Aircraft wind tunnel test model wide-range attack angle change tail / web support device

Abstract

The invention discloses a model wide-range attack angle change tail and web support device suitable for an airplane wind tunnel test, which comprises two support modes, namely a curved knife support rod and a web support support rod, an attack angle change mechanism, a lifting compensation mechanism and a mounting base, and is characterized in that a wind tunnel airplane model is arranged at the end part of the support rod, and the support rod is in screw connection with the attack angle change mechanism; the attack angle changing mechanism is connected to the lifting compensation mechanism through the mounting base, and the lifting compensation mechanism is mounted in wind tunnel test equipment. According to the invention, the large-range attack angle change of the airplane model in the wind tunnel test can be realized, and the center is kept unchanged at the height of the wind tunnel test.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft wind tunnel tests, and in particular relates to a tail and belly support device suitable for aircraft wind tunnel tests with a wide range of fuselage angle of attack changes. Background Art

[0002] Wind tunnel testing plays an irreplaceable role in the field of aerospace. China has also made significant progress in the field of wind tunnel testing. The Aerodynamics Research and Development Center of the Chinese Academy of Sciences has developed the world's largest aerodynamic simulation wind tunnel, which can simulate the flight conditions of supersonic aircraft and provide important support for the design and development of my country's supersonic aircraft.

[0003] Wind tunnel testing is an experimental method for testing the aerodynamic performance of aircraft models by simulating wind field conditions. This test can evaluate the aerodynamic characteristics of an aircraft under different flight conditions, including aerodynamic force, structural strength and flight characteristics. In the aerospace field, wind tunnel testing promotes the progress and innovation of aircraft design. By simulating the air flow of an aircraft under real flight conditions in a wind tunnel, flight characteristics can be verified, providing important support and guidance for optimizing the design and improving the flight efficiency and safety performance of the aircraft.

[0004] There are many forms of support for wind tunnel tests, usually including belly support, back support, tail support, vertical tail support, double support under the wing, "Z"-shaped support, three-point support and tension line support. The support method of the aircraft model may affect the stability, posture and airflow of the aircraft model in the wind tunnel. Each method has its advantages and disadvantages. It is important to choose the appropriate support method according to different requirements. By changing the support method, the performance of the aircraft under different flight conditions can be simulated, so as to better understand the flight characteristics of the aircraft.

[0005] The model support system of existing aircraft wind tunnel tests has the problems of single support mode, small angle of attack change, and the inability of the model's center of mass to always remain at the height required by the wind tunnel test during the entire angle of attack change operation, which is not conducive to ensuring the integrity and accuracy of the test data. Summary of the invention

[0006] In order to solve the problems of the existing model support system of aircraft wind tunnel tests having a single support mode, small angle of attack change, and inability to always keep the model's center of mass at the required height during operation, the present invention proposes a model support system suitable for aircraft wind tunnel tests, which can effectively increase the angle of attack change range, always keep the center of mass at the height required by the wind tunnel test, thereby ensuring the integrity of the test data and improving the stability of the test data.

[0007] To achieve the above-mentioned purpose, the technical solution adopted by the present invention is: a tail and belly support device with a large range of angle of attack change of the model suitable for aircraft wind tunnel tests, including two support methods of scimitar support rods and belly support rods, an angle of attack change mechanism, a lifting and compensating mechanism, and a mounting base. The aircraft model is arranged at the end of the support rod, the angle of attack change mechanism is arranged at the bottom of the support rod, and the lifting and compensating mechanism is arranged at the bottom of the angle of attack change mechanism. The angle of attack change mechanism is connected to the lifting and compensating mechanism through the mounting base, and the lifting and compensating mechanism is installed in the equipment of the wind tunnel test through the base; the angle of attack change mechanism is driven by a servo motor and performs rotational motion on an arc guide rail, and the lifting and compensating mechanism is controlled by an electric cylinder to perform linear motion. The two motions are combined through linkage to make the angle of attack of the aircraft model continuously and controllably change, and the height of the model center in the wind tunnel test section always remains unchanged.

[0008] Furthermore, the support rod has two supporting modes: a scimitar support rod and a belly support rod. The support rod can be replaced according to different supporting forms of the aircraft model. The support rod base at the bottom of the support rod is bolted to the angle of attack changing mechanism to ensure that it can rotate with it to achieve the change of the angle of attack of the aircraft model.

[0009] Furthermore, the angle of attack change of the aircraft model is controlled by the angle of attack change mechanism, and the lifting compensation mechanism causes the angle of attack change mechanism to move up and down, carrying the aircraft model to move in the angle of attack change and up and down directions, and the angle of attack change movement and the up and down movement are unidirectionally coupled; the unidirectional coupling is that the up and down movement does not affect the change of the pitch angle movement, and the angle of attack change movement does not cause the change of the center height of the model.

[0010] When the angle of attack of the aircraft model changes during the wind tunnel test, the angle of attack changing mechanism and the lifting compensation mechanism are controlled to move simultaneously to ensure that the center of the aircraft model always meets the required height in the wind tunnel test section during the change of the angle of attack of the test model.

[0011] The lifting compensation mechanism is composed of a driving motor and a motor support, an auxiliary support rod and a base. Furthermore, the driving electric cylinder and the electric cylinder support drive the electric cylinder through a servo motor and are equipped with a specially designed electric cylinder support structure to ensure that the electric cylinder remains stable and prevents tilting during the upward pushing process. The electric cylinder drives the mounting base to move up and down, thereby causing the angle of attack changing mechanism to move up and down.

[0012] The auxiliary support rod includes a fixed column, a sliding support rod, a slider 1, a slider 2, a guide rail 1 and a guide rail 2. The auxiliary support rod is installed on the base through the fixed column. The track 1 on the fixed column and the slider 1 on the sliding support rod constitute a moving pair, and the track 2 on the sliding support rod and the slider 2 on the fixed column constitute a moving pair, which can reduce the effect of the torque generated by the continuous rise of the sliding support rod.

[0013] Furthermore, the angle of attack changing mechanism is composed of an arc-shaped support, an arc-shaped track and a support rod base. The servo motor drives the gear to rotate, and the gear engages with the arc-shaped rack, driving the support rod base to move along the arc-shaped track, thereby driving the support rod on the support rod base, thereby realizing flexible adjustment of the angle of attack of the aircraft model in a wide range.

[0014] The support rod support includes an upper cover and side covers on both sides. A servo motor is arranged on the outer side of the side cover, and gears and sliders are arranged on the inner side. The gears are connected to the servo motor, and the sliders are fitted with arc guide rails to guide the support rod support to slide on the arc support.

[0015] The arc track is installed on the arc support by bolts, and the arc gear is installed on the arc support. The arc gear is meshed with the gear. Under the drive of the servo motor, the gear is meshed with the arc gear. At the same time, the support rod base connected to the servo motor slides on the arc guide rail through a slider, thereby realizing the movement of the support rod base on the arc support.

[0016] Furthermore, the arc support is further provided with an adaptive change mechanism on the existing basis. The adaptive change mechanism includes an arc mounting block, and the arc mounting block is connected to the arc support by a connecting plate, so as to increase the range of angle of attack change. The arc support can be installed and used when the aircraft model needs to change over a large range.

[0017] The beneficial effects of adopting this technical solution are: The present invention adopts a linkage mechanism between a pitch angle motion mechanism and a lifting compensation mechanism to achieve a large-range continuous adjustment of the pitch angle of the aircraft model. On the premise of maintaining a constant center height of the aircraft model, the pitch angle change is used to simulate the aircraft's conditions in different postures, which is suitable for wind tunnel test application scenarios of such aircraft models.

[0018] The present invention provides an adaptive change mechanism to enable the aircraft model to have a larger pitch angle, which is particularly suitable for the wind tunnel test environment of high-elevation-angle dynamic simulation. At the same time, the support rods include tail support and belly support. The tail support design is suitable for high-angle-of-attack situations, ensuring the structural stability of the model and the reliability of the test data in different postures; while the belly support mode optimizes the bottom airflow interference and is suitable for test cases that are sensitive to downwash. The two support rods can be flexibly installed and used according to the specific experimental conditions and the model's load-bearing requirements, which not only reduces aerodynamic interference but also improves the versatility and efficiency of wind tunnel tests. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic structural diagram of a model pitch angle motion support device suitable for a wing-body fusion aircraft wind tunnel test according to the present invention; Figure 2 It is a schematic diagram of the motion principle of the model pitch angle motion support device suitable for the wind tunnel test of the wing-body fusion aircraft of the present invention; Figure 3 The adaptive change mechanism of the model pitch angle motion support device suitable for the wind tunnel test of the wing-body fusion aircraft of the present invention; Figure 4 The invention discloses an angle of attack variation mechanism of a model pitch angle motion support device suitable for a wing-body fusion aircraft wind tunnel test.

[0020] Among them, 1-support rod, 2-support rod, 3-pull rod, 4-slider connecting rod, 5-slider one, 6-screw of the first worm gear screw elevator, 7-pitch motion motor, 8-second worm gear screw elevator, 9-lifting motion motor, 10-screw of the second worm gear screw elevator, 11-first worm gear screw elevator, 12-base, 13-motion controller, 14-wing-body fusion aircraft model, 15-wind tunnel foundation, 16-sliding guide rail one, 17-gear, 18-servo motor mounting plate, 19-arc rack-, 20-slider, 21-support rod connecting plate, 22-arc mounting block, 23-connecting plate. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical solutions and advantages of the present invention more clear, the present invention is further described below with reference to the accompanying drawings.

[0022] In this embodiment, see Figure 1 As shown, the present invention proposes a model support system suitable for aircraft wind tunnel tests, characterized in that it includes struts 4 and 6, an angle of attack variation mechanism, a lifting compensation mechanism and a base 10, the aircraft model 5 is placed at the end of the strut 4 or 6, the strut 4 or 6 is connected to the angle of attack variation mechanism by bolts, the angle of attack variation mechanism is driven by a servo motor to control the angle of attack variation, the angle of attack variation mechanism is fixed to the lifting compensation mechanism by a mounting base 7, the lifting compensation mechanism is built into a specific position of the wind tunnel test equipment through the base 10, and the height of the center of the aircraft model in the wind tunnel test section is ensured to remain unchanged through the joint movement of the angle of attack variation mechanism and the lifting compensation mechanism.

[0023] Based on the optimized embodiment 1 of the above implementation scheme, the ends of the struts 4 and 6 are connected to the aircraft model. The struts are divided into scimitar (tail strut) struts 4 and belly struts 6, two different structural modes to adapt to the different support requirements of the model at the tail or belly position. Different struts can be installed according to different test environment requirements to ensure the structural stability of the model in different postures and the reliability of the test data.

[0024] In the wind tunnel test, the angle of attack change mechanism controls the angle of attack change of the aircraft model 5, the lifting and lowering compensation mechanism makes the angle of attack change mechanism move up and down, thereby realizing the up and down compensation movement of the aircraft model 5, and the pitch angle movement mechanism and the lifting and lowering compensation mechanism move simultaneously to ensure that the height of the center of the aircraft model 5 in the wind tunnel test section remains unchanged during the pitch angle change of the test model.

[0025] Based on the optimized embodiment 2 of the above implementation scheme, the model support system suitable for aircraft wind tunnel test is characterized in that the lifting and lowering compensation mechanism is connected to the angle of attack change mechanism through the mounting base 7, and the lifting and lowering compensation mechanism is divided into a driving motor and motor support 8, an auxiliary support rod 9 and a base 10.

[0026] The driving electric cylinder and the electric cylinder support 8 are driven by a servo motor and a specially designed electric cylinder support structure is designed to ensure that the electric cylinder remains stable and prevents tilting during the upward pushing process. The electric cylinder drives the mounting base 7 to move up and down, thereby causing the angle of attack changing mechanism to move up and down.

[0027] Based on the optimized embodiment 3 of the above implementation scheme, see Figure 2 As shown, the auxiliary support rod 9 of the lifting compensation mechanism is composed of a fixed column 11, a sliding support rod 12, a slider 1, a slider 2, a guide rail 1 and a guide rail 2, which can keep the center of mass of the model always at the height required by the wind tunnel test.

[0028] The auxiliary support rod 9 is installed on the base 10 through a fixing column 11, which is used to support the auxiliary support rod to ensure that the auxiliary support rod does not fall over.

[0029] The track 1 arranged on the fixed column 11 and the slider 1 arranged on the sliding support rod 12 form a moving pair, which is used to guide the sliding support rod during the pushing process of the electric cylinder.

[0030] The track 2 on the sliding support rod 12 and the slider 2 on the fixed column form a moving pair. When the electric cylinder pushes the angle of attack changing mechanism to a certain height, it can prevent the sliding support rod from being subjected to excessive overturning torque, thereby ensuring the stability of the system.

[0031] The base 10 has the lifting compensation mechanism built into a specific position of the wind tunnel test equipment to ensure that during the entire angle of attack change operation, the center of mass of the model always remains unchanged at the height required by the wind tunnel test, thereby ensuring the validity and accuracy of the test data.

[0032] Based on the optimized embodiment 4 of the above implementation scheme, see Figure 3As shown, the angle of attack changing mechanism consists of an arc-shaped support 1, an arc-shaped track 2, an arc-shaped rack 19 and a support rod base 3. The motor drives the gear to rotate, and the gear engages with the arc-shaped rack, driving the support rod base 3 to move along the arc-shaped track 2, thereby driving the support rod on the support rod base, thereby realizing flexible adjustment of the angle of attack of the aircraft model in a wide range.

[0033] The support rod base 3 includes an upper cover and side covers on both sides. A servo motor is arranged on the outer side of the side cover, and a gear 17 and a slider 20 are arranged on the inner side. The gear 17 is connected to the servo motor. At the same time, the slider 20 is fitted with the arc guide rail 2 to guide the support rod support to slide on the arc support.

[0034] In the preferred solution of the above embodiments, the arc-shaped support is further provided with an adaptive change mechanism on the existing basis, see Figure 3 As shown, the adaptive change mechanism includes an arc-shaped mounting block 22, which is connected to the arc-shaped support 1 by a connecting plate 23, so as to increase the range of angle of attack change, and can be installed and used when the aircraft model needs to be changed in a large range.

[0035] The preferred solution of each of the above embodiments is that the angle of attack changing mechanism is connected to the aircraft model through (different) struts, and has two different structural modes, namely the scimitar strut 4 and the belly support strut 6, to adapt to the different support requirements of the model at the tail or belly position.

[0036] In the preferred scheme of the above-mentioned embodiments, the lifting and compensating mechanism is built into a specific position of the wind tunnel test equipment through a base, and the electric cylinder on the lifting and compensating mechanism is driven by a servo motor to push the mounting base, thereby causing the angle of attack changing mechanism on the mounting base to move up and down, and under the action of the auxiliary support rod, the center of mass of the model is always kept at the height required by the wind tunnel test. The support rod base on the angle of attack changing mechanism moves along an arc track under the drive of the motor, driving the support rod to achieve flexible changes in a wide range of angles of attack, thereby achieving flexible adjustment of a wide range of angles of attack of the aircraft model. The end of the support rod is connected to the aircraft model, and is divided into two different structural modes: a scimitar support rod and a belly support rod, to adapt to the different support requirements of the model at the tail or belly position.

[0037] The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions are only for illustrating 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 shall fall within the scope of the present invention to be protected. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. A model support system suitable for aircraft wind tunnel testing, characterized in that: The invention comprises struts (4) and (6), an angle of attack variation mechanism, a lifting compensation mechanism and a base (10), wherein the aircraft model (5) is arranged at the end of the struts (4) or (6), the struts (4) or (6) are connected to the angle of attack variation mechanism via bolts, the angle of attack variation mechanism is driven by a servo motor to control the angle of attack variation, the angle of attack variation mechanism is fixed to the lifting compensation mechanism via a mounting base (7), and the lifting compensation mechanism is built into a specific position of the wind tunnel test equipment via the base (10).

2. The model support system suitable for aircraft wind tunnel testing according to claim 1, characterized in that: The ends of the struts (4) and (6) are connected to the aircraft model. The struts are divided into two different structural modes: a scimitar (tail strut) strut (4) and a belly strut strut (6) to meet the different support requirements of the model at the tail or belly position.

3. According to claim 1, the angle of attack variation mechanism controls the angle of attack variation of the aircraft model (5), and the lifting compensation mechanism causes the angle of attack variation mechanism to move up and down, thereby realizing the up and down compensation movement of the aircraft model (5).

4. The model support system suitable for aircraft wind tunnel testing according to claim 3, characterized in that: The lifting and compensating mechanism is connected to the angle of attack changing mechanism via a mounting base (7), and the lifting and compensating mechanism is divided into a driving motor and a motor support (8), an auxiliary support rod (9) and a base (10); The driving electric cylinder and the electric cylinder support (8) drive the electric cylinder through a servo motor and are matched with a specially designed electric cylinder support structure, so that the electric cylinder can remain stable and prevent tilting during the upward pushing process. The electric cylinder drives the mounting base (7) to move up and down, thereby causing the angle of attack changing mechanism to move up and down.

5. The auxiliary support rod (9) of the lifting compensation mechanism according to claim 4, which is composed of a fixed column (11), a sliding support rod (12), a slider 1 (13), a slider 2 (16), a guide rail 1 (14) and a guide rail 2 (15), can keep the center of mass of the model always at the height required by the wind tunnel test; The auxiliary support rod (9) is mounted on the base (10) via a fixed column (11) and is used to support the auxiliary support rod; The track 1 (14) provided on the fixed column (11) and the slider 1 (13) provided on the sliding support rod (12) form a moving pair, which is used to guide the sliding support rod during the pushing process of the electric cylinder; The track 2 (15) arranged on the sliding support rod (12) and the slider 2 (16) arranged on the fixed column (11) form a moving pair. When the electric cylinder pushes the angle of attack changing mechanism to rise to a certain height, the sliding support rod can be prevented from being subjected to excessive overturning torque, thereby ensuring the stability of the system.

6. According to claims 3-5, the base (10) has a lifting compensation mechanism built into a specific position of the wind tunnel test equipment to ensure that during the entire angle of attack change operation, the center of mass of the model always remains at the height required by the wind tunnel test, thereby ensuring the validity and accuracy of the test data.

7. According to claim 3, the angle of attack changing mechanism is composed of an arc-shaped support (1), an arc-shaped track (2), an arc-shaped rack (19) and a support rod base (3); the motor drives the gear to rotate, and the gear meshes with the arc-shaped rack, driving the support rod base (3) to move along the arc-shaped track (2), thereby driving the support rod on the support rod base, so as to realize flexible adjustment of the angle of attack of the aircraft model in a wide range; The support rod base (3) comprises an upper cover and two side covers, a servo motor is arranged on the outer side of the side cover, and a gear (17) and a slider (20) are arranged on the inner side of the side cover, the gear (17) is connected to the servo motor, and the slider (20) is fitted with the arc guide rail (2) to guide the support rod support to slide on the arc support; The arc-shaped support is further provided with an adaptive change mechanism on the existing basis. The adaptive change mechanism comprises an arc-shaped mounting block (22). The arc-shaped mounting block (22) is connected to the arc-shaped support (1) by a connecting plate (23) so as to increase the range of angle of attack change. The invention can be installed and used when the aircraft model needs to be changed within a large range.

8. The angle of attack variation mechanism according to claim 7 is connected to the aircraft model via (different) struts, with two different structural modes, namely the scimitar strut (4) and the belly strut (6), to meet the different support requirements of the model at the tail or belly position.

9. According to claims 1-8, the lifting and compensating mechanism is built into a specific position of the wind tunnel test equipment through a base, and the electric cylinder on the lifting and compensating mechanism is driven by a servo motor to push the mounting base, thereby making the angle of attack changing mechanism on the mounting base move up and down, and under the action of the auxiliary support rod, the center of mass of the model is always kept at the height required by the wind tunnel test. The support rod base on the angle of attack changing mechanism moves along an arc track under the drive of the motor, driving the support rod to achieve a wide range of flexible changes in the angle of attack, thereby achieving a wide range of flexible adjustment of the angle of attack of the aircraft model. The end of the support rod is connected to the aircraft model, and is divided into two different structural modes: a scimitar support rod and a belly support rod, to adapt to the different support requirements of the model at the tail or belly position.

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