Force measuring device for static and dynamic wind tunnel test with super-large angle of attack of 180 degrees

Abstract

The invention discloses a 180-degree super-large attack angle static and dynamic wind tunnel test force measuring device which comprises a wind tunnel, an attack angle mechanism, a follow-up mechanism, a first supporting rod, a balance, a wind tunnel test model and a second supporting rod. The balance is of a'double-measuring-end 'integral structure and is arranged in the wind tunnel; the attack angle mechanism and the follow-up mechanism are installed on the upper side and the lower side outside the wind tunnel respectively. A driving shaft of the attack angle mechanism and a follow-up shaft of the follow-up mechanism are respectively inserted into the wind tunnel, and the axes of the two are coaxial; the first supporting rod is installed on the driving shaft, and the second supporting rod is installed on the follow-up shaft. The first fixed end of the balance is connected with the first support rod, and the second fixed end is connected with the second support rod. The force measuring device can achieve 0-180-degree static test and large-amplitude oscillation dynamic test simulation, double-measuring-end balance design and measurement are adopted, the problem that rigidity / strength of a single connection model is insufficient is solved, two parts of aerodynamic force of the model can be measured at the same time, and pneumatic analysis and support interference deduction are facilitated.

Description

Technical Field

[0001] The invention belongs to the technical field of experimental aerodynamic measurement, and in particular relates to a 180° ultra-large attack angle static and dynamic wind tunnel test force measuring device. Background Art

[0002] A certain aircraft is required to be able to achieve a 180° angle of attack maneuver and redirect in a very short time, so as to achieve a quick U-turn and handle the target behind, which puts higher requirements on the aircraft aerodynamic design and wind tunnel test technology. The current wind tunnel test technology cannot fully meet the development needs of such aircraft in terms of the simulated angle of attack range, static / dynamic simulation capabilities, and high-precision aerodynamic measurement capabilities.

[0003] In terms of static test capability, the maximum angle of attack of traditional tail support test technology does not exceed 90°, and the measurement method of adding preset attack angles and changing the support form in sections will introduce data connection problems and the problem that segment interference cannot be uniformly corrected.

[0004] In terms of dynamic test capabilities, the pitch amplitude of existing mainstream test technologies is generally 30°, the maximum angle of attack does not exceed 90°, and the test oscillation frequency does not exceed 3Hz. However, when the pitch amplitude is increased, the test frequency drops sharply.

[0005] In view of this, it is urgent to develop 180° ultra-large angle of attack static and dynamic wind tunnel test force measurement technology to break through the existing wind tunnel test difficulties and provide technical support for the development of advanced aircraft. Summary of the invention

[0006] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art and provide a 180° ultra-large angle of attack static and dynamic wind tunnel test force measuring device, aiming to solve the problem that the prior art has insufficient static and dynamic simulation and measurement capabilities for such wind tunnel tests.

[0007] In order to solve the above technical problems, the present invention discloses a 180° large attack angle static and dynamic wind tunnel test force measuring device, comprising: a wind tunnel, an attack angle mechanism, a follower mechanism, a first support rod, a balance 、 A wind tunnel test model and a second support rod; wherein a balance is arranged in the wind tunnel; an angle of attack mechanism and a follower mechanism are respectively installed on the upper and lower sides outside the wind tunnel; a driving shaft of the angle of attack mechanism and a follower shaft of the follower mechanism are respectively inserted into the wind tunnel, and the axes of the two are coaxial; the first support rod is installed on the driving shaft, and the second support rod is installed on the follower shaft; a first fixed end of the balance is connected to the first support rod, and a second fixed end of the balance is connected to the second support rod; during the test, the wind tunnel test model is installed on the balance.

[0008] In the above-mentioned 180° ultra-large angle of attack static and dynamic wind tunnel test force measuring device, the balance is a "double measuring end" integral structure, including: a first measuring end, a first measuring element, a first fixed end, a second measuring element, a second measuring end and a second fixed end; wherein the first fixed end and the second fixed end are respectively arranged on the upper and lower sides of the center of the balance, and together constitute the fixed end of the balance; the first measuring end is connected to the first measuring element and is arranged on one side of the fixed end; the second measuring end is connected to the second measuring element and is symmetrically arranged on the other side of the fixed end.

[0009] In the above-mentioned 180° ultra-large attack angle static and dynamic wind tunnel test force measuring device, the attack angle mechanism includes: a drive motor, a motor base, a reducer, a reducer base, a first coupling, a first bearing seat and a drive shaft; wherein the drive motor, the reducer, the first coupling and the drive shaft are connected in sequence; the drive motor is installed on the motor base; the reducer is installed on the reducer base; the drive shaft is installed on the first bearing seat through two sets of bearings.

[0010] In the above-mentioned 180° ultra-large attack angle static and dynamic wind tunnel test force measuring device, the follower mechanism includes: a follower shaft, a second bearing seat, a second coupling, an encoder seat and an attack angle encoder; wherein the follower shaft, the second coupling and the attack angle encoder are connected in sequence; the follower shaft is installed on the second bearing seat through two sets of bearings; and the attack angle encoder is installed on the encoder seat.

[0011] In the above-mentioned 180° ultra-large attack angle static and dynamic wind tunnel test force measuring device, the wind tunnel test model includes: a model head, a first model middle section, a second model middle section and a model tail; wherein the model head is installed on the first model middle section, together constituting the model front section; the model tail is installed on the second model middle section, together constituting the model rear section; the first model middle section is installed on the first measuring end of the balance; the second model middle section is installed on the second measuring end of the balance.

[0012] In the above-mentioned 180° ultra-large angle of attack static and dynamic wind tunnel test force measuring device, during the test, by inputting different motion control instructions to the drive motor, the wind tunnel test model can be subjected to static force measurement tests with an attack angle range of 0° to 180° and large-scale oscillation dynamic force measurement test simulations around the axis of the drive shaft in the horizontal plane of the wind tunnel.

[0013] In the above-mentioned 180° ultra-large angle of attack static and dynamic wind tunnel test force measuring device, the axis of the angle of attack encoder is coaxial with the axis of the drive shaft, and is used to measure the angle of attack of the wind tunnel test model.

[0014] In the above-mentioned 180° ultra-large angle of attack static and dynamic wind tunnel test force measuring device, the balance realizes dual six-component measurement based on the first measuring element and the second measuring element; wherein, the first measuring element is used to measure the six-component aerodynamic force of the front section of the model; the second measuring element is used to measure the six-component aerodynamic force of the rear section of the model; the aerodynamic force of the wind tunnel test model is obtained by coordinate synthesis of the six-component aerodynamic force of the front section of the model and the six-component aerodynamic force of the rear section of the model.

[0015] In the above-mentioned 180° ultra-large angle of attack static and dynamic wind tunnel test force measuring device, semicircular holes are respectively opened on the middle section of the first model and the middle section of the second model. After the middle section of the first model and the middle section of the second model are butt-jointed and installed, a complete circular hole is formed; the first fixed end and the second fixed end pass through the upper and lower parts of the circular hole respectively; the gap t between the outer wall surface of the fixed end and the inner wall surface of the circular hole is ≥2mm, ensuring that the fixed end does not touch the circular hole.

[0016] In the above-mentioned 180° ultra-large attack angle static and dynamic wind tunnel test force measuring device, a maze structure is formed at the docking position between the middle section of the first model and the middle section of the second model, and the single-side gap h≥2mm.

[0017] The present invention has the following advantages:

[0018] (1) The present invention provides a 180° ultra-large angle of attack static and dynamic wind tunnel test force measuring device, which adopts a "double measuring end" balance design and measurement, effectively shortening the balance force transmission path, significantly improving the overall stiffness of the force measuring device, and is conducive to improving the dynamic test frequency and static and dynamic force measurement accuracy of the force measuring device.

[0019] (2) The present invention provides a 180° ultra-large angle of attack static and dynamic wind tunnel test force measuring device, in which the front section and the rear section of the model are respectively installed at the two measuring ends of the balance, which not only avoids the problem of insufficient stiffness / strength of a single-connection model; at the same time, it can also realize the separate and simultaneous measurement of the aerodynamic forces of the two parts of the model, which is convenient for aerodynamic analysis and support interference deduction.

[0020] (3) The present invention provides a 180° ultra-large angle of attack static and dynamic wind tunnel test force measurement device, which can realize a wind tunnel test model in a horizontal plane in the wind tunnel around the axis of the drive shaft to perform a static force measurement test with an attack angle range of 0° to 180° and a large-scale oscillation dynamic force measurement test simulation by inputting different motion control instructions to the drive motor. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic structural diagram of a 180° ultra-large angle of attack static and dynamic wind tunnel test force measuring device according to an embodiment of the present invention;

[0022] Figure 2 It is a schematic diagram of the installation of a wind tunnel test model-balance-support rod in an embodiment of the present invention;

[0023] Figure 3 It is a structural schematic diagram of a balance in an embodiment of the present invention;

[0024] Figure 4 yes Figure 2 AA section view. DETAILED DESCRIPTION

[0025] In order to make the objectives, technical solutions and advantages of the present invention more clear, the embodiments disclosed in the present invention will be further described in detail below with reference to the accompanying drawings.

[0026] Reference Figures 1 to 4 In this embodiment, the 180° large angle of attack static and dynamic wind tunnel test force measuring device comprises: a wind tunnel 1, an angle of attack mechanism, a follower mechanism, a first support rod 9, a balance 10, a wind tunnel test model 11 and a second support rod 12. The balance 10 is arranged in the wind tunnel 1; the angle of attack mechanism and the follower mechanism are respectively installed on the upper and lower sides outside the wind tunnel 1; the driving shaft 8 of the angle of attack mechanism and the follower shaft 13 of the follower mechanism are respectively inserted into the wind tunnel 1, and the axes of the two are coaxial; the first support rod 9 is installed on the driving shaft 8, and the second support rod 12 is installed on the follower shaft 13; the first fixed end 1003 of the balance 10 is connected to the first support rod 9, and the second fixed end 1006 of the balance 10 is connected to the second support rod 12; during the test, the wind tunnel test model 11 is installed on the balance 10.

[0027] In this embodiment, the balance 10 is a "double-measuring end" integral structure, including: a first measuring end 1001, a first measuring element 1002, a first fixed end 1003, a second measuring element 1004, a second measuring end 1005, and a second fixed end 1006. The first fixed end 1003 and the second fixed end 1006 are respectively arranged on the upper and lower sides of the center of the balance, and together constitute the fixed end of the balance; the first measuring end 1001 is connected to the first measuring element 1002 and is arranged on one side of the fixed end; the second measuring end 1005 is connected to the second measuring element 1004 and is symmetrically arranged on the other side of the fixed end.

[0028] Furthermore, the balance 10 implements dual six-component measurement based on the first measuring element 1002 and the second measuring element 1004. The first measuring element 1002 is used to measure the six-component aerodynamic force of the front section of the model; the second measuring element 1004 is used to measure the six-component aerodynamic force of the rear section of the model; the aerodynamic force of the wind tunnel test model 11 is obtained by coordinate synthesis from the six-component aerodynamic force of the front section of the model and the six-component aerodynamic force of the rear section of the model.

[0029] Furthermore, the balance 10 is made of high-strength alloy steel in one piece.

[0030] In this embodiment, the angle of attack mechanism mainly includes: a driving motor 2, a motor base 3, a reducer 4, a reducer base 5, a first coupling 6, a first bearing seat 7 and a driving shaft 8. The driving motor 2, the reducer 4, the first coupling 6 and the driving shaft 8 are connected in sequence; the driving motor 2 is mounted on the motor base 3; the reducer 4 is mounted on the reducer base 5; and the driving shaft 8 is mounted on the first bearing seat 7 through two sets of bearings.

[0031] In this embodiment, the follower mechanism mainly includes: a follower shaft 13, a second bearing seat 14, a second coupling 15, an encoder seat 16 and an angle of attack encoder 17. The follower shaft 13, the second coupling 15 and the angle of attack encoder 17 are connected in sequence; the follower shaft 13 is mounted on the second bearing seat 14 through two sets of bearings; the angle of attack encoder 17 is mounted on the encoder seat 16, and the axis of the angle of attack encoder 17 is coaxial with the axis of the drive shaft 8, which is used to measure the angle of attack of the wind tunnel test model 11.

[0032] In this embodiment, the wind tunnel test model 11 mainly includes: a model head 1101, a first model middle section 1102, a second model middle section 1103 and a model tail 1104. The model head 1101 is installed on the first model middle section 1102, together forming a model front section; the model tail 1104 is installed on the second model middle section 1103, together forming a model rear section; the first model middle section 1102 is installed on the first measuring end 1001 of the balance 10; and the second model middle section 1103 is installed on the second measuring end 1005 of the balance 10.

[0033] Furthermore, semicircular holes are respectively opened on the middle section 1102 of the first model and the middle section 1103 of the second model. After the middle section 1102 of the first model and the middle section 1103 of the second model are butt-jointed and installed, a complete circular hole is formed; the first fixed end 1003 and the second fixed end 1006 pass through the upper and lower parts of the circular hole respectively; the gap t between the outer wall surface of the fixed end and the inner wall surface of the circular hole is ≥ 2mm, ensuring that the fixed end does not touch the circular hole.

[0034] Furthermore, a maze structure 1105 is formed at the joint position between the first model middle section 1102 and the second model middle section 1103, and a single-side gap h≥2 mm.

[0035] In this embodiment, during the test, by inputting different motion control instructions to the drive motor 2, the wind tunnel test model 11 can be subjected to a static force measurement test and a large-scale oscillation dynamic force measurement test simulation with an attack angle range of 0° to 180° around the axis of the drive shaft 8 in the horizontal plane of the wind tunnel 1.

[0036] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

[0037] The contents not described in detail in the specification of the present invention belong to the common knowledge of the professionals in this field.

Claims

1. A 180° large attack angle static and dynamic wind tunnel test force measuring device, characterized in that: include: A wind tunnel (1), an angle of attack mechanism, a follower mechanism, a first support rod (9), a balance (10), a wind tunnel test model (11) and a second support rod (12); wherein the balance (10) is arranged in the wind tunnel (1); the angle of attack mechanism and the follower mechanism are respectively installed on the upper and lower sides outside the wind tunnel (1); the driving shaft (8) of the angle of attack mechanism and the follower shaft (13) of the follower mechanism are respectively inserted into the wind tunnel (1), and the axes of the two are coaxial; the first support rod (9) is installed on the driving shaft (8), and the second support rod (12) is installed on the follower shaft (13); the first fixed end (1003) of the balance (10) is connected to the first support rod (9), and the second fixed end (1006) of the balance (10) is connected to the second support rod (12); during the test, the wind tunnel test model (11) is installed on the balance (10).

2. The 180° large angle of attack static and dynamic wind tunnel test force measuring device according to claim 1 is characterized in that: The balance (10) is a "double-measuring-end" integral structure, comprising: a first measuring end (1001), a first measuring element (1002), a first fixed end (1003), a second measuring element (1004), a second measuring end (1005) and a second fixed end (1006); wherein the first fixed end (1003) and the second fixed end (1006) are respectively arranged on the upper and lower sides of the center of the balance, and together constitute the fixed end of the balance; the first measuring end (1001) is connected to the first measuring element (1002) and is arranged on one side of the fixed end; the second measuring end (1005) is connected to the second measuring element (1004) and is symmetrically arranged on the other side of the fixed end.

3. The 180° large angle of attack static and dynamic wind tunnel test force measuring device according to claim 2 is characterized in that: The angle-of-attack mechanism comprises: a driving motor (2), a motor base (3), a reducer (4), a reducer base (5), a first coupling (6), a first bearing seat (7) and a driving shaft (8); wherein the driving motor (2), the reducer (4), the first coupling (6) and the driving shaft (8) are connected in sequence; the driving motor (2) is mounted on the motor base (3); the reducer (4) is mounted on the reducer base (5); and the driving shaft (8) is mounted on the first bearing seat (7) via two sets of bearings.

4. The 180° large angle of attack static and dynamic wind tunnel test force measuring device according to claim 3 is characterized in that: The follower mechanism comprises: a follower shaft (13), a second bearing seat (14), a second coupling (15), an encoder seat (16) and an angle of attack encoder (17); wherein the follower shaft (13), the second coupling (15) and the angle of attack encoder (17) are connected in sequence; the follower shaft (13) is mounted on the second bearing seat (14) through two sets of bearings; and the angle of attack encoder (17) is mounted on the encoder seat (16).

5. The 180° large angle of attack static and dynamic wind tunnel test force measuring device according to claim 2 is characterized in that: A wind tunnel test model (11) comprises: a model head (1101), a first model middle section (1102), a second model middle section (1103) and a model tail section (1104); wherein the model head (1101) is mounted on the first model middle section (1102), and together they constitute a model front section; the model tail section (1104) is mounted on the second model middle section (1103), and together they constitute a model rear section; the first model middle section (1102) is mounted on a first measuring end (1001) of a balance (10); and the second model middle section (1103) is mounted on a second measuring end (1005) of the balance (10).

6. The 180° large attack angle static and dynamic wind tunnel test force measuring device according to claim 3 is characterized in that: During the test, by inputting different motion control instructions to the drive motor (2), the wind tunnel test model (11) can be subjected to static force measurement tests and large-scale oscillation dynamic force measurement test simulations with an attack angle range of 0° to 180° around the axis of the drive shaft (8) in a horizontal plane in the wind tunnel (1).

7. The 180° large angle of attack static and dynamic wind tunnel test force measuring device according to claim 4 is characterized in that: The axis of the angle of attack encoder (17) is coaxial with the axis of the drive shaft (8) and is used to measure the angle of attack of the wind tunnel test model (11).

8. The 180° large angle of attack static and dynamic wind tunnel test force measuring device according to claim 2 is characterized in that: The balance (10) realizes dual six-component measurement based on a first measuring element (1002) and a second measuring element (1004); wherein the first measuring element (1002) is used to measure the six-component aerodynamic force of the front section of the model; and the second measuring element (1004) is used to measure the six-component aerodynamic force of the rear section of the model; and the aerodynamic force of the wind tunnel test model (11) is obtained by coordinate synthesis from the six-component aerodynamic force of the front section of the model and the six-component aerodynamic force of the rear section of the model.

9. The 180° large angle of attack static and dynamic wind tunnel test force measuring device according to claim 5, characterized in that: Semicircular holes are respectively opened on the middle section (1102) of the first model and the middle section (1103) of the second model. After the middle section (1102) of the first model and the middle section (1103) of the second model are butt-jointed and installed, a complete circular hole is formed; the first fixed end (1003) and the second fixed end (1006) pass through the upper and lower parts of the circular hole respectively; the gap t between the outer wall surface of the fixed end and the inner wall surface of the circular hole is ≥2mm, so as to ensure that the fixed end does not touch the circular hole.

10. The 180° large angle of attack static and dynamic wind tunnel test force measuring device according to claim 9, characterized in that: The first model middle section (1102) and the second model middle section (1103) form a maze structure (1105) at the joint position, and the single-side gap h is ≥ 2mm.

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