An aircraft model simulation verification platform

Abstract

The invention relates to the technical field of simulation experiment, and in particular to an aircraft model simulation verification platform, which comprises a base, a bearing block, a push rod, a motor and a controller; a bearing block is arranged above the base, and the bearing block moves in a vertical direction to support an aircraft model, and a corresponding push rod is arranged at the tail of the engine of the aircraft model; since a supporting structure fixed on the aircraft model interferes with the aerodynamic layout of a connection, the measured aerodynamic performance is affected, and the aircraft model is in a relatively static state, so that the data of the simulation verification has limitations; therefore, the invention performs aerodynamic performance simulation verification on the force generated by the airflow in a wind tunnel on the aircraft model through the push rod arranged at the tail of the aircraft model engine, so that the aircraft model itself is adaptively adjusted in the simulation, more complete aerodynamic performance data is obtained, and the richness and authenticity of the aircraft model simulation verification data are improved.

Description

Technical Field

[0001] The invention relates to the technical field of simulation experiments, and in particular to an aircraft model simulation verification platform. Background Art

[0002] With the continuous opening up of the aviation field, more and more new aircraft are coming into being. When designing an aircraft, it is necessary to simulate and verify the aircraft model, and use the platform to simulate the impact of various situations on the aircraft model, and verify the aircraft model and design feasibility. Among them, simulation verification is assisted by computers to establish a virtual flow field model for fluid mechanics simulation, but the accuracy of the calculation results often depends on whether the definition of boundary conditions and physical parameters during the pre-processing of complex flow field simulation is consistent with the actual situation, and whether the calculation method and post-processing are accurate. It is often necessary to verify in a real physical flow field wind tunnel.

[0003] The word wind tunnel comes from the English word “Wind Tunnel”. A wind tunnel laboratory uses artificial airflow to simulate the gas flow around an aircraft and makes the best design by collecting and analyzing data. Before the aircraft can be put into use, it must be repeatedly tested in a wind tunnel laboratory. It is an indispensable and important part of aircraft development. For an introduction to aircraft simulation and verification wind tunnels, see: Ai Yu, Overview of NASA Wind Tunnel Laboratory [J]. Astronaut. 2013. (3): 56-59.

[0004] Some technical solutions for aircraft model simulation and verification platforms have also appeared in the prior art. For example, a Chinese patent with application number 2018115954716 discloses an aircraft model simulation and verification platform: comprising a simulation excitation module and a simulation display module; the simulation model unit in the simulation excitation module is connected to the simulation excitation unit, the simulation excitation unit is connected to the first data management unit, the first data management unit is connected to the first database and the first data interface management unit respectively; the simulation display unit in the simulation display module is connected to the second data management unit, the second data management unit is connected to the second database and the second data interface management unit respectively; the first data interface management unit is connected to the second data interface management unit; the first database is connected to the second database; this technical solution can achieve low-cost, fast and scalable verification to meet the simulation and verification requirements of various aircraft and various equipment; it realizes the parallel development of system modules and improves the development efficiency of the platform; however, the simulation results in this technical solution need to be verified by wind tunnel experiments or actual physical flow fields to ensure reliability, which makes it difficult to ensure the quality of the aircraft model simulation and verification data in this technical solution.

[0005] In view of this, in order to overcome the above-mentioned technical problems, our company has designed and developed an aircraft model simulation verification platform, which adopts a special simulation verification platform structure to solve the above-mentioned technical problems. Summary of the invention

[0006] In order to make up for the shortcomings of the prior art, the present invention proposes an aircraft model simulation verification platform, which is equipped with a push rod at the tail of the aircraft model engine and the force exerted on the aircraft model by the airflow generated in the wind tunnel, so that the aircraft model only acts on the push rod to perform simulation verification of aerodynamic performance. In conjunction with slight changes in wind parameters in the wind tunnel, the aircraft model can perform slight adaptive attitude adjustments during the simulation verification, thereby obtaining more complete aerodynamic performance data, thereby improving the richness and authenticity of the aircraft model simulation verification data.

[0007] The airplane model simulation verification platform described in the present invention comprises a base, a bearing block, a push rod, a motor and a controller; a pit is arranged on the base, a telescopic frame is installed in the pit, and a bearing block is arranged on the top of the telescopic frame; the telescopic frame is driven by a hydraulic rod to control the movement of the bearing block in the vertical direction; the bearing block is used to support the airplane model; a column is arranged at the rear of the airplane model, and a push rod is arranged at the tail position of the engine of the airplane model; the head of the push rod is in contact with the tail of the engine of the airplane model, and the tail of the push rod is fixed on the column; the push rod corresponds to the engine position of the airplane model one by one, and the push rod is fixedly installed on the base through the column; the motor drives The fan of the simulation platform runs to provide a wind source for the simulation verification of the aircraft model; the controller adjusts the wind force during the simulation verification process by controlling the power of the motor, and drives the lifting and lowering of the bearing block by controlling the action of the hydraulic rod on the telescopic frame; when working, the controller is started, the telescopic frame is extended, so that the bearing block is raised, and the aircraft model is placed on the bearing block, and the position of the adjustment column is installed on the base so that the head of the push rod corresponds to the tail position of the engine of the aircraft model, and the fan is started by controlling the motor to blow from the head direction of the aircraft model, simulating the interaction between the aircraft and the wind during flight, and the telescopic frame is gradually retracted and lowered. The load-bearing block is made to fall into the concave pit of the base, the aircraft model is held up by the lift of the wind in the vertical direction, and the aircraft model is positioned in the horizontal direction by the push rod at the tail position of the engine; since it is often fixedly connected to the middle or tail of the aircraft model through the support structure during the simulation process to fully measure its aerodynamic performance, but the support structure fixedly connected to the aircraft model interferes with the aerodynamic layout of the connection, affecting the aerodynamic performance of the local measurement, and the aircraft model in the wind tunnel is in a relatively static state during the simulation verification, and it is impossible to obtain the dynamic aerodynamic performance data of the aircraft model, which makes the simulation verification data have limitations; the present invention utilizes the support structure set on the aircraft The push rod at the tail of the model engine exerts a force on the aircraft model through the airflow generated in the wind tunnel, so that the aircraft model only acts on the push rod for aerodynamic performance simulation verification. The push rod is selected to act on the tail of the aircraft model's engine, which more realistically simulates the power source of the aircraft in flight and avoids the simulation interference of the supporting structure on the local aerodynamic shape of the aircraft model. By setting the push rod in contact with the tail of the aircraft model's engine, combined with the slight changes in the wind parameters in the wind tunnel, the aircraft model can make slight adaptive attitude adjustments in the simulation verification, obtain more complete aerodynamic performance data, and improve the richness and authenticity of the aircraft model simulation verification data.

[0008] Preferably, the head of the push rod is provided with an airbag, which is truncated cone-shaped, with a small end face of the truncated cone-shaped airbag fixedly connected to the head of the push rod, and a large end face of the truncated cone-shaped airbag facing the tail of the engine of the aircraft model; the middle part of the large end face of the airbag is recessed for fitting on the tail of the engine of the aircraft model; when working, the push rod is aligned with the tail position of the engine of the aircraft model, and the wind tunnel is started for simulation verification. Due to the differences in engine shapes of various types of aircraft models, the corresponding push rod heads require different shapes to cooperate with the contact at the tail position of the engine of the aircraft model, thereby preventing the position deviation of the push rod positioning from affecting the simulation verification data; by providing the truncated cone-shaped airbag on the head of the push rod, the middle part of the airbag is recessed so that the push rod can be accurately positioned at the tail position of the engine of the aircraft model. At the same time, under the action of wind in the wind tunnel, the shape of the tail of the engine of the aircraft model causes the contact surface shape of the airbag to change accordingly, thereby avoiding the deviation of the push rod positioning at the tail position of the engine of the aircraft model, thereby improving the richness and authenticity of the aircraft model simulation verification data.

[0009] Preferably, an air tube is provided inside the push rod; a micro air pump is provided on the column; one end of the air tube is connected to the airbag, and the other end of the air tube is connected to the micro air pump through the tail of the push rod, and a pressure sensor is provided on the micro air pump; the pressure sensor feeds back the pressure value of the airbag at the head of the push rod through the air tube; when working, the aircraft model is positioned in the wind tunnel only by the push rod at the tail of the engine, and the airflow parameters in the wind tunnel need to be controlled to ensure the smooth progress of the aircraft model simulation verification; the airbag arranged at the head of the push rod can feed back the engine stress conditions at different positions on the aircraft model, and the air pressure data of the airbag is fed back to the processing module of the controller through the pressure sensor, and then the wind force in the wind tunnel is adjusted by the controller to be within a reasonable range of the simulation verification, so as to avoid the aircraft model in the wind tunnel being blown up or dropped during the simulation and terminating the verification process, thereby improving the richness and authenticity of the aircraft model simulation verification data.

[0010] Preferably, the micro air pump is provided with an air pressure regulator, which is controlled by a controller; the controller can adjust the air pressure value in each airbag respectively through the air pressure regulator; when working, the aircraft model needs to simulate various actual situations in aircraft operation in the simulation to obtain real and comprehensive verification data, and changing the airflow parameters in the wind tunnel can only verify the performance of the aircraft model as a change in the external environment, but cannot verify the performance of the aircraft model by changing the parameters of the aircraft model itself; the controller controls the air pressure regulator on the micro air pump so that the airbags at the head of each push rod have different air pressure values ​​to simulate the working conditions of each engine of the aircraft under different working conditions, as well as the influence on the overall aerodynamic performance of the aircraft model, thereby improving the richness and authenticity of the aircraft model simulation verification data.

[0011] Preferably, the tail section of the push rod is provided with a thread, and the push rod is installed on the column by rotating the thread, and a positioning nut is provided at the contact point of the push rod on the outside of the column; when working, the extension length of the push rod on the column is adjusted by rotation to adapt to the engine position on different types of aircraft models, and the provided positioning nut limits the positioned push rod, ensuring precise control of the action position of the push rod in the aircraft model simulation, thereby improving the versatility of the aircraft model simulation verification platform.

[0012] Preferably, a base is provided below the column, and support rods are provided at three positions on the base, and the base and the column are connected by the support rods; a fixed spherical joint is provided at the upper end of the support rod, and the spherical joint is rotatably installed in the spherical hole at the bottom of the column; the lower end of the support rod is located in a hole groove inside the base, and a servo motor is provided at the bottom of the hole groove; a lead screw pair is provided inside the support rod, and the lead screw pair is driven by the servo motor to make the support rod rise and fall on the base; when working, the aircraft model needs to be positioned in different postures in the simulation to simulate the take-off, landing and rotation processes of the aircraft in operation, and the aircraft model needs to be adjusted to the required posture in the wind tunnel for many times before performing flight simulation verification, which reduces the simulation verification efficiency of the aircraft model and increases the workload; the servo motor is controlled by the provided controller to operate, so that the support rods are raised to different heights respectively, thereby changing the tilt angle of the column, and the top rod also changes its posture accordingly, which is convenient for the aircraft model to change its own posture during different movements, and improves the richness and authenticity of the aircraft model simulation verification data.

[0013] The beneficial effects of the present invention are as follows:

[0014] 1. The present invention arranges a push rod at the tail of the aircraft model engine, utilizes the force exerted on the aircraft model by the airflow generated in the wind tunnel, so that the aircraft model only acts on the push rod to perform simulation verification of aerodynamic performance, and selects the push rod to act on the tail of the aircraft model engine, which more realistically simulates the power source of the aircraft in flight and avoids the simulation interference of the supporting structure on the local aerodynamic shape of the aircraft model. By arranging a truncated cone-shaped airbag at the head of the push rod, the shape of the tail of the engine of the aircraft model and the contact surface shape of the airbag are changed accordingly, so as to avoid the deviation of the positioning position of the push rod. The controller is arranged to control the air pressure regulator on the micro air pump, so that the airbags at the heads of the push rods have different air pressure values, so as to simulate the action of each engine of the aircraft under different working conditions and the influence on the overall aerodynamic performance of the aircraft model, thereby improving the richness and authenticity of the aircraft model simulation verification data.

[0015] 2. The present invention limits the push rod after adjustment and positioning by setting a positioning nut to adapt to the engine position on different types of aircraft models, thereby ensuring the precise control of the push rod's action position in the aircraft model simulation. The set controller controls the operation of the servo motor, so that the support rods are raised to different heights, thereby changing the tilt angle of the column, and the push rod also changes its posture accordingly, which facilitates the aircraft model's own posture changes during different movement processes, thereby improving the richness and authenticity of the aircraft model simulation verification data. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The present invention is further described below in conjunction with the accompanying drawings and implementation modes.

[0017] Figure 1 It is a three-dimensional diagram of the simulation verification platform in the present invention;

[0018] Figure 2 It is the main view of the simulation verification platform in the present invention;

[0019] Figure 3 yes Figure 2 A partial enlarged view of the middle part;

[0020] Figure 4 It is a structural schematic diagram of the base in the present invention;

[0021] In the figure: base 1, pit 11, telescopic frame 12, bearing block 2, push rod 3, air bag 31, air pipe 32, positioning nut 33, column 4, micro air pump 5, air pressure regulator 51, base 6, support rod 61, ball joint 611, servo motor 62, screw pair 63. DETAILED DESCRIPTION

[0022] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further explained below in conjunction with specific implementation methods.

[0023] like Figures 1 to 4As shown, an aircraft model simulation verification platform described in the present invention comprises a base 1, a bearing block 2, a push rod 3, a motor and a controller; a pit 11 is provided on the base 1, a telescopic frame 12 is installed in the pit 11, and a bearing block 2 is provided at the top of the telescopic frame 12: the telescopic frame 12 is driven by a hydraulic rod to control the movement of the bearing block 2 in the vertical direction; the bearing block 2 is used to support the aircraft model; a column 4 is provided at the rear of the aircraft model, and a push rod 3 is provided at the tail position of the engine of the aircraft model; the head of the push rod 3 is in contact with the tail of the engine of the aircraft model, and the tail of the push rod 3 is fixed on the column 4; the push rod 3 corresponds to the engine position of the aircraft model one by one, and the push rod 3 is connected to the column 4 through the column 4 It is fixedly installed on the base 1; the motor drives the fan of the simulation platform to operate, providing a wind source for the simulation verification of the aircraft model; the controller adjusts the wind force during the simulation verification process by controlling the power of the motor, and the controller drives the lifting of the bearing block 2 by controlling the action of the hydraulic rod on the telescopic frame 12; when working, the controller is started, the telescopic frame 12 is extended, so that the bearing block 2 is raised, and the aircraft model is placed on the bearing block 2, and the position of the adjustment column 4 is installed on the base 1 so that the head of the top rod 3 corresponds to the tail position of the engine of the aircraft model, and the fan is started by controlling the motor to operate, and the wind blows from the head direction of the aircraft model, simulating the interaction between the aircraft and the wind when flying. The telescopic frame 12 is gradually retracted to lower the bearing block 2, so that the bearing block 2 falls into the pit 11 of the base 1. The aircraft model is lifted by the lift of the wind in the vertical direction, and the aircraft model is positioned in the horizontal direction by the push rod 3 at the tail position of the engine. In the simulation process, the aircraft model is often fixedly connected to the middle or tail of the aircraft model through a supporting structure to fully measure its aerodynamic performance. However, the supporting structure fixedly connected to the aircraft model interferes with the aerodynamic layout of the connection, affecting the aerodynamic performance of the local measurement. At the same time, the aircraft model in the wind tunnel is in a relatively static state during the simulation verification, and it is impossible to obtain the dynamic aerodynamic performance data of the aircraft model, which makes the data of the simulation verification limited. The invention utilizes a push rod 3 arranged at the tail of the aircraft model engine, and generates a force on the aircraft model through the airflow generated in the wind tunnel, so that the aircraft model only acts on the push rod 3 to perform a simulation verification of aerodynamic performance. The push rod 3 is selected to act on the tail of the engine of the aircraft model, which more realistically simulates the power source of the aircraft in flight and avoids the simulation interference of the supporting structure on the local aerodynamic shape on the aircraft model. By making the push rod 3 contact with the tail of the engine of the aircraft model and cooperating with the slight change of the wind parameters in the wind tunnel, the aircraft model performs a slight adaptive attitude adjustment in the simulation verification, thereby obtaining more complete aerodynamic performance data, and improving the richness and authenticity of the aircraft model simulation verification data.

[0024] As an embodiment of the present invention, the head of the push rod 3 is provided with an air bag 31, and the air bag 31 is in a truncated cone shape. The small end face of the truncated cone air bag 31 is fixedly connected to the head of the push rod 3, and the large end face of the truncated cone air bag 31 faces the tail of the engine of the aircraft model; the middle part of the large end face of the air bag 31 is concave, and is used to fit on the tail of the engine of the aircraft model; when working, the push rod 3 is aligned with the tail position of the engine of the aircraft model, and the wind tunnel is started for simulation verification. Due to the difference in the engine shape of each type of aircraft model, the corresponding push rod 3 head needs a different shape to match the connection The push rod 3 is placed on the tail of the engine of the aircraft model to prevent the position deviation of the push rod 3 from affecting the simulation verification data; the push rod 3 is provided with a truncated cone-shaped air bag 31 at the head of the push rod 3, and the middle part of the air bag 31 is concave so that the push rod 3 can be accurately positioned on the tail of the engine of the aircraft model. At the same time, under the action of wind force in the wind tunnel, the shape of the tail of the engine of the aircraft model causes the contact surface shape of the air bag 31 to change accordingly, thereby avoiding the deviation of the positioning of the push rod 3 on the tail of the aircraft model engine, thereby improving the richness and authenticity of the aircraft model simulation verification data.

[0025] As an embodiment of the present invention, an air tube 32 is arranged inside the push rod 3; a micro air pump 5 is arranged on the column 4; one end of the air tube 32 is connected to the air bag 31, and the other end of the air tube 32 is connected to the micro air pump 5 through the tail of the push rod 3, and a pressure sensor is arranged on the micro air pump 5; the pressure sensor feeds back the pressure value of the air bag 31 at the head of the push rod 3 through the air tube 32; when working, the aircraft model is positioned in the wind tunnel only by the push rod 3 at the tail of the engine, and the air flow parameters in the wind tunnel need to be controlled to ensure the smooth progress of the aircraft model simulation verification; the air bag 31 arranged at the head of the push rod 3 can feed back the engine stress conditions at different positions on the aircraft model, and the air pressure data of the air bag 31 is fed back to the processing module of the controller through the pressure sensor, and then the controller adjusts the size of the wind force in the wind tunnel to be within a reasonable range of the simulation verification, so as to avoid the aircraft model in the wind tunnel being blown up or dropped during the simulation and terminating the verification process, thereby improving the richness and authenticity of the aircraft model simulation verification data.

[0026] As an embodiment of the present invention, the micro air pump 5 is provided with an air pressure regulator 51, and the air pressure regulator 51 is controlled by a controller; the controller can adjust the air pressure value in each airbag 31 respectively through the air pressure regulator 51; when working, the aircraft model needs to simulate various actual conditions in the operation of the aircraft in the simulation to obtain real and comprehensive verification data, and changing the airflow parameters in the wind tunnel can only verify the performance of the aircraft model as a change in the external environment, and cannot verify the performance of the aircraft model by changing the parameters of the aircraft model itself; the controller controls the air pressure regulator 51 on the micro air pump 5, so that the airbag 31 at the head of each push rod 3 has a different air pressure value, so as to simulate the working conditions of each engine of the aircraft under different working conditions, and the influence on the overall aerodynamic performance of the aircraft model, thereby improving the richness and authenticity of the aircraft model simulation verification data.

[0027] As an embodiment of the present invention, the tail section of the push rod 3 is provided with a thread, and the push rod 3 is installed on the column 4 by rotating the thread, and a positioning nut 33 is provided at the contact point of the push rod 3 on the outside of the column 4; when working, the extension length of the push rod 3 on the column 4 is adjusted by rotation to adapt to the engine position on different types of aircraft models. The set positioning nut 33 limits the positioned push rod 3, ensuring the precise control of the action position of the push rod 3 in the aircraft model simulation, and improving the versatility of the aircraft model simulation verification platform.

[0028] As an embodiment of the present invention, a base 6 is provided below the column 4, and support rods 61 are provided at three positions on the base 6, and the base 6 and the column 4 are connected through the support rods 61; a fixed spherical joint 611 is provided at the upper end of the support rod 61, and the spherical joint 611 is rotatably installed in the spherical hole at the bottom of the column 4; the lower end of the support rod 61 is located in the hole groove inside the base 6, and a servo motor 62 is provided at the bottom of the hole groove; a lead screw pair 63 is provided inside the support rod 61, and the lead screw pair 63 is driven by the servo motor 62 to make the support rod 61 rise and fall on the base 6; when working In the simulation, the aircraft model needs to be positioned in different postures to simulate the take-off, landing and rotation processes of the aircraft in operation. The aircraft model needs to be adjusted to the required posture in the wind tunnel for multiple times before performing flight simulation verification, which reduces the simulation verification efficiency of the aircraft model and increases the workload. The servo motor 62 is controlled by the controller to operate, so that the support rod 61 is raised to different heights, thereby changing the tilt angle of the column 4, and the top rod 3 also changes its posture accordingly, which is convenient for the aircraft model to change its own posture during different movements, and improves the richness and authenticity of the aircraft model simulation verification data.

[0029] When working, the controller is started, the telescopic frame 12 is extended, so that the bearing block 2 is raised, and the aircraft model is placed on the bearing block 2. The position of the column 4 is adjusted on the base 1 so that the head of the push rod 3 is correspondingly fitted to the tail position of the engine of the aircraft model. The fan is started by controlling the motor to blow from the head direction of the aircraft model to simulate the interaction between the aircraft and the wind when flying. At the same time, the telescopic frame 12 is gradually retracted to lower the bearing block 2 so that the bearing block 2 falls into the pit 11 of the base 1. The aircraft model is lifted in the vertical direction by the lift of the wind, and the aircraft model is supported in the horizontal direction by the push rod at the tail position of the engine. 3. Positioning; the push rod 3 arranged at the tail of the aircraft model engine, through the force generated by the airflow generated in the wind tunnel on the aircraft model, makes the aircraft model only act on the push rod 3 to perform aerodynamic performance simulation verification, by setting the push rod 3 in contact with the tail of the aircraft model engine, with the slight change of the wind force parameters in the wind tunnel, the aircraft model makes a slight adaptive attitude adjustment in the simulation verification, and obtains more complete aerodynamic performance data; the truncated cone-shaped airbag 31 is arranged at the head of the push rod 3, and the middle part of the airbag 31 is concave so that the push rod 3 can be accurately positioned at the tail of the aircraft model engine, and at the same time Under the action of the wind force in the wind tunnel, the shape of the tail of the engine of the aircraft model causes the contact surface shape of the airbag 31 to change accordingly, thereby avoiding the deviation of the positioning of the push rod 3 on the tail of the aircraft model engine; the airbag 31 arranged at the head of the push rod 3 can feedback the engine force conditions at different positions on the aircraft model, and the air pressure data of the airbag 31 is fed back to the processing module of the controller through the pressure sensor, and then the size of the wind force in the wind tunnel is adjusted by the controller to be within the reasonable range of the simulation verification, so as to avoid the aircraft model in the wind tunnel being blown up or dropped in the simulation and terminating the verification process; the controller is set to control the micro air pump 5 The air pressure regulator 51 makes the airbag 31 at the head of each push rod 3 have different air pressure values ​​to simulate the working conditions of each engine of the aircraft under different working conditions; the set positioning nut limits the push rod after adjustment and positioning, ensuring the precise control of the working position of the push rod 3 in the aircraft model simulation; the set controller controls the operation of the servo motor 62, so that the support rod 61 is raised to different heights respectively, thereby changing the tilt angle of the column 4, and the push rod 3 also changes its posture accordingly, which is convenient for the aircraft model to change its own posture during different movements, and improves the richness and authenticity of the aircraft model simulation verification data.

[0030] The above shows and describes the basic principles, main features and advantages of the present invention. It should be understood by those skilled in the art that the present invention is not limited to the above embodiments. The above embodiments and descriptions are only for explaining the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. An aircraft model simulation verification platform, comprising a base (1), a bearing block (2), a mandrel (3), a motor and a controller; characterized in that: The base (1) is provided with a pit (11), a telescopic frame (12) is installed in the pit (11), and a bearing block (2) is provided at the top of the telescopic frame (12): the telescopic frame (12) is driven by a hydraulic rod to control the movement of the bearing block (2) in the vertical direction; the bearing block (2) is used to support the aircraft model; a column (4) is provided at the rear of the aircraft model, and a push rod (3) is provided at the tail position of the engine of the aircraft model; the head of the push rod (3) is in contact with the tail of the engine of the aircraft model, and the tail of the push rod (3) is fixed on the column (4); the push rod (3) corresponds to the engine position of the aircraft model one by one, and the push rod (3) is fixedly installed on the base (1) through the column (4); the motor drives the fan of the simulation platform to operate, providing a wind source for the simulation verification of the aircraft model; the controller adjusts the wind force during the simulation verification process by controlling the power of the motor, and the controller drives the lifting of the bearing block (2) by controlling the action of the hydraulic rod on the telescopic frame (12); The head of the push rod (3) is provided with an air bag (31), which is in the shape of a truncated cone. The small end face of the truncated cone-shaped air bag (31) is fixedly connected to the head of the push rod (3), and the large end face of the truncated cone-shaped air bag (31) faces the engine tail of the aircraft model; the middle part of the large end face of the air bag (31) is concave, and is used to fit on the engine tail of the aircraft model; An air pipe (32) is arranged inside the push rod (3); a micro air pump (5) is arranged on the column (4); one end of the air pipe (32) is connected to the air bag (31), and the other end of the air pipe (32) is connected to the micro air pump (5) through the tail of the push rod (3); a pressure sensor is arranged on the micro air pump (5); the pressure sensor feeds back the pressure value of the air bag (31) at the head of the push rod (3) through the air pipe (32); The micro air pump (5) is provided with an air pressure regulator (51), and the air pressure regulator (51) is controlled by a controller; the controller can adjust the air pressure value in each air bag (31) through the air pressure regulator (51); The tail section of the push rod (3) is provided with a thread, and the push rod (3) is rotatably mounted on the column (4) through the thread, and a positioning nut (33) is provided at the contact point of the push rod (3) with the outside of the column (4); A base (6) is provided below the column (4), and support rods (61) are provided at three positions on the base (6), and the base (6) and the column (4) are connected via the support rods (61); a fixed spherical joint (611) is provided at the upper end of the support rod (61), and the spherical joint (611) is rotatably mounted in a spherical hole at the bottom of the column (4); the lower end of the support rod (61) is located in a hole groove inside the base (6), and a servo motor (62) is provided at the bottom of the hole groove; a lead screw pair (63) is provided inside the support rod (61), and the lead screw pair (63) is driven by the servo motor (62) to make the support rod (61) rise and fall on the base (6); The controller is started, the telescopic frame (12) is extended, so that the bearing block (2) is raised, and the aircraft model is placed on the bearing block (2). The position of the adjustment column (4) is installed on the base (1) so that the head of the push rod (3) is correspondingly fitted to the tail position of the aircraft model engine. The fan is started by controlling the motor to blow from the head direction of the aircraft model, simulating the interaction between the aircraft and the wind when flying. At the same time, the telescopic frame (12) is gradually retracted to lower the bearing block (2) so that the bearing block (2) falls into the pit (11) of the base (1). The aircraft model is lifted up in the vertical direction by the lift force of the wind, and the aircraft model is positioned in the horizontal direction by the push rod (3) at the tail position of the engine. The push rod (3) arranged at the tail of the aircraft model engine generates a force on the aircraft model through the airflow generated in the wind tunnel, so that the aircraft model only interacts with the push rod (3) to perform aerodynamic performance simulation verification. The push rod (3) is connected to the tail of the aircraft model engine. The push rod (3) is provided with a truncated cone-shaped airbag (31) at the head of the push rod (3), and the middle part of the airbag (31) is concave, so that the push rod (3) can be accurately positioned at the tail position of the engine of the aircraft model. At the same time, under the action of the wind force in the wind tunnel, the shape of the tail of the engine of the aircraft model causes the contact surface shape of the airbag (31) to change accordingly, thereby avoiding the deviation of the push rod (3) being positioned at the tail position of the engine of the aircraft model; the airbag (31) provided at the head of the push rod (3) can feedback the force conditions of the engine at different positions on the aircraft model, and the air pressure data of the airbag (31) is fed back to the processing module of the controller through the pressure sensor, and then the size of the wind force in the wind tunnel is adjusted by the controller to be within the reasonable range of the simulation verification, so as to avoid the aircraft model in the wind tunnel being blown up or dropped during the simulation and terminating the verification process; A controller is provided to control the air pressure regulator (51) on the micro air pump (5), so that the airbag (31) at the head of each push rod (3) has different air pressure values, so as to simulate the working conditions of each engine of the aircraft under different working conditions; The positioning nut is set to limit the push rod after adjustment and positioning, ensuring accurate control of the action position of the push rod (3) in the aircraft model simulation; the controller is set to control the operation of the servo motor (62), so that the support rod (61) is raised to different heights respectively, thereby causing the column (4) to change its tilt angle, and the push rod (3) also changes its posture accordingly, which facilitates the posture change of the aircraft model itself during different movement processes, thereby improving the richness and authenticity of the aircraft model simulation verification data.

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