Wing expansion transformation and angle change device applied to wind tunnel model

Abstract

A test model comprises a head part and a body part which are connected with each other, a rod type balance penetrates through the body part in the axial direction and then is connected with the head part, the rod type balance does not make contact with the body part, the body part is of a barrel-shaped structure, a step is arranged on the outer surface of the circumference of the body part, and the step is connected with the rod type balance through the rod type balance. The step is used for limiting a telescopic wing arranged on the body part, and a first adjusting part capable of changing the axial position and the circumferential angle of the telescopic wing relative to the body part is arranged between the end part of the telescopic wing and the step; the design problem of telescopic transformation and angle transformation of missile type wind tunnel model wings is solved, front wings of different shapes can be replaced, front-back telescopic and angle transformation design is achieved, and disassembly and assembly are convenient and fast.

Description

Technical Field

[0001] This invention relates to the field of wind tunnel testing, and more specifically to a wing extension / extension and angle adjustment device applied to a wind tunnel model. Background Technology

[0002] In high-speed wind tunnel force measurement testing, most projectile models require a support inserted into the model's internal cavity. One end of the force measurement support is fixed to the model, while the other end maintains a certain circumferential gap with the model's internal cavity. The projectile's body is generally a thin-walled cylindrical structure. Considering its strength and stiffness requirements, the wings on the projectile body are usually integrated to achieve the extension, retraction, and angle transformation functions of the canard. This results in multiple models being fabricated for a single test to meet attitude transformation requirements, making it impossible to verify the attitude transformation of different wing shapes. To avoid interference from repeated installations of different models on the test data, and to obtain more realistic data by varying the extension, retraction, and angle transformation of different wing shapes on the same model, a special structural design is needed to achieve the extension, retraction, and angle transformation of the canard on the same model during the test. Summary of the Invention

[0003] The purpose of this invention is to improve the structure of the model based on the current experimental status of the model, so that different airfoil structures can be used to conduct tests at different positions and angles on the missile body during wind tunnel testing, avoiding the drawbacks of aerodynamic interference caused by the scaling and angle changes of multiple models and machining errors.

[0004] To achieve the above objectives, the present invention adopts the following technical solution: A wing extension and angle adjustment device for wind tunnel models is disclosed. The test model includes a head and a body connected to each other. A support rod and a rod-type balance pass through the body along the axial direction and are connected to the head. The support rod does not contact the body. The body is a cylindrical structure with two through ends. A step is provided on the outer circumference of the body. The step is used to limit the extension wing set on the body. The extension wing includes a wing body fitted on the body and a wing set on the wing body. A first adjustment part is provided between the wing body and the step, which can change the axial position and circumferential angle of the extension wing relative to the body. The total thickness of the wing body after contact with the body is not greater than 2 mm.

[0005] In the above technical solution, the first adjustment part serves as an alternative structure, and the axial position of the telescopic wing relative to the body is changed by adjusting the length of the first adjustment part.

[0006] In the above technical solution, a second adjustment part is provided at the other end of the telescopic wing opposite to the position of the first adjustment part, and one end of the second adjustment part is connected to the head.

[0007] In the above technical solution, the second adjustment part is a replacement structure, and the length of the second adjustment part is adjusted by adjusting the length of the first adjustment part.

[0008] In the above technical solution, one end of the first adjusting part is provided with a first groove, and the step is provided with a first protrusion, the first groove matching the first protrusion. The other end of the first adjustment part is provided with a second protrusion, and the end of the wing body is provided with a second groove, the second protrusion matching the second groove.

[0009] In the above technical solution, the end of the wing body is provided with a number of second grooves, and the circumferential angle of the telescopic wing can be changed by different second grooves and second protrusions engaging.

[0010] In the above technical solution, a second protrusion is provided on the first adjustment part, the number of which is the same as the number of the second grooves, and one second protrusion corresponds to one second groove.

[0011] In the above technical solution, the second groove and the second protrusion are evenly distributed along the circumferential direction of the wing body and the step, respectively.

[0012] According to claim 1, the wing telescopic transformation and angle-changing device applied to a wind tunnel model is characterized in that: the telescopic wing and the first adjustment part are both cavity structures that are connected at both ends.

[0013] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are: This invention solves the problems of wing extension and angle transformation under the same model and the installation of various components by using a first adjustment part of different lengths and angles, and by pressing and fixing the second adjustment part, telescopic wing and the first adjustment part with the projectile head and the projectile body. Moreover, the assembly length is adjustable, the connection is tight, and it is simple to disassemble and replace telescopic wings of different shapes.

[0014] This invention solves the design problem of telescopic and angle transformation of the wings of a ballistic wind tunnel model, realizing the design of interchangeable front wings with different shapes that can be telescopically and angled, and is easy to assemble and disassemble. Attached Figure Description

[0015] The present invention will be described by way of example and with reference to the accompanying drawings, wherein: Figure 1 This is a schematic cross-sectional view of the overall structure of the present invention; Figure 2 This is a schematic diagram of the model's external structure; Figure 3 This is a schematic diagram of the retractable wing structure; Figure 4 This is a schematic diagram of the model's body structure; Figure 5This is a schematic diagram of the structure of the first adjustment section; Wherein: 1 is the head, 2 is the body, 21 is the first protrusion, 3 is the telescopic wing, 31 is the second groove, 4 is the support rod, 5 is the first adjustment part, 51 is the second protrusion, 52 is the first groove, and 6 is the second adjustment part. Detailed Implementation

[0016] All features disclosed in this specification, or all steps in all disclosed methods or processes, may be combined in any way, except for mutually exclusive features and / or steps.

[0017] Any feature disclosed in this specification (including any appended claims, abstract, and drawings) may be replaced by other equivalent or similar features for a similar purpose, unless specifically stated otherwise. That is, unless specifically stated otherwise, each feature is merely one example of a series of equivalent or similar features.

[0018] like Figure 1 As shown, the projectile model in this embodiment includes a head 1 and a body 2. The body 2 is a cylindrical structure with two through-ends and an internal cavity structure with two through-ends. A rod balance passes through the body 2 along its axial direction and connects to the head 1. The head 1 and the body 2 are connected as one unit. The support rod 4 does not contact the inner wall of the body 2 after it is connected to the rod balance.

[0019] like Figure 4 As shown, the body 2 is distributed in a three-segment stepped cylindrical mating surface along the axial direction. The thickness of the body 2 does not exceed 4mm, therefore many conventional structures cannot be used on the thin walls of this embodiment. A step is formed at the end face of the tail section and the middle section of the body 2 to define the telescopic wing 3. Figure 3 The telescopic wing 3 shown includes a wing body extending through both ends, with wings provided on the outer wall of the wing body. The wing body of the telescopic wing 3 is fitted onto the middle section of the body 2, and a first adjustment part 5 is provided between the telescopic wing 3 and the step. A second adjustment part 6 is provided on the front end of the body 2, and the second adjustment part 6 is located between the head 1 and the telescopic wing 3. One end of the second adjustment part 6 is connected to the head 1, and the other end of the second adjustment part 6 contacts the telescopic wing 3, thereby fixing the telescopic wing 3.

[0020] In this embodiment, in order to meet the requirements of wind tunnel testing, after the body 2 and the telescopic wing 3 are connected, the overall thickness of the wall of the body 2 and the wing body cannot exceed 2mm. Under this thickness, the existing general connector structure can no longer meet the requirements.

[0021] The first adjustment section 5 is also a cylindrical structure with both ends open, and its function is to adjust the relative position of the telescopic wings 3 as a whole. As a replacement part, the first adjustment section 5 can have structures with different lengths, and each length of the first adjustment section 5 can adjust the relative position of the telescopic wings 3 on the body 2.

[0022] The second adjustment part 6 is also a cylindrical structure with both ends through it. Like the first adjustment part 5, it is a replacement part and can have a structure with different length dimensions. The second adjustment part 6 adjusts its length according to the first adjustment part 5. When the length of the first adjustment part 5 increases, the length of the second adjustment part 6 decreases. Ultimately, this ensures that the telescopic wing 3 can be axially adjusted on the body part 2.

[0023] In this embodiment, the telescopic wing 3 on the body 2 also serves to achieve circumferential angle changes, therefore the first adjustment part 5 undergoes further structural improvements. For example... Figure 5 As shown, a first groove 52 is provided on one end of the first adjusting part 5, and a first protrusion 21 is provided on the step on the body part 2. The first groove 52 and the first protrusion 21 are used for locking connection. A second protrusion 51 is provided on the other end of the first adjusting part 5, and a second groove 31 is provided on the end of the corresponding telescopic wing 3 fuselage. Figure 3 As shown, when the wing body has several second grooves 31, the telescopic wing 3 can be adjusted in the circumferential direction by engaging different second grooves 31 with the second protrusion 51.

[0024] In this embodiment, in order to ensure a better connection effect, a number of second protrusions 51 are provided on the first adjustment part 5. The number of second protrusions 51 and second grooves 31 are the same and they are evenly distributed, so that when the telescopic wing 3 is rotated, each second protrusion 51 can be engaged with a second groove 31.

[0025] In this embodiment, the first adjustment part 5, the second adjustment part 6, and the telescopic wing 3 are used together. In wind tunnel tests, the telescopic wing 3 can be arranged at different rotation angles, either clockwise or counterclockwise. The axial position of the telescopic wing 3 can also be adjusted by adjusting the length of the first adjustment part 5 and the second adjustment part 6. Thus, the telescopic wing 3 can be changed back and forth and rotated around the axis in the same wind tunnel test.

[0026] This invention is not limited to the specific embodiments described above. The invention extends to any new feature or combination disclosed in this specification, as well as any new method or process step or combination disclosed herein.

Claims

1. A wing extension / retraction and angle-changing device applied to a wind tunnel model, the test model comprising a head and a body connected to each other, a support rod and a rod-type balance passing through the body axially and connecting to the head, wherein the support rod does not contact the body, characterized in that: The body is a cylindrical structure that extends through both ends. A step is provided on the outer circumference of the body. The step is used to limit the telescopic wing that is provided on the body. The telescopic wing includes a wing body that is fitted on the body and a wing that is provided on the wing body. A first adjustment part is provided between the wing body and the step, which can change the axial position and circumferential angle of the telescopic wing relative to the body. The total thickness of the wing body after contacting the body is not greater than 2mm.

2. The wing extension / retraction and angle-changing device for a wind tunnel model according to claim 1, characterized in that: The first adjustment part serves as an alternative structure, and the axial position of the telescopic wing relative to the body is changed by adjusting the length of the first adjustment part.

3. A wing extension / retraction and angle-changing device for a wind tunnel model according to claim 1 or 2, characterized in that: A second adjustment part is provided at the other end of the telescopic wing opposite to the position of the first adjustment part, and one end of the second adjustment part is connected to the head.

4. The wing extension / retraction and angle-changing device for a wind tunnel model according to claim 3, characterized in that: The second adjustment part serves as a replacement structure, and its length is adjusted by adjusting the length of the first adjustment part.

5. The wing extension / retraction and angle-changing device for a wind tunnel model according to claim 1, characterized in that: One end of the first adjusting part is provided with a first groove, and the step is provided with a first protrusion, the first groove matching the first protrusion. The other end of the first adjustment part is provided with a second protrusion, and the end of the wing body is provided with a second groove, the second protrusion matching the second groove.

6. The wing extension / retraction and angle adjustment device for wind tunnel models according to claim 5, characterized in that: The wing body end is provided with several second grooves, and the circumferential angle of the telescopic wing can be changed by different second grooves engaging with the second protrusion.

7. The wing extension / retraction and angle-changing device for a wind tunnel model according to claim 6, characterized in that: A second protrusion is provided on the first adjustment part, the number of which is the same as the number of the second grooves, with one second protrusion corresponding to one second groove.

8. A wing extension / retraction and angle-changing device for a wind tunnel model according to claim 5 or 6, characterized in that: The second groove and the second protrusion are evenly distributed along the circumferential direction of the wing body and the step, respectively.

9. The wing extension / retraction and angle-changing device for a wind tunnel model according to claim 1, characterized in that: Both the telescopic wing and the first adjustment section are cavity structures that extend through both ends.

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