Variable deflection structure of thin-wall model in wind tunnel test

Abstract

The utility model discloses a kind of variable rudder deflection structures of wind tunnel test thin-walled model, comprising: missile body, rudder base and rudder surface;Rudder surface is installed on missile body by rudder base;Missile body includes: main body and tail, main body is connected with tail, and support rib is set on main body;Tail is the annular structure of integrated molding, recess is equipped in inside, recess is connected with main body and is axially locked by compression nail solid connection;Rudder base is the ladder-shaped plate structure, and the front end upper portion of rudder base is equipped with the front positioning slot matched with main body, and the rear end upper portion is equipped with the rear positioning slot matched with tail, and the middle lower portion is equipped with the limiting slot matched with the support rib on main body;Rudder base is also equipped with the rudder surface insertion slot matched with rudder surface, and rudder surface root is inserted into rudder surface insertion slot, and overall rudder deflection structure is formed by welding. Through the variable rudder deflection structure described in the utility model, the defects such as screw connection destroying thin-walled model integrity, angle pin adjustment relying on wall thickness, multi-component replacement inefficiency and the like existing in the variable rudder deflection structure of existing wind tunnel test are solved.

Description

Technical Field

[0001] This utility model relates to the field of wind tunnel testing technology for aircraft, and in particular to a variable rudder deflection structure for a thin-walled model used in wind tunnel testing. Background Technology

[0002] Rudder deflection refers to the deflection angle produced when an aircraft rotates horizontally around an axis perpendicular to its fuselage. The aircraft's attitude is adjusted by changing the rudder deflection angle under different flight conditions.

[0003] Wind tunnel testing is the primary means of evaluating rudder deflection performance and obtaining rudder effectiveness parameters. The rudder deflection structure is connected to the aircraft's wind tunnel model body, and flight data at corresponding rudder deflection angles is obtained by changing the rudder deflection structure at different angles. Due to the limitations of wind tunnel size and model support structure, the test model cannot be too large, but its inner diameter cannot be too small. This places certain requirements on the model's wall thickness. However, traditional variable rudder deflection schemes have the following drawbacks in thin-walled models:

[0004] 1. Multi-structure screw-fixed type: Independent rudder base-rudder surface components are machined for different rudder deflection angles and connected to the projectile body by screws. This method results in: 1) Screw installation requires drilling holes in the thin-walled projectile body (wall thickness ≤ 3mm), which can easily lead to structural tearing or fatigue failure; 2) Screw heads protrude or are recessed on the projectile body surface, resulting in discontinuous profiles, disrupting aerodynamic shape, and distorting test data; 3) Each angle change is time-consuming, and all screws need to be removed each time, which is inefficient, and repeated disassembly and assembly can easily damage the screws and projectile body model.

[0005] 2. Angle Pin Adjustment Type: An angled positioning pin is inserted between the rudder base and the missile body to achieve deflection. Although this reduces the number of components, it requires a missile body wall thickness of ≥4mm to ensure the strength of the pin hole, which cannot meet the requirements of lightweight thin-walled missile body models. Utility Model Content

[0006] The technical problem solved by this utility model is to overcome the shortcomings of the prior art and provide a variable rudder deflection structure for thin-walled models in wind tunnel tests. It aims to solve the defects of existing variable rudder deflection structures in wind tunnel tests, such as screw connections damaging the integrity of thin-walled models, angle pin adjustment depending on wall thickness, and low efficiency of replacing multiple components.

[0007] To solve the above-mentioned technical problems, this utility model discloses a variable rudder deflection structure for a thin-walled model in a wind tunnel test, including: a projectile body, a rudder base, and a rudder surface; wherein the rudder surface is mounted on the projectile body through the rudder base.

[0008] In the above-mentioned wind tunnel test thin-walled model variable rudder deflection structure, the projectile body includes: a main body and a tail; wherein, the main body and the tail are connected, and the main body is provided with support ribs.

[0009] In the aforementioned wind tunnel test thin-walled model variable rudder structure, the tail is an integrally formed ring structure with a groove inside; during assembly, the groove engages with the main body and is axially locked by clamping nails.

[0010] In the aforementioned wind tunnel test thin-walled model variable rudder deflection structure, the rudder base has a stepped plate-like structure.

[0011] In the above-mentioned wind tunnel test thin-walled model variable rudder deflection structure, the upper front end of the rudder base is provided with a front positioning groove that cooperates with the main body, the upper rear end is provided with a rear positioning groove that cooperates with the tail, and the lower middle part is provided with a limiting groove that cooperates with the support rib on the main body.

[0012] In the aforementioned wind tunnel test thin-walled model variable rudder deflection structure, the length of the mating section between the front positioning groove and the main body accounts for 1 / 15 to 1 / 10 of the total length of the rudder base; the length of the mating section between the rear positioning groove and the tail accounts for 1 / 15 to 1 / 10 of the total length of the rudder base.

[0013] In the aforementioned wind tunnel test thin-walled model variable rudder deflection structure, the depth of the mating section between the front positioning groove and the main body accounts for 1 / 2 of the total depth of the rudder base; the depth of the mating section between the rear positioning groove and the tail accounts for 1 / 2 of the total depth of the rudder base.

[0014] In the aforementioned wind tunnel test thin-walled model variable rudder deflection structure, the depth of the mating section between the limiting groove and the main body accounts for 1 / 2 of the total depth of the rudder base.

[0015] In the aforementioned wind tunnel test thin-walled model variable rudder deflection structure, a rudder base is provided with a rudder surface slot that mates with the rudder surface; wherein, the root of the rudder surface is inserted into the rudder surface slot, and the integral rudder deflection structure is formed by welding.

[0016] In the aforementioned wind tunnel test thin-walled model variable rudder deflection structure, the rudder surface slot is set according to a preset angle.

[0017] This utility model has the following advantages:

[0018] (1) This utility model discloses a variable rudder deflection structure for a thin-walled model in a wind tunnel test, which eliminates the screw connection between the rudder base and the projectile body, avoids openings in the thin-walled projectile body, and ensures the integrity of the aerodynamic shape by eliminating through holes on the surface of the projectile body.

[0019] (2) This utility model discloses a variable rudder deflection structure for a thin-walled model in a wind tunnel test. The tail end adopts a ring-shaped locking to disperse the clamping force, which reduces the minimum applicable wall thickness of the structure to 2mm and has the advantages of ultra-thin wall compatibility.

[0020] (3) This utility model discloses a variable rudder deflection structure for a thin-walled model in a wind tunnel test. By replacing the rudder deflection angle with a modular rudder base, the replacement time is shortened. There is no need to replace the body or angle pin assembly, avoiding wear of the threaded hole. It has the advantages of efficient disassembly and assembly and low-cost maintenance. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the overall structure of a variable rudder deflection structure for a thin-walled model in a wind tunnel test according to an embodiment of this utility model;

[0022] Figure 2 This is a schematic diagram of the tail section in one embodiment of the present utility model;

[0023] Figure 3 yes Figure 2 Sectional view along axis AA;

[0024] Figure 4 This is a schematic diagram of the structure of a 0-degree rudder base in an embodiment of this utility model;

[0025] Figure 5 yes Figure 4 Sectional view along axis AA;

[0026] Figure 6 This is a schematic diagram of the assembly of a rudder base and a rudder surface in one embodiment of this utility model;

[0027] Figure 7 This is a schematic diagram of another 30-degree rudder base in an embodiment of this utility model. Detailed Implementation

[0028] To make the objectives, technical solutions, and advantages of this utility model clearer, the embodiments disclosed herein will be described in further detail below with reference to the accompanying drawings.

[0029] The core of this invention lies in the following: For thin-walled projectile models, a variable rudder deflection structure for wind tunnel testing is proposed, where the main body and tail form a continuous cavity; the rudder base has a stepped plate-like structure, with a front positioning groove at the upper front end that mates with the main body, a rear positioning groove at the upper rear end that mates with the tail, and a limiting groove at the lower middle part that mates with the main body support; the rudder surface root is inserted into the rudder base slot and then laser-welded, with the weld completely embedded in the rudder base slot and no protrusions on the outer surface; the tail clamping pin uses a countersunk screw, with its mounting surface flush with the outer surface of the projectile; the tail is an integrally formed annular structure with an internal groove, which engages with the main body during assembly and is axially locked by the clamping pin. This invention eliminates surface discontinuities such as screw holes and is applicable to multi-angle rudder base components. Through three-dimensional slot coupling and elastic clamping mechanisms, it systematically solves the defects of existing variable rudder deflection structures for wind tunnel testing, such as screw connections damaging the integrity of thin-walled models, angle pin adjustment depending on wall thickness, and low efficiency in replacing multiple components.

[0030] Reference Figure 1 In this embodiment, the wind tunnel test thin-walled model variable rudder deflection structure includes: a missile body, a rudder base 3, and a rudder surface 4. The rudder surface 4 is mounted on the missile body via the rudder base 3.

[0031] In this embodiment, the projectile body includes a main body 1 and a tail 2; wherein the main body 1 is connected to the tail 2, and the main body 1 is provided with supporting ribs. Figures 2-3 As shown, the tail section 2 is an integrally formed ring structure with a groove inside; during assembly, the groove engages with the main body 1 and is axially locked by clamping nails.

[0032] In this embodiment, the rudder base 3 has a stepped plate-like structure. For example... Figures 4-5 As shown, the upper front end of the rudder base 3 has a front positioning groove 301 that mates with the main body 1, the upper rear end has a rear positioning groove 303 that mates with the tail section 2, and the lower middle part has a limiting groove 304 that mates with the support ribs on the main body 1. The length of the section where the front positioning groove 301 mates with the main body 1 is 1 / 15 to 1 / 10 of the total length of the rudder base 3; the length of the section where the rear positioning groove 303 mates with the tail section 2 is 1 / 15 to 1 / 10 of the total length of the rudder base 3. The depth of the section where the front positioning groove 301 mates with the main body 1 is 1 / 2 of the total depth of the rudder base 3; the depth of the section where the rear positioning groove 303 mates with the tail section 2 is 1 / 2 of the total depth of the rudder base 3. The depth of the section where the limiting groove 304 mates with the main body 1 is 1 / 2 of the total depth of the rudder base 3.

[0033] In this embodiment, as Figure 6 As shown, the rudder base 3 is also provided with a rudder surface slot 302 that mates with the rudder surface 4. The root of the rudder surface 4 is inserted into the rudder surface slot 302, and the two are welded together to form an integral rudder deflection structure. The rudder surface slot 302 is set at a preset angle, which includes, but is not limited to, 0°, ±10°, ±20°, ±30°, etc. Figure 3 and Figure 7 As shown.

[0034] Based on the above embodiments, the following explanation will be based on a thin-walled wind tunnel test model with a diameter of 26 mm and a wall thickness of 2 mm, with a rudder deflection angle adjustment range of ±30°.

[0035] (1) Structural assembly relationship: The main body of the missile body is machined with a stepped mounting port, and a positioning groove A is provided inside; the front positioning groove on the rudder base forms an axial constraint with the positioning groove A, and the limiting groove forms a radial limit with the support rib of the main body of the missile body; the tail of the missile body is an annular part with an inner groove, which forms an interference fit with the main body of the missile body through the groove; the tail of the missile body presses the positioning groove of the rudder base and is axially fixed by a clamping pin.

[0036] (2) Rudder base structure: The rudder base is formed by integral milling of alloy. Key feature dimensions include: front positioning groove: length 3.0mm, thickness 1mm; rear positioning groove: length 5.0mm, thickness 1mm; limiting groove: opening width 25mm, depth 1mm; rudder surface slot: equipped with three sets of polygonal slots of ±10°, ±20° and ±30°, with a slot depth of 2mm and a 0.3mm welding bevel reserved at the bottom of the slot.

[0037] The above description is only the best specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model.

[0038] The contents not described in detail in this utility model specification are common knowledge to those skilled in the art.

Claims

1. A variable rudder deflection structure for a thin-walled model used in wind tunnel testing, characterized in that, include: The missile body, rudder base (3), and rudder surface (4); wherein the rudder surface (4) is mounted on the missile body via the rudder base (3); The projectile body includes: a main body (1) and a tail (2); the main body (1) is connected to the tail (2), and a support rib is provided on the main body (1); The tail (2) is an integrally formed ring structure with a groove inside; during assembly, the groove is engaged with the main body (1) and is axially locked by clamping nails. The upper front end of the rudder base (3) is provided with a front positioning groove (301) that cooperates with the main body (1), the upper rear end is provided with a rear positioning groove (303) that cooperates with the tail (2), and the lower middle part is provided with a limiting groove (304) that cooperates with the support rib on the main body (1); the rudder base (3) is provided with a rudder surface slot (302) that cooperates with the rudder surface (4), and the root of the rudder surface (4) is inserted into the rudder surface slot (302) and welded together to form an overall rudder deflection structure.

2. The variable rudder deflection structure for a thin-walled wind tunnel test model according to claim 1, characterized in that, The rudder base (3) has a stepped plate-like structure.

3. The variable rudder deflection structure for a thin-walled wind tunnel test model according to claim 1, characterized in that, The length of the mating section between the front positioning groove (301) and the main body (1) accounts for 1 / 15 to 1 / 10 of the total length of the rudder base (3); the length of the mating section between the rear positioning groove (303) and the tail (2) accounts for 1 / 15 to 1 / 10 of the total length of the rudder base (3).

4. The variable rudder deflection structure for a thin-walled wind tunnel test model according to claim 1, characterized in that, The depth of the mating section between the front positioning groove (301) and the main body (1) is 1 / 2 of the total depth of the rudder base (3); the depth of the mating section between the rear positioning groove (303) and the tail (2) is 1 / 2 of the total depth of the rudder base (3).

5. The variable rudder deflection structure for a thin-walled wind tunnel test model according to claim 1, characterized in that, The depth of the mating section between the limiting groove (304) and the main body (1) accounts for 1 / 2 of the total depth of the rudder base (3).

6. The variable rudder deflection structure for a thin-walled wind tunnel test model according to claim 1, characterized in that, The rudder slot (302) is set at a preset angle.

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