Fixed adjustment device suitable for self-coupling jet wind tunnel test and application method

Abstract

The present invention discloses a fixing and adjusting device and an application method suitable for self-coupling jet wind tunnel test, which relates to the field of wind tunnel test, including: a main support for fixing the test model on a mounting platform; an auxiliary support arranged on the main support for limiting the jet mechanism; wherein a support flange group and a transverse flange group are respectively arranged at the positions where the main support and the auxiliary support match; the support flange group and the transverse flange group are respectively provided with orthogonal U-shaped grooves, and the adjusting mechanism arranged between the support flange and the transverse flange is provided with a mounting hole matched with the U-shaped groove. The present invention provides a fixing and adjusting device and an application method suitable for self-coupling jet wind tunnel test, which has a simple structure, is easy to manufacture, has a clear principle, and has a good effect. It has strong applicability to aviation and aerospace in the field of self-coupling jet wind tunnel test, and the overall manufacturing cost is very low, which has certain economy.

Description

Technical Field

[0001] The present invention relates to the field of wind tunnel testing, and more specifically, to a fixing and adjusting device suitable for self-coupling jet wind tunnel testing and an application method thereof. Background Art

[0002] When conducting self-coupled jet wind tunnel tests for the aviation, aerospace and other industries, the test model and local jet holes are tested under different working conditions at the same time. The local jet holes of the model are of many types and small in diameter. Considering the processing and assembly errors, the jet device needs to be appropriately adjusted according to the test conditions to ensure that the jet device does not contact the local jet holes of the test model. During the test, since both the test model and the jet device are placed in a high-speed test airflow, they will be affected by vibration and surface aerodynamics. The jet device must have a certain strength to ensure that the jet device does not contact the local jet holes of the test model during the test to ensure the test effect. It is necessary to develop and design a fixed adjustment device and application method suitable for self-coupled jet wind tunnel tests, which not only fixes and supports the model and the jet device at the same time, but also has good strength, stiffness, corrosion resistance and other characteristics, and has an adjustment function, and can adjust the jet device with multiple degrees of freedom to meet the test requirements.

[0003] In similar domestic wind tunnel equipment, different fixed adjustment devices are generally designed for different self-coupling jet wind tunnel tests, which not only increases the development cost, but also has poor consistency. Especially when facing complex support structures, fixed adjustment devices require complex design and high-cost manufacturing, which not only increases the R&D cost, but also makes it difficult to promote in practical applications. In particular, when supporting and adjusting the jet device, a special local support device needs to be designed, and its strength and rigidity cannot be guaranteed, and there is no corresponding adjustment function; if there is an adjustment function, it can only be adjusted in a single degree of freedom, and cannot be adjusted in multiple degrees of freedom; when it is impossible to continue to support due to different directions, the device needs to be disassembled and the support direction needs to be changed for support. This method is not only time-consuming and labor-intensive, but also has poor practicality. There are also limitations in accuracy and stability, and the adjustment effect is not ideal. Summary of the invention

[0004] An object of the present invention is to solve at least the above problems and / or disadvantages and to provide at least the advantages which will be described hereinafter.

[0005] In order to achieve these purposes and other advantages of the present invention, a fixed adjustment device and an application method suitable for a self-coupled jet wind tunnel test are provided, comprising:

[0006] Main support for fixing the test model to the mounting platform;

[0007] An auxiliary support provided on the main support and used to define the jet mechanism;

[0008] Wherein, a support flange group and a transverse flange group are respectively arranged at the positions where the main support and the auxiliary support cooperate with each other;

[0009] The supporting flange group and the transverse flange group are respectively provided with orthogonal U-shaped grooves.

[0010] Preferably, the supporting flange set comprises:

[0011] Support flange I that matches the free end of the auxiliary support;

[0012] A supporting flange II provided on the auxiliary supporting side wall;

[0013] The transverse flange group includes: transverse flange I matched with supporting flange I, and transverse flange II matched with supporting flange II;

[0014] Among them, the U-shaped grooves on the supporting flange I and the transverse flange I are arranged in multiple numbers on the periphery of the flange end surface, and the U-shaped grooves on the supporting flange II and the transverse flange II are arranged at the center of the flange end surface.

[0015] Preferably, the main support comprises:

[0016] Connecting rods that match the test model;

[0017] A main support rod which is integrated with the connecting rod by a wedge key;

[0018] An L-shaped connector provided on the main support rod to provide a support flange I mounting position;

[0019] Wherein, the support flange II is arranged on the side wall of the support rod;

[0020] The auxiliary support comprises:

[0021] An auxiliary support rod is provided for providing a transverse flange assembly installation position and transmitting the force of the jet mechanism to the main support rod;

[0022] A fixing seat is arranged at one end of the auxiliary support rod to provide a mounting position for the jet mechanism.

[0023] Preferably, it also includes:

[0024] An adjustment mechanism I disposed between the supporting flange I and the transverse flange I;

[0025] An adjusting mechanism II is arranged between the supporting flange II and the transverse flange II.

[0026] Preferably, the adjustment mechanism I is configured to adopt a gasket I, and the gasket I is provided with a fixing hole I that matches the position of the U-shaped groove.

[0027] Preferably, the adjustment mechanism II is configured to include: a plurality of pads and gaskets II with different thicknesses, and the pads and gaskets II are provided with fixing holes II that match the positions of the U-shaped grooves.

[0028] An application method is applied to a fixed adjustment device of a self-coupling jet wind tunnel test, comprising:

[0029] S1. Connect the connecting rod and the main support rod in the main support device by means of a wedge key;

[0030] S2, fixedly connecting the free end of the support rod to the mounting platform, and the free end of the connecting rod to the test model;

[0031] S3, connecting the auxiliary support rod with the main support rod through the installation mechanism matched with the support flange group and the transverse flange group;

[0032] The spatial position of the auxiliary support rod can be fine-tuned up and down, left and right, and front and back through the adjustment mechanism I and the adjustment mechanism II.

[0033] Preferably, the method further comprises: verifying the reliability of the fixed adjustment device in a high-speed wind tunnel test environment through numerical simulation and theoretical analysis.

[0034] Preferably, the verification method includes:

[0035] The jet flow rates of different attack angles and different jet mechanisms are numerically simulated at a predetermined Mach number when the aircraft is in flight, so as to calculate the pressure load on the aircraft surface;

[0036] A strength analysis of the fixed adjusting device is carried out based on the calculated pressure load to verify the reliability of the fixed adjusting device.

[0037] The present invention includes at least the following beneficial effects: the fixed adjustment device of the present invention has a simple structure, is easy to manufacture, has a clear principle, and has a good effect. It has strong applicability in the field of self-coupled jet wind tunnel tests in aviation and aerospace, and the overall manufacturing cost is very low, and it has certain economy.

[0038] Other advantages, objectives and features of the present invention will be embodied in part through the following description, and in part will be understood by those skilled in the art through study and practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 It is a structural schematic diagram of the fixing and adjusting device of the present invention;

[0040] Figure 2 It is a structural schematic diagram of the main support of the present invention;

[0041] Figure 3 It is a structural schematic diagram of the auxiliary support of the present invention;

[0042] Figure 4 It is a structural schematic diagram of the regulating mechanism I of the present invention;

[0043] Figure 5 It is a structural schematic diagram of gasket II in the adjustment mechanism II of the present invention;

[0044] Figure 6 It is a structural schematic diagram of the cushion block in the adjustment mechanism II of the present invention;

[0045] Figure 7 It is the stress cloud diagram under working condition 1 of the present invention;

[0046] Figure 8 It is the stress cloud diagram under working condition 2 of the present invention;

[0047] Fig. 9 It is the stress cloud diagram under working condition 3 of the present invention;

[0048] Fig.10 It is the stress cloud diagram under working condition 4 of the present invention;

[0049] Fig.11 It is the stress cloud diagram under working condition 5 of the present invention;

[0050] Fig.12 It is the stress cloud diagram under working condition 6 of the present invention;

[0051] Fig.13 It is the stress cloud diagram under working condition 7 of the present invention;

[0052] Fig.14 It is the stress cloud diagram under working condition 8 of the present invention;

[0053] Fig.15 It is the stress cloud diagram under working condition 9 of the present invention;

[0054] Fig.16 It is the stress cloud diagram under working condition 10 of the present invention;

[0055] Fig.17 It is the stress cloud diagram under the working condition 11 of the present invention;

[0056] Fig.18 It is the stress cloud diagram under working condition 12 of the present invention;

[0057] Among them, main support-1, auxiliary support-2, connecting rod 3, main support rod 4, wedge key 5, support flange group 6, support flange I60, support flange II61, auxiliary support rod 7, transverse flange group 8, transverse flange I80, transverse flange II81, gasket 9, gasket II10, fixing hole II101, test model 11, jet mechanism 12, adjustment mechanism I13, fixing hole I130, adjustment mechanism II-14. DETAILED DESCRIPTION

[0058] The present invention is further described in detail below in conjunction with the accompanying drawings so that those skilled in the art can implement the invention with reference to the description.

[0059] like Figure 1 As shown, the fixed adjustment device and application method suitable for self-coupling jet wind tunnel test mainly include main support 1, auxiliary support 2 and adjustment mechanism II 14. In actual application, the fixed adjustment device of the present invention can support and adjust the test model as a whole and the jet mechanism according to the needs of different fields, and has the characteristics of good consistency, high strength, convenient adjustment, high reliability, low cost, etc. During use, according to the specific parameter requirements such as the internal space, external dimensions, application scenarios, and actual needs of the test model, the above parts can be appropriately optimized to achieve the actual effect, which can reduce the device R&D and maintenance costs and improve the operability of the device.

[0060] Among them, the main support 1 structure is as follows Figure 2 As shown, it mainly includes a connecting rod 3, a main support rod 4, a wedge key 5 and a support flange group 6 (the support flange group 6 includes: a support flange Ⅰ60 matched with the free end of the auxiliary support; a support flange Ⅱ61 arranged on the side wall of the auxiliary support). In the preparation stage, the connecting rod 3 and the main support rod 4 in the main support 1 are first fixed with a wedge key 5. When the other end of the main support rod 4 is fixedly connected to the installation platform, one end of the connecting rod 3 is fixedly connected to the test model 11 with nuts and washers. Different connection methods can be designed according to different use fields and application scenarios, such as flange connection or external thread connection. Finally, the main support rod 4 is fixedly connected to the support flange group 6. The connection methods are divided into welding, pin connection and integrated processing. The connection method can be confirmed according to actual needs, material selection and surface treatment. In this scheme, in order to ensure the overall connection strength, integrated processing is adopted.

[0061] The auxiliary support 2 structure is as follows Figure 4As shown, it mainly includes an auxiliary support rod 7 and a transverse flange group 8, (the transverse flange group includes: a transverse flange I80 matched with the support flange I60, and a transverse flange II81 matched with the support flange II61, and the U-shaped grooves on the support flange I60 and the transverse flange I80 are arranged in a plurality of positions on the periphery of the flange end surface, and the U-shaped grooves on the support flange II61 and the transverse flange II81 are arranged in the center of the flange end surface). Among them, the transverse flange group 8 in the auxiliary support 2 and the support flange group 6 in the main support 1 are connected by orthogonal U-shaped grooves and bolts, and the auxiliary support can be adjusted up and down, left and right, and front and back according to actual needs, and the fixed position can be adjusted to achieve the use effect. The auxiliary support rod 7 and the transverse flange group 8 in the auxiliary support 2 are connected in the same way as the main support rod 4 and the support flange group 6 in the main support 1, which are welding, pin connection and integrated processing. The connection method can be determined according to actual needs, material selection and surface treatment. The other end of the auxiliary support rod 7 can be connected and fixed with a thread or flange surface. The jet mechanism 12. In this solution, the auxiliary support rod 7 and the transverse flange group 8 are connected in an integrated manner; the other end of the auxiliary support rod 7 is connected to the jet mechanism 12 by a flange surface, both of which are to ensure the connection strength and ensure that the jet mechanism 12 does not contact the local jet hole of the test model 11 when subjected to vibration and surface aerodynamic force.

[0062] The structure of the regulating mechanism Ⅰ13 is as follows Figure 4 As shown, its periphery has a plurality of fixing holes Ⅰ130 that match with the supporting flange Ⅰ60 and the transverse flange Ⅰ;

[0063] The structure of regulating mechanism II14 is as follows Figure 5-Figure 6 As shown, it is composed of a pad 9 and a gasket II 10 for adjustment. The pad 9 and the gasket II 10 are provided with a fixing hole II 101 that matches the support flange II 61 and the transverse flange II 81. The thickness of the pad 9 and each gasket is designed and processed in an incremental manner. According to actual needs, the auxiliary support can be further fine-tuned up and down, left and right, and front and back positions to further achieve the use effect. The purpose of fine-tuning in this scheme is to prevent the jet mechanism 12 from contacting the local jet hole of the test model 11, thereby affecting the test results.

[0064] Working principle: This scheme is based on the main support to support and adjust the auxiliary support with multiple degrees of freedom. The adjustment method is to use the orthogonal U-shaped grooves 13 on the support flange group and the transverse flange group, as well as the pads and gaskets with gradually increasing thickness to adjust the auxiliary support up and down, left and right, and front and back positions, adjust the direction and support position, ensure the use effect and then achieve the use effect. At the same time, all parts in the fixed adjustment device are made of high-strength and fatigue-resistant alloy steel and stainless steel, and are subjected to heat treatment and surface hardening treatment, such as quenching, tempering, carburizing, chrome plating, etc., to improve the hardness, toughness, wear resistance and corrosion resistance of the surface, thereby improving the strength and rigidity of the entire device and ensuring the reliability of the fixed adjustment device.

[0065] Example 1

[0066] The fixed adjustment device is applied to the high-speed self-coupled jet wind tunnel test to meet the needs of aviation and aerospace in the self-coupled jet wind tunnel test. The application method mainly includes the following steps:

[0067] In the preparation stage, first, the connecting rod and the support rod in the main support are connected with a wedge key, the other end of the support rod is fixedly connected to the mounting platform, and the other end of the connecting rod is fixedly connected to the test model with nuts and gaskets. Different connection methods can be designed according to different use fields and application scenarios, such as flange connection or external thread connection;

[0068] Then, the support rod is fixedly connected to the supporting flange. The connection methods are divided into welding, pin connection and integrated processing. The connection method is determined according to actual needs, material selection and surface treatment.

[0069] Furthermore, the support flange in the main support and the transverse flange in the auxiliary support are fixedly connected by bolts and nuts, wherein the support flange group and the transverse flange group are connected by orthogonal U-shaped grooves and bolts, so that the auxiliary support can be adjusted up and down, left and right, and front and back according to actual needs.

[0070] Finally, the auxiliary support is fine-tuned up and down, left and right, and front and back through the pads and adjustment gaskets in the adjustment device. The pads and adjustment gaskets are used in conjunction with the support flange in the main support and the transverse flange in the auxiliary support. The thickness of the pads and adjustment gaskets are designed and processed in a gradually increasing manner, and can be used in combination according to actual needs. Both adjustment methods perform multi-degree-of-freedom adjustment on the auxiliary support to ensure that the jet mechanism does not contact the local jet hole of the test model, thereby achieving the best test effect.

[0071] Example 2

[0072] The reliability of the fixed adjustment device in the high-speed wind tunnel test environment is verified through numerical simulation and theoretical analysis. With Mach number 12 as the flight state, a certain aircraft is numerically simulated at different angles of attack and different jet flow rates of the jet mechanism, and the pressure load on the aircraft surface is calculated (such as the pressure load on the aircraft under different working conditions shown in Table 1). The strength analysis of the fixed adjustment device is carried out according to the pressure load, and finally the reliability of the device is verified based on the calculation results.

[0073] Table 1

[0074]

[0075] Through numerical simulation, it is found that the pressure load on the outer surface of the aircraft is mainly axial force.F x and normal force F y , the strength analysis of the fixed adjustment device is carried out according to the pressure load on the aircraft. The strength conditions are: , is the maximum stress value of the simulation, is the allowable stress, is the yield limit, S is the safety factor, which is 2. The parts of the fixed adjustment device in the implementation process are all made of high-strength and fatigue-resistant alloy quenched and tempered steel 30CrMnSiA, whose material properties are shown in Table 2, and the stress cloud diagram of the fixed adjustment device under different working conditions is shown in Table 3 (it should be noted that Figure 7-Figure 18 A: Static Structural Equivalent in the English part in the upper left corner is the equivalent stress in the static structure; Stress Type: Equivalent (von-Mises) means the stress type is equivalent (von-Mises) stress; Stress Unit: Mpa, Time: 1 means the stress unit is MPa).

[0076] Table 2

[0077]

[0078] Table 3

[0079]

[0080] Through strength analysis, it is found that the maximum stress points of the fixed adjustment device under different working conditions are all at the transverse flange, and are all smaller than the allowable stress of the material, and the strength meets the use requirements.

[0081] The above numerical simulation and theoretical analysis verify that the fixed adjustment device has high reliability in the high-speed wind tunnel test environment.

[0082] The above solution is only an illustration of a preferred embodiment, but is not limited thereto. When implementing the present invention, appropriate replacement and / or modification can be performed according to user needs.

[0083] Although the embodiments of the present invention have been disclosed above, they are not limited to the applications listed in the specification and the embodiments. It can be fully applied to various fields suitable for the present invention. For those familiar with the art, additional modifications can be easily realized. Therefore, without departing from the general concept defined by the claims and equivalent scope, the present invention is not limited to the specific details and the illustrations shown and described here.

Claims

1. A fixed adjustment device suitable for self-coupling jet wind tunnel test, characterized in that: include: Main support for fixing the test model to the mounting platform; An auxiliary support provided on the main support and used to define the jet mechanism; Wherein, a support flange group and a transverse flange group are respectively arranged at the positions where the main support and the auxiliary support cooperate with each other; The supporting flange group and the transverse flange group are respectively provided with orthogonal U-shaped grooves; The supporting flange assembly comprises: Support flange I that matches the free end of the auxiliary support; A supporting flange II provided on the auxiliary supporting side wall; The transverse flange group includes: transverse flange I matched with supporting flange I, and transverse flange II matched with supporting flange II; The U-shaped grooves on the supporting flange I and the transverse flange I are arranged in a plurality on the periphery of the flange end surface, and the U-shaped grooves on the supporting flange II and the transverse flange II are arranged at the center of the flange end surface; Also includes: An adjustment mechanism I disposed between the supporting flange I and the transverse flange I; An adjustment mechanism II is arranged between the supporting flange II and the transverse flange II; The adjustment mechanism I is configured to use a gasket I, and the gasket I is provided with a fixing hole I that matches the position of the U-shaped groove; The adjustment mechanism II is configured to include: a plurality of pads and gaskets II with different thicknesses, and the pads and gaskets II are provided with fixing holes II that match the positions of the U-shaped grooves.

2. The fixing and adjusting device for self-coupling jet wind tunnel test according to claim 1, characterized in that: The main support comprises: Connecting rods that match the test model; A main support rod which is integrated with the connecting rod by a wedge key; An L-shaped connector provided on the main support rod to provide a support flange I mounting position; Wherein, the support flange II is arranged on the side wall of the support rod; The auxiliary support comprises: An auxiliary support rod is provided for providing a transverse flange assembly installation position and transmitting the force of the jet mechanism to the main support rod; A fixing seat is arranged at one end of the auxiliary support rod to provide a mounting position for the jet mechanism.

3. An application method, applied to the fixed adjustment device of the self-coupled jet wind tunnel test according to any one of claims 1-2, characterized in that: include: S1. Connect the connecting rod and the main support rod in the main support device by means of a wedge key; S2, fixedly connecting the free end of the support rod to the mounting platform, and the free end of the connecting rod to the test model; S3, connecting the auxiliary support rod with the main support rod through the installation mechanism matched with the support flange group and the transverse flange group; The spatial position of the auxiliary support rod can be fine-tuned up and down, left and right, and front and back through the adjustment mechanism I and the adjustment mechanism II.

4. The application method according to claim 3, characterized in that: Also includes: The reliability of the fixed adjustment device in the high-speed wind tunnel test environment is verified through numerical simulation and theoretical analysis.

5. The application method according to claim 4, characterized in that: The verification methods include: The jet flow rates of different attack angles and different jet mechanisms are numerically simulated at a predetermined Mach number when the aircraft is in flight, so as to calculate the pressure load on the aircraft surface; A strength analysis of the fixed adjusting device is carried out based on the calculated pressure load to verify the reliability of the fixed adjusting device.

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