A mounting structure for a blowing model rudder blade

Abstract

The present invention relates to the technical field of blowing model, and discloses a rudder blade mounting structure for a blowing model, which includes a model fuselage, a rudder blade, a variable angle piece and an adjusting piece. The fuselage and the rudder blade are basically mounted and matched through respectively provided shaft holes and rudder shafts. A receiving groove is arranged inside the fuselage, so that the variable angle piece can be positioned and matched with a matching groove on the positioning shaft of the rudder blade through the receiving groove, thereby fixing the rudder blade and controlling its angle. An adjusting piece is also designed behind the variable angle piece, and the adjusting piece can control the variable angle piece through a thread provided on the fuselage, including pressing the variable angle piece to fix and position the rudder blade, and removing the variable angle piece for disassembly or replacement. The invention has a novel structure and reliable installation, can greatly improve the replacement efficiency of the rudder blade, meet the requirements of the blowing model for changing states, and has the characteristics of high structural precision, large variable angle, and simple and easy installation operation, such as the model fuselage.

Description

Technical Field

[0001] The present invention belongs to the technical field of blowing models, and particularly relates to a rudder blade mounting structure for a blowing model. Background Art

[0002] During the development process of various types of aircraft, especially various missile weapons, it is necessary to manufacture a blowing model for aerodynamic experiments and verifications. As the most important flight control component, the rudder blade needs to change various angles during the blowing test. In the structural design of traditional blowing models, the mounting base and the rudder blade are always designed as a whole, and the angle change of the rudder blade is achieved by processing rudder blades with various different angles. However, this method requires that the mounting area and the mounting wall thickness of the mounting part on the model are sufficient, which is difficult to achieve for those blowing models with small size and thin wall thickness. Moreover, this structure has the disadvantages of time-consuming and laborious processing, and it is not easy to replace the state during the blowing test. Therefore, it is particularly important to design a rudder blade mounting structure for a blowing model that is suitable for thin wall thickness, small fuselage, easy to install, and easy to change the state. Summary of the Invention

[0003] The first object of the present invention is to provide a rudder blade mounting structure for a blowing model to solve the deficiencies of the prior art.

[0004] The embodiments of the present invention are implemented as follows:

[0005] A rudder blade mounting structure for a blowing model, comprising:

[0006] A model fuselage;

[0007] A rudder blade, the rudder blade is rotatably connected to the model fuselage through a rotating member provided on the rudder blade, a receiving groove perpendicular to the rotating member is provided on the model fuselage, and a first connecting portion is provided on the rotating member;

[0008] A variable angle piece, the variable angle piece is inserted into the receiving groove, and a second connecting portion is provided at one end of the variable angle piece away from the rotating member;

[0009] An adjusting member, the adjusting member is connected to the second connecting portion, and the adjusting member is used to push the variable angle piece to abut against the first connecting portion to position the rudder blade.

[0010] Further, the rotating member is a cylindrical rotating shaft, and the first connecting portion is a clamping groove that is matched and clamped with the variable angle piece.

[0011] Further, the end surface of the variable angle piece in contact with the first connecting portion is an inclined end surface, and the inclined end surface can cause the rotating shaft to rotate during the process of gradually contacting the first connecting portion.

[0012] Further, the adjusting member includes a front end portion, a middle end portion, and a rear end portion that are integrally formed. The front end portion and the rear end portion are provided with external threads. The second connecting portion is a concave groove, and the concave groove is threadedly connected to the front end portion. Threaded holes are provided on the groove wall of the accommodating groove, and the adjusting member can be connected to the threaded holes so that the adjusting member can push the variable angle piece to reciprocate in the accommodating groove.

[0013] Further, the shaft diameter of the middle end portion is smaller than the shaft diameters of the front end portion and the rear end portion.

[0014] Further, a hexagonal screw hole for adjusting the rotation of the adjusting member is provided on the end face of the rear end portion.

[0015] Further, the notch portion of the accommodating groove is V-shaped.

[0016] The beneficial effects of the present invention are as follows:

[0017] The structure of the present invention is flexible, highly reliable, and occupies a small space. It is applicable to various blowing models. By pushing the variable angle piece against the first connecting portion through the adjusting member, the rudder piece can be positioned on the model fuselage. At the same time, by replacing the variable angle piece with different inclined end faces, during the contact process between the variable angle piece and the first connecting portion, the rudder piece can be rotated, thereby quickly changing the angle of the rudder piece and realizing the switching of different test states of the blowing model. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following will briefly introduce the drawings required for the embodiments. It should be understood that the following drawings only show some embodiments of the present invention, and therefore should not be regarded as limiting the scope. For those of ordinary skill in the art, without creative efforts, other related drawings can also be obtained based on these drawings.

[0019] Figure 1 is a schematic structural diagram of a certain state of the present invention;

[0020] Figure 2 is a schematic structural diagram of another state of the present invention;

[0021] Figure 3 is a schematic structural diagram of the model fuselage;

[0022] Figure 4 is a schematic structural diagram of the variable angle piece;

[0023] Figure 5 is a schematic structural diagram of the variable angle piece;

[0024] Figure 6 is a schematic structural diagram of the adjusting member;

[0025] Figure 7 It is the schematic diagram of the angle transformation of the rudder blade adjusted by the angle-changing piece.

[0026] Icons: 1 - Model fuselage, 2 - Rudder blade, 3 - Angle-changing piece, 4 - Adjusting part, 101 - Connecting block, 102 - Accommodating groove, 103 - Threaded hole, 201 - Rotating part, 202 - Clamping groove, 301 - Second connecting part, 401 - Front end part, 402 - Middle end part, 403 - Rear end part, 404 - Hexagonal threaded hole. Specific embodiments

[0027] To make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. Components of the embodiments of the present invention usually described and illustrated in the accompanying drawings here can be arranged and designed in various different configurations.

[0028] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed present invention, but merely represents selected embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts fall within the scope of protection of the present invention.

[0029] It should be noted that similar reference numerals and letters indicate similar items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings.

[0030] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left",

[0031] "right", "vertical", "horizontal", "inner", "outer", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the inventive product is usually placed during use. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation to the present invention.

[0032] Please refer to Figures 1 to 6As shown in the figure, this embodiment provides a mounting structure for a blowing model rudder blade, including: a model fuselage 1, a rudder blade 2, a variable-angle piece 3, and an adjusting piece 4; a connection hole 101 is machined at the center position of the upper surface of the model fuselage 1, and a rotating piece 201 is integrally formed at the bottom of the rudder blade 2. Preferably, the rotating piece is a cylindrical rotating shaft, and the cylindrical rotating shaft is installed in the connection hole 101 to enable the rudder blade 2 to rotate on the model fuselage 1; a first connection portion 202 is provided at the lower end of the rotating piece 201. The first connection portion 202 is preferably a shaped clamping groove. The model fuselage 1 is provided with a receiving groove 102 on one side of the rotating piece 201 from its right end face. A threaded hole 103 is provided in the receiving groove 102. The threaded hole 103 is parallel to the receiving groove 102 and their axes coincide.

[0033] The variable-angle piece 3 is a plate-shaped structure matching the receiving groove 102. The variable-angle piece 3 is inserted into the receiving groove 102 in a matching manner. The left end face of the variable-angle piece 3 is an inclined end face, and the inclined direction of the inclined end face is inclined from the front end face to the rear end face or from the rear end face to the front end face. The inclination angle of the inclined end face is set according to the angle that the rudder blade needs to rotate during the test; the upper and lower end faces of the variable-angle piece 3 can be attached to the upper and lower end faces of the clamping groove; a second connection portion 301 is provided on the right end face of the variable-angle piece 3. The second connection portion 301 is preferably a concave groove, and internal threads are provided on the groove wall of the concave groove.

[0034] The adjusting piece 4 includes a front end portion 401, a middle end portion 402, and a rear end portion 403 integrally formed. The shaft diameter of the middle end portion 402 is smaller than the shaft diameters of the front end portion 401 and the rear end portion 403. External threads are provided on the front end portion 401 and the rear end portion 403. The front end portion 401 is threadedly connected to the second connection portion 301, that is, the concave groove. A threaded hole 103 is provided on the groove wall of the receiving groove 102. The rear end portion 403 is threadedly connected to the threaded hole 103 of the receiving groove 102. Different from a conventional screw, the adjusting piece 4 can penetrate into the concave groove of the variable-angle piece 3. When screwing out, the narrow-mouth structure on both sides of the concave groove causes the variable-angle piece 3 to be pulled out as the adjusting piece 4 exits. Therefore, by screwing in the adjusting piece 4, the variable-angle piece 3 is pushed to be clamped in the clamping groove, so that the rudder blade 2 is positioned on the model fuselage 1; when the adjusting piece 4 is screwed out, the variable-angle piece 3 exits together with the adjusting piece 4, and the replacement of the rudder blade 2 is simple and convenient.

[0035] See Figure 7As shown in the figure, when changing the angle of the rudder vane 2, insert the rudder vane 2 into the connection hole 101, and then use the adjusting member 4 to push the angle-changing piece 3 to move towards the clamping groove side. Since the left end face of the angle-changing piece 3 is an inclined end face, during the continuous advancement of the angle-changing piece 3, after the inclined end face gradually contacts the vertical surface of the clamping groove, the rudder vane rotates at an angle under the action of force. When the inclined end face is completely fitted with the vertical surface of the clamping groove, the angle adjustment is completed. Therefore, by selecting angle-changing pieces with different inclined end faces, different angle changes of the rudder vane can be achieved in the present invention.

[0036] To facilitate the insertion of the angle-changing piece 3 into the receiving groove 102, a V-shaped structure is provided at the notch of the receiving groove 102; at the same time, to facilitate the rotation of the adjusting member 4, a hexagonal threaded hole 404 is machined on the end face of the rear end portion 403 of the adjusting member 4, and an internal hexagonal wrench can be used for adjustment.

[0037] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, various modifications and changes can be made to the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A mounting structure for a blowing model rudder blade, characterized in that, Comprising: Model fuselage (1); Rudder blade (2), the rudder blade (2) is rotationally connected to the model fuselage (1) through a rotating member (201) provided on the rudder blade (2), a receiving groove (102) perpendicular to the rotating member (201) is provided on the model fuselage (1), a first connecting portion (202) is provided on the rotating member (201), the rotating member (201) is a cylindrical rotating shaft, and the first connecting portion (202) is a clamping groove that is matched and clamped with the angle-changing piece (3); Angle-changing piece (3), the angle-changing piece (3) is inserted into the receiving groove (102), a second connecting portion (301) is provided at one end of the angle-changing piece (3) away from the rotating member (201), the end face of the angle-changing piece (3) in contact with the first connecting portion (202) is an inclined end face, and the inclined end face can cause the rotating member (201) to rotate during the process of gradually contacting the first connecting portion (202); Adjusting member (4), the adjusting member (4) is connected to the second connecting portion (301), and the adjusting member (4) is used to push the angle-changing piece (3) to abut against the first connecting portion (202) to position the rudder blade (2); When the angle of the rudder blade (2) is changed, the adjusting member (4) pushes the angle-changing piece (3) to move towards the clamping groove side. During the continuous advancement of the angle-changing piece (3), after the inclined end face gradually contacts the vertical surface of the clamping groove, the rudder blade (2) rotates in angle. When the inclined end face is completely attached to the vertical surface of the clamping groove, the angle adjustment is completed. Selecting angle-changing pieces (3) with different inclined end faces can achieve different angle changes of the rudder blade (2).

2. The installation structure of the blowing model rudder blade according to claim 1, wherein: The adjusting member (4) includes a front end portion (401), a middle end portion (402), and a rear end portion (403) that are integrally formed. External threads are provided on the front end portion (401) and the rear end portion (403). The second connecting portion (301) is a concave groove, and the concave groove is threadedly connected to the front end portion (401). A threaded hole (103) is provided on the groove wall of the receiving groove (102), and the adjusting member (4) can be connected to the threaded hole (103) so that the adjusting member (4) can push the angle-changing piece (3) to reciprocate in the receiving groove (102).

3. The installation structure of the blowing model rudder blade according to claim 2, characterized in that: The shaft diameter of the middle end portion (402) is smaller than the shaft diameters of the front end portion (401) and the rear end portion (403).

4. The installation structure of the blowing model rudder blade according to claim 2, characterized in that: A hexagonal screw hole (404) for adjusting the rotation of the adjusting member (4) is provided on the end face of the rear end portion (403).

5. The installation structure of the blowing model rudder blade according to claim 1, characterized in that: The notch portion of the receiving groove (102) is V-shaped.

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