the mapping half model; the measurement half model and the mapping half model are sealed and isolated, and a gap is reserved between the measurement half model and the mapping half model;

the other end of each side supporting arm is fixedly connected with a wind tunnel side window, the side supporting arms, the balance seat, the measurement semi-model and the mapping semi-model are driven to rotate through the rotation of the wind tunnel side window, the change of the aircraft model along with the attack angle is achieved, aerodynamic force and aerodynamic moment of the measurement semi-model along with the change of the attack angle are measured through the measurement balance, and the aerodynamic force and aerodynamic moment of the full model along with the change of the attack angle can be measured through measuring the symmetrical relation of the semi-model and the full model.

Preferably, a side sliding block is arranged at the joint of the balance seat and the side supporting arm, and aerodynamic force and aerodynamic moment measurement tests of the aircraft under different side sliding angles are realized by replacing the side sliding blocks at different angles.

Preferably, gaps are reserved between the balance seat and the measuring half model and between the balance seat and the mapping half model, and are not smaller than 2 mm.

Preferably, the clearance between the measurement and mapping half models is no more than 1% of the lateral maximum dimension of the air breathing aircraft model.

Preferably, the side supporting arms are designed into a V-shaped structure, so that the center of the air breathing model of the air breathing type air inlet channel aircraft is on the extension line of the rotation axis of the side window of the wind tunnel, and the model is always positioned in the central area of the flow field of the wind tunnel when the window tray rotates to change the attack angle.

Preferably, the measuring semi-model is provided with a first labyrinth seal part close to the symmetrical surface part of the whole air breathing type air inlet aircraft ventilation model, and the first labyrinth seal part is fixedly connected with the measuring semi-model but is not contacted with the measuring balance and the balance seat.

Preferably, the mapping half model is provided with a second labyrinth seal part close to the symmetrical surface part of the whole air breathing type air inlet channel aircraft ventilation model, and the second labyrinth seal part is fixedly connected with the mapping half model but is not contacted with the mapping support rod and the balance seat.

Based on the device, the invention also provides a method for measuring the aerodynamic force of the ventilation model of the air-breathing type air inlet aircraft, which comprises the following steps:

s1-1, acquiring aerodynamic force and aerodynamic moment of the measurement half model, which are measured by a measurement balance and change along with the attack angle;

and S1-2, calculating to obtain aerodynamic force and aerodynamic moment of the whole model of the air intake type air inlet aircraft ventilation model by measuring the measurement result of the half model and the symmetry relation of the model.

In the step S1-2, the calculation formulas of aerodynamic force and aerodynamic moment of the full model of the air breathing type air inlet aircraft ventilation model are as follows:

wherein, F_x、F_y、F_zAerodynamic force of three directions under body coordinate system of air breathing type air inlet channel aircraft ventilation modelComponent, M_x、M_y、M_yFor the aerodynamic moment of three directions under the air intake type air inlet channel aircraft ventilation model body coordinate system, the upper and lower limits define as follows:representing the aerodynamic force of the whole model of the air breathing model of the air intake channel aircraft when the sideslip angle is 0 degrees and the attack angle is alpha,representing that aerodynamic force of the half model is measured when the sideslip angle is 0 degrees and the attack angle is alpha;represents the aerodynamic moment of the whole model of the air intake channel aircraft ventilation model when the sideslip angle is 0 degrees and the attack angle is alpha,the aerodynamic moment of the half model is measured when the sideslip angle is 0 degrees and the attack angle is alpha.

Preferably, the invention also provides an aerodynamic force measurement method for the air intake channel aircraft ventilation model, which comprises the following steps:

s2-1, adjusting the ventilation model of the air-breathing type air inlet channel aircraft to be in a positive sideslip state, and performing a pneumatic force measurement test to obtain the pneumatic force and the pneumatic moment of a measurement half model, which are measured by a measurement balance and change along with the positive sideslip angle;

s2-2, adjusting the ventilation model of the air-breathing type air inlet channel aircraft to be in a negative sideslip state, and performing a pneumatic force measurement test to obtain the pneumatic force and the pneumatic moment of a measurement half model, which are measured by a measurement balance and change along with the negative sideslip angle;

and S2-3, according to the positive sideslip angle and the negative sideslip angle, measuring the aerodynamic force and aerodynamic moment of the half model changing along with the positive sideslip angle and the negative sideslip angle, and the symmetry relation of the model, and obtaining the aerodynamic force and aerodynamic moment of the whole model of the air breathing type air inlet aircraft ventilation model.

In step S2-3, the calculation formulas of the aerodynamic force and the aerodynamic moment of the full model of the air breathing type air inlet aircraft ventilation model are as follows:

in the formula, F_x、F_y、F_zIs the aerodynamic force component in three directions under the coordinate system of the aircraft body, M_x、M_y、M_yThe aerodynamic moment in three directions under the coordinate system of the aircraft body is defined as follows:represents the aerodynamic force of the whole model of the air breathing model of the air-breathing type air inlet aircraft when the sideslip angle is beta and the attack angle is alpha,the aerodynamic force of the half model is measured when the sideslip angle is-beta and the attack angle is alpha,aerodynamic force of a measurement semi-model representing a sideslip angle beta;represents the aerodynamic moment of the whole model of the air breathing model of the air-breathing type air inlet aircraft when the sideslip angle is beta and the attack angle is alpha,the aerodynamic moment of the half model is measured when the sideslip angle is beta and the attack angle is alpha,the aerodynamic moment of the semi-model is measured with a sideslip angle of-beta and an attack angle of alpha.

Compared with the prior art, the invention has the beneficial effects that:

(1) according to the invention, the model is divided into the measuring half model and the mapping half model, the aerodynamic force of the half model is measured through the balance in the test, the aerodynamic characteristics of the full model can be obtained through the symmetrical relation of the models, the test has no supporting interference, and the test precision is high.

(2) The interference amount during measurement is the interference amount of the mapping half model to the measurement half model, the interference amount is exactly the interference amount existing in a real aircraft, meanwhile, the flow characteristic structure in the air inlet channel is completely and truly simulated, and the test measurement accuracy is high.

(3) Gaps are reserved between the balance seat and the measuring half model and between the balance seat and the mapping half model, and measured data distortion caused by contact of the measuring half model and the mapping half model when the model is loaded and deformed is prevented. At the same time, the gap cannot be too large, causing distortion of the model and the real shape.

(4) The measurement half model and the mapping half model are packaged, so that the up-and-down flow channeling phenomenon of the model is avoided, and the flow channeling phenomenon of the air flow inside the air inlet passage of the model and the air flow outside the aircraft is avoided, so that the test data is distorted.

(5) The side sliding blocks are arranged at the connecting positions of the balance seat and the side supporting arms, and aerodynamic force and aerodynamic moment measurement tests of the aircraft under different side sliding angles are realized by replacing the side sliding blocks at different angles.

(6) The side supporting arms are designed into a V-shaped structure, so that the center of the air breathing model of the air suction type air inlet channel aircraft is on the extension line of the rotation axis of the side window of the wind tunnel, the model is always in the center position of the wind tunnel when the attack angle changes, the test in a larger angle range can be realized, and the interference change of the wall of the wind tunnel is not large.

(7) The measuring method designed by the invention can completely reflect the real condition of the internal flow of the air inlet channel, and the test fidelity is high.

Drawings

FIG. 1 is a schematic diagram of the method for measuring aerodynamic force of a ventilation model according to the present invention;

FIG. 2 is a schematic cross-sectional view of a ventilation model according to the present invention;

FIG. 3 is a schematic view of a breather model labyrinth seal according to the present invention;

FIG. 4 is a schematic illustration of a sideslip angle block configuration according to the present invention;

the figures are labeled as follows:

the method comprises the following steps of 1-wind tunnel side wall, 2-side window, 3-side supporting arm, 4-measuring half model, 5-mapping half model, 6-balance seat, 7-measuring balance, 8-mapping supporting rod, 9-first labyrinth seal, 10-first labyrinth seal, 11-side sliding block and 12-air inlet channel.

Detailed Description

The invention is described in detail below with reference to the figures and examples.

Example 1:

as shown in fig. 1 and fig. 2, the invention provides a test measurement device for a ventilation model of an air-breathing type air inlet aircraft, which can completely simulate the test measurement of complete simulation of internal and external flows of an air-breathing type air inlet aircraft model with a large size. The device is including measuring half model 4, image half model 5, measuring balance 7, image bracing piece 8, side brace 3, side window 2, balance seat 6, wherein:

the air intake type air inlet aircraft ventilation model is used for simulating an air intake type air inlet aircraft and is divided into two half models by a longitudinal symmetry plane, the measuring half model 4 is one of the half models, the mapping half model 5 is the other half model, and the measuring half model and the mapping half model need to ensure that the external dimension and the internal structure of an air inlet are the same as those of the aircraft.

A mounting groove of a measuring balance and a balance seat 6 is arranged in the middle of the measuring semi-model 4 and at a position avoiding an air inlet, and in the mounting groove, one end of the measuring balance 7 is fixedly connected with the measuring semi-model 4, and the other end of the measuring balance is fixedly connected with the balance seat; the part of the mapping half model, which is far away from the symmetrical surface of the full model, is provided with a hole for mounting a balance seat, and the other half of the balance seat penetrates through a through hole on the side surface of the mapping half model 5 and is fixedly connected with one end of the side supporting arm 3.

The installation groove that the air inlet duct position was equipped with image bracing piece 8 is avoided at image half model 5 middle part, and this installation groove communicates with each other with the through-hole that is used for placing the balance seat, and in this installation groove, 8 one end of image bracing piece are in the same place with image half model 5 fixed connection, and the other end is in the same place with the balance seat fixed connection that is located image half model 5 through-hole.

The measuring balance 7 and the imaging support rod 8 have the same structural characteristics and are opposite in installation position, namely: the balance seat is connected with the measuring balance and the mapping support rod side by side, so that deformation of the measuring half model and the mapping half model relative to the balance seat is consistent when the measuring half model and the mapping half model are loaded in airflow. Gaps are reserved between the balance seat and the measuring half model 4 and between the balance seat and the mapping half model 5; the measurement half model 4 and the mapping half model 5 are sealed and isolated, and a gap is reserved between the two models, so that the model is prevented from contacting with a balance seat when being subjected to load deformation, and the measured data is prevented from being distorted.

The other end of the side supporting arm 3 is fixedly connected with the wind tunnel side window 2, the side supporting arm 3, the balance seat, the measuring semi-model 4 and the mapping semi-model 5 are driven to rotate through the rotation of the wind tunnel side window 2, the change of the aircraft model along with the attack angle is realized, the aerodynamic force and the aerodynamic moment of the measuring semi-model 4 along with the change of the attack angle are measured through the measuring balance 7, the measurement of the aerodynamic force and the aerodynamic moment of the full model along with the change of the attack angle can be obtained through measuring the symmetrical relation of the semi-model and the full model, and the measurement of the aerodynamic characteristic of the aircraft model without supporting interference is realized.

Preferably, gaps are reserved between the balance seat and the measuring half model 4 and between the balance seat and the mapping half model 5 and are not smaller than 2mm, and the measuring data distortion caused by the contact of the measuring half model and the mapping half model when the model is deformed under load is prevented. At the same time, the gap cannot be too large, causing distortion of the model and the real shape.

Preferably, the clearance between the measurement half-model 4 and the mapping half-model 5 is not greater than 1% of the lateral maximum dimension of the aspirated channel aircraft ventilation model.

Preferably, the side support arms 3 are designed into a V-shaped structure, so that the center of the air breathing model of the air breathing type air inlet channel aircraft is on the extension line of the rotation axis of the side window 2 of the wind tunnel, and the model is always in the central area of the flow field of the wind tunnel when the window tray rotates to change the attack angle.

Preferably, the part of the measurement half model 4, which is close to the symmetrical plane of the whole air breathing model of the air breathing type air inlet aircraft, is provided with a first labyrinth seal 9, and the first labyrinth seal 9 is fixedly connected with the measurement half model but is not in contact with the measurement balance 7 and the balance seat, so that the up-and-down cross flow phenomenon of the model is avoided, and the cross flow phenomenon of the air flow inside the air inlet of the model and the air flow outside the aircraft is avoided, thereby causing the distortion of test data.

As shown in fig. 3, preferably, the mapping half model 5 is provided with a second labyrinth seal 10 near the symmetrical plane part of the whole air intake channel aircraft ventilation model, and the second labyrinth seal 10 is fixedly connected with the mapping half model but is not contacted with the mapping support rod 8 and the balance seat. There is no contact between the first labyrinth seal and the second labyrinth seal. The measuring half model, the mapping half model, the labyrinth seal 9 and the second labyrinth seal 10 together form a complete air intake channel aircraft ventilation model.

Based on the device, the invention also provides a method for testing and measuring the ventilation model of the air-breathing type air inlet aircraft, which comprises the following steps:

s1-1, acquiring aerodynamic force and aerodynamic moment of the measurement half model 4, which is measured by the measurement balance 7 and changes along with the attack angle;

s1-2, calculating and obtaining the aerodynamic force and the starting moment of the full aircraft model by measuring the measurement result of the half model 4 and the symmetry relation of the model, wherein the specific calculation formula is as follows:

wherein, F_x、F_y、F_zFor aerodynamic force component, M, of three directions under the body coordinate system of the air breathing type air inlet channel aircraft ventilation model_x、M_y、M_yFor the aerodynamic moment of three directions under the air intake type air inlet channel aircraft ventilation model body coordinate system, the upper and lower limits define as follows:representing the aerodynamic force of the whole model of the air breathing model of the air intake channel aircraft when the sideslip angle is 0 degrees and the attack angle is alpha,representing that aerodynamic force of the half model is measured when the sideslip angle is 0 degrees and the attack angle is alpha;represents the aerodynamic moment of the whole model of the air intake channel aircraft ventilation model when the sideslip angle is 0 degrees and the attack angle is alpha,the aerodynamic moment of the half model is measured when the sideslip angle is 0 degrees and the attack angle is alpha.

Example 2:

as shown in fig. 4, preferably, a side slider 11 is arranged at the joint of the balance seat and the side support arm 3, and aerodynamic force and aerodynamic moment measurement tests of the aircraft at different side slip angles are realized by replacing the side slider 11 at different angles.

Furthermore, because the device also has the function of adjusting the sideslip angle, the invention also provides a second method for testing and measuring the ventilation model of the air-breathing type air inlet channel aircraft, which comprises the following steps:

s2-1, adjusting the ventilation model of the air-breathing type air inlet channel aircraft to be in a positive sideslip state, and carrying out a primary aerodynamic force measurement test to obtain the aerodynamic force and aerodynamic moment of the measurement half model 4, which is measured by the measurement balance 7 and changes along with the positive sideslip angle;

s2-2, adjusting the ventilation model of the air-breathing type air inlet channel aircraft to be in a negative sideslip state, and carrying out a primary aerodynamic force measurement test to obtain the aerodynamic force and aerodynamic moment of the measurement half model 4, which is measured by the measurement balance 7 and changes along with the negative sideslip angle;

s2-3, according to the positive sideslip angle and the negative sideslip angle, measuring the aerodynamic force and aerodynamic moment of the half model 4 changing along with the positive sideslip angle and the negative sideslip angle, and the symmetry relation of the model, and obtaining the aerodynamic force and aerodynamic moment of the whole model of the air intake type air inlet aircraft ventilation model; the specific calculation formula is as follows:

in the formula, F_x、F_y、F_zIs the pneumatic operation in three directions under the coordinate system of the aircraft bodyComponent of force, M_x、M_y、M_yThe aerodynamic moment in three directions under the coordinate system of the aircraft body is defined as follows:represents the aerodynamic force of the whole model of the air breathing model of the air-breathing type air inlet aircraft when the sideslip angle is beta and the attack angle is alpha,the aerodynamic force of the half model is measured when the sideslip angle is-beta and the attack angle is alpha,aerodynamic force of a measurement semi-model representing a sideslip angle beta;represents the aerodynamic moment of the whole model of the air breathing model of the air-breathing type air inlet aircraft when the sideslip angle is beta and the attack angle is alpha,the aerodynamic moment of the half model is measured when the sideslip angle is beta and the attack angle is alpha,the aerodynamic moment of the semi-model is measured with a sideslip angle of-beta and an attack angle of alpha.

Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications without departing from the spirit and scope of the present invention.

Those skilled in the art will appreciate that the invention may be practiced without these specific details.