A wind tunnel test rudder deflection mounting structure for a small missile model

Abstract

The application discloses a wind tunnel test rudder deflection mounting structure of a small missile model, which comprises a missile model, which is in a cylindrical thin-wall structure, a supporting rod is fixedly arranged in the missile model, a gap is reserved between the supporting rod and the inner wall of the missile model, a plurality of test rudders are mounted on the outer surface of the missile model, a plurality of mounting grooves are formed in the missile model at positions corresponding to the mounting positions of the test rudders, the lower end of each test rudder is provided with a mounting piece matched with the mounting groove, and the mounting piece can be detachably mounted in the mounting groove; and a pressing ring is detachably mounted at the end of the missile model, and the pressing ring tightly fixes the mounting piece on the surface of the missile model. The test rudder is embedded and mounted in the mounting groove formed in the missile model, so that the mounting and replacement of the test rudder on the small trajectory model are solved, and the test rudder is stably mounted and is simple to disassemble and assemble.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of wind tunnel test, more particularly, the present application relates to a wind tunnel test rudder surface deflection mounting structure of a micro missile model. BACKGROUND

[0002] For the micro missile model used in the wind tunnel test, the micro trajectory test model used is a cylindrical thin-walled structure. In order to fix the micro missile test model, a support rod needs to be inserted into the inside of the micro missile model, and one end of the support rod needs to be fixed with the micro missile model, and the other end needs to keep a certain gap with the support rod. Because the size of the micro missile is very small and the slenderness ratio (i.e. the ratio of the length to the diameter of the micro missile) is very large, and the inner diameter of the micro missile is very small, in order to prevent the support rod from colliding with the micro missile test model during the test, a gap must be left between the support rod and the inner wall of the micro missile model. At the same time, the test rudder needs to be designed to be replaceable due to the need for rudder angle change, so the installation position and installation method of the test rudder need to be relatively designed. The test rudder needs to be installed on the micro missile model for wind tunnel test, and because the support rod and the micro missile model are small size structures, the installation requirements of the test rudder are relatively harsh, and the test rudder needs to be replaced according to different test requirements, so the installation and dismounting of the test rudder and the micro missile model should be convenient. In order to install the test rudder on the surface of the micro missile model, the existing test rudder mounting method needs to be redesigned. SUMMARY

[0003] An object of the present application is to solve at least the above problems and / or deficiencies, and to provide at least the advantages described later.

[0004] In order to achieve these objects and other advantages according to the present application, a wind tunnel test rudder surface mounting structure of a micro missile model is provided, which includes a missile model in a cylindrical thin-walled structure, a support rod is fixedly inserted into the inside of the missile model, a gap is left between the support rod and the inner wall of the missile model, a plurality of test rudders are installed on the outer surface of the missile model, a plurality of installation grooves are provided on the missile model at the installation positions of the test rudders, the lower end of the test rudder is provided with an installation piece matched with the installation groove, and the installation piece is detachably installed in the installation groove; a compression ring is detachably installed at the end of the missile model, and the compression ring compresses and fixes the installation piece on the surface of the missile model.

[0005] Preferably, the structure of the test rudder includes:

[0006] a rudder surface, the installation piece is fixedly arranged at the lower end of the rudder surface;

[0007] The front end of the mounting sheet is integrally formed with a front end insert sheet, the rear end of the mounting sheet is integrally formed with a rear end insert sheet, the mounting groove is provided with an insert groove matched with the front end insert sheet, and the compression ring is provided with a compression groove matched with the rear end insert sheet; the front end insert sheet is embedded into the insert groove, the rear end insert sheet is compressed in the compression groove, and the thickness of the front end insert sheet and the rear end insert sheet is 0.4mm.

[0008] Preferably, the thickness of the compression ring is 0.6mm, and the detachable mounting mode of the compression ring and the missile model is screw connection.

[0009] Preferably, the mounting sheet, the front end insert sheet and the rear end insert sheet are all sheet-shaped structures with the same bending radius, and the bending radius is the same as the bending radius of the mounting groove, the insert groove and the compression groove.

[0010] Preferably, the outer surface of the mounting sheet is flush with the outer surface of the missile model.

[0011] The present application at least has the following beneficial effects: the present application solves the problem of split design and installation of the test rudder on the micro missile model by embedding the test rudder into the mounting groove of the missile model and compressing and fixing the mounting sheet of the test rudder with the compression ring, and the test rudder is stable in installation and simple in disassembly and replacement.

[0012] The present application solves the design problem of the large slenderness ratio micro missile tail support force measuring model rudder surface deflection, realizes the replaceable deflection rudder surface design, and the test rudder deflection angle is accurate and the disassembly and assembly are convenient.

[0013] Other advantages, objects and features of the present application will be apparent to those skilled in the art from the following description, and will be understood to be within the scope of the present application. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 The present application provides a schematic view of the wind tunnel test rudder surface deflection installation structure of the micro missile model;

[0015] Figure 2 The present application provides a sectional structure schematic view of the mounting sheet, the mounting groove and the compression ring;

[0016] Figure 3 The present application provides a structure schematic view of the test rudder;

[0017] Figure 4 The present application provides a structure schematic view of the compression ring. DETAILED DESCRIPTION

[0018] The present application will be further described in detail below with reference to the accompanying drawings, so that those skilled in the art can implement the present application according to the description.

[0019] It should be understood that terms such as “having,” “comprising,” and “including” as used herein do not exclude the presence or addition of one or more other elements or combinations thereof.

[0020] It should be noted that in the description of this invention, the orientations or positional relationships indicated by terms are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing this invention and simplifying the description. They do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting this invention. In addition, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0021] In the description of this invention, unless otherwise explicitly specified and limited, the terms "installed", "equipped", "sleeved / connected", "connected", etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0022] Furthermore, in this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Moreover, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0023] like Figures 1-4 As shown: A wind tunnel test control surface mounting structure for a miniature missile model according to the present invention includes: a missile model 1, which is a cylindrical thin-walled structure; a support rod 2 is fixedly inserted inside the missile model 1, and a gap is reserved between the support rod 2 and the inner wall of the missile model 1; four test control surfaces 3 are mounted on the outer surface of the missile model 1; mounting grooves 4 are opened on the missile model 1 at the mounting positions corresponding to the test control surfaces 3; mounting pieces 5 adapted to the mounting grooves 4 are provided at the lower end of the test control surfaces 3, and the mounting pieces 5 are detachably mounted in the mounting grooves 4; a clamping ring 6 is detachably mounted at the end of the missile model 1, and the clamping ring 6 clamps and fixes the mounting pieces 5 to the surface of the missile model 1.

[0024] Working principle: the present application is through the surface of the cylindrical thin wall structure's missile model 1 sets up installation groove 4, and installation groove 4 is set close to the edge of missile model 1, then the installation piece 5 is embedded and installed to installation groove 4, and the other end of installation piece 5 is pressed and fixed with the compression ring 6, so that the technical problem of installing test rudder 3 on the surface of the missile model 1 of small size structure is solved.This installation structure will not cause the collision between the strut 2 and the missile model 1, will not affect the aerodynamic shape of the missile model 1, and the test rudder 3 is simple to disassemble and replace, and the installation is stable and reliable. Figure 1 As shown in the figure, four installation grooves 4 with equal interval are set on the missile model 1 for installing four test rudders 3 respectively, and only the installation of one test rudder 3 is shown in the figure for simplifying the description.The strut 2 is used to penetrate into the missile model 1 and fix the missile model 1 at the corresponding position in the wind tunnel.

[0025] In the above technical solution, the structure of the test rudder 3 comprises:

[0026] The installation piece 5 is fixedly arranged at the lower end of the rudder surface;

[0027] The front end of the installation piece 5 is integrally formed with a front end insert 51, the rear end of the installation piece 5 is integrally formed with a rear end insert 52, the installation groove 4 is provided with an insert groove 41 matched with the front end insert 51, and the compression ring 6 is provided with a compression groove 61 matched with the rear end insert 52; the front end insert 51 is embedded into the insert groove 41, and the rear end insert 52 is compressed in the compression groove 61.This way of inserting the front end insert 51 into the insert groove 41, and compressing the rear end insert 52 into the compression groove 61 while the compression ring 6 compresses the installation piece 5, realizes the compression and fixation of both ends of the installation piece 5, and improves the stability of the installation of the test rudder 3.

[0028] In the above technical solution, the detachable installation mode of the compression ring 6 and the missile model 1 is screw connection.This installation mode of the compression ring 6 is simple to disassemble and has high installation stability, and is more convenient for disassembling and replacing the test rudder 3; when the compression ring 6 is completely tightened, the compression groove 61 formed in the inner side of the compression ring 6 can just compress the rear end insert 52 of the installation piece 5.

[0029] In the above technical solution, the installation piece 5, the front end insert 51 and the rear end insert 52 are all sheet-shaped structures with the same bending radius, and the bending radius is the same as that of the installation groove 4, the insert groove 41 and the compression groove 61.This setting mode makes the installation of the installation piece 5 and the installation groove 4 more closely, and ensures that there is no gap between the installation piece 5 and the installation groove 4.

[0030] In the above technical solution, the outer surface of the mounting sheet 5 is flush with the outer surface of the missile model 1, and this arrangement makes the mounting sheet 5 consistent with the outer shape of the missile model 1, effectively avoiding the influence of the mounting sheet 5 on the aerodynamic shape of the missile model.

[0031] The number of devices and the scale of processing illustrated herein are intended to simplify the description of the present application. Applications, modifications and variations of the present application, which are apparent to persons skilled in the art, are to be considered within the scope of the present application.

[0032] Although embodiments of the present application have been disclosed in connection with the specified embodiments, it should be understood that they can be applied in various fields of the application, and additional modifications can be easily made by those skilled in the art, and therefore the present application is not limited to the specific details and examples shown and described herein, but only to the general concept defined by the claims and their equivalents.

Claims

1. A rudder deflection mounting structure for a wind tunnel test of a small missile model, comprising a missile model in a cylindrical thin-walled structure, a support rod being fixedly inserted into the inside of the missile model, and a gap being provided between the support rod and the inner wall of the missile model, characterized in that, The missile model is provided with a plurality of test rudders, a plurality of installation grooves are formed on the missile model at positions corresponding to the installation positions of the test rudders, the lower ends of the test rudders are provided with installation pieces matched with the installation grooves, and the installation pieces are detachably installed in the installation grooves; and the end of the missile model is detachably provided with a compression ring, which compressively fixes the installation pieces on the surface of the missile model. The test rudder comprises: a rudder surface, and the installation piece is fixedly arranged at the lower end of the rudder surface; the front end of the installation piece is integrally provided with a front end insert piece, the rear end of the installation piece is integrally provided with a rear end insert piece, the installation groove is provided with an insert groove matched with the front end insert piece, and the compression ring is provided with a compression groove matched with the rear end insert piece; the front end insert piece is embedded into the insert groove, and the rear end insert piece is compressed in the compression groove.

2. The rudder deflection mounting structure for a wind tunnel test of a small missile model according to claim 1, wherein The detachable installation mode of the compression ring and the missile model is screw connection.

3. The rudder deflection mounting structure for a wind tunnel test of a small missile model according to claim 1, wherein The installation piece, the front end insert piece and the rear end insert piece are all sheet structures with the same bending radius, and the bending radius is the same as that of the installation groove, the insert groove and the compression groove.

4. The rudder deflection mounting structure for a wind tunnel test of a small missile model according to Claim 1, wherein The outer surface of the installation piece is flush with the outer surface of the missile model.

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