Rudder wing structure

Abstract

The utility model discloses a rudder wing structure, which belongs to the technical field of control surfaces and comprises a rudder shaft, a control surface, a control surface shaft and a torsion spring. An axial through groove matched with the root of the control surface is formed in the tip of the rudder shaft, a radial through hole penetrating through the axial through groove is further formed in the rudder shaft, the control surface shaft is inserted into the radial through hole in a penetrating mode, a shaft hole matched with the control surface shaft is formed in the root of the control surface, and a stop structure is further arranged between the control surface shaft and the rudder shaft. And the torsion spring is sleeved on the control surface shaft and is fixed between the control surface and the control surface shaft. The utility model has the advantages of simple structure and reasonable design.

Description

Technical Field

[0001] This utility model relates to the field of rudder surface technology, and in particular to a rudder wing structure. Background Technology

[0002] Control surfaces are components installed on aircraft to change the aircraft's flight attitude. Control surfaces are usually installed on the surface of the aircraft. Unless for maintenance, control surfaces are usually installed on the surface of the aircraft in a non-removable manner, such as the control surfaces of an airplane. When the aircraft is in normal use, the control surfaces installed on its surface do not affect the normal operation of the aircraft.

[0003] However, for smaller and more regular-shaped aircraft such as missiles, the relative size of their control surfaces is significantly larger. This results in higher size requirements for the transfer and storage equipment of the missile. Therefore, it is necessary to design the missile's control surfaces to reduce the size requirements of the storage equipment without affecting the missile's normal flight.

[0004] However, the existing missile control surface folding structure has some defects. For example, Chinese invention patent CN109253667A discloses a missile folding control surface longitudinal unfolding mechanism, in which the folding control surface can rotate around the spindle under the action of a tension spring, but the structure of the folding control surface is more complicated. Summary of the Invention

[0005] In view of the problem that the folding structure of missile control surfaces is complex in the prior art, the purpose of this utility model is to provide a control wing structure so as to at least partially solve the above-mentioned problems.

[0006] To achieve the above objectives, the technical solution of this utility model is as follows:

[0007] A rudder structure includes a rudder shaft, a rudder surface, a rudder surface shaft, and a torsion spring. The tip of the rudder shaft has an axial through groove that matches the root of the rudder surface. The rudder shaft also has a radial through hole that passes through the axial through groove. The rudder surface shaft is inserted into the radial through hole, and the root of the rudder surface has a shaft hole that matches the rudder surface shaft. A stop structure is also provided between the rudder surface shaft and the rudder shaft. The torsion spring is sleeved on the rudder surface shaft and is fixed between the rudder surface and the rudder surface shaft.

[0008] In some preferred embodiments, the stop structure includes a threaded hole formed on the rudder shaft and communicating with the radial through hole, and a set screw screwed into the threaded hole, the set screw being used to press against the rudder shaft.

[0009] In some preferred embodiments, the stop structure includes a stop step disposed on the rudder shaft and having a diameter larger than the radial through hole. The stop structure also includes a retaining ring and screws for fixing the retaining ring to the rudder shaft. The rudder shaft is located between the retaining ring and the stop step. The mating point between the radial through hole and the rudder shaft is a non-circular mating surface.

[0010] In some preferred embodiments, the non-circular mating surface is square.

[0011] In some preferred embodiments, the rudder shaft includes a smaller diameter tip and a larger diameter root, with the screw screwed onto the tip of the rudder shaft.

[0012] In some preferred embodiments, a limiting groove is provided on the end face of the rudder shaft, and one end of the torsion spring is engaged in the limiting groove to prevent the torsion spring from rotating circumferentially relative to the rudder shaft.

[0013] In some preferred embodiments, the limiting slot is arranged along the radial direction of the rudder surface shaft.

[0014] In some preferred embodiments, the two ends of the rudder shaft are exposed on both sides of the rudder shaft, and the two ends of the torsion spring are respectively sleeved on the two sides of the rudder shaft exposed on the rudder shaft, so as to prevent the torsion spring from axially moving relative to the rudder shaft.

[0015] The beneficial effects of this invention, achieved by adopting the above technical solution, are as follows: Through the axial through groove on the rudder shaft and the arrangement of the rudder surface shaft and torsion spring, the rudder surface can rotate both around the rudder surface shaft and under the drive of the rudder shaft. This allows the rudder surface to switch between two positions: perpendicular to and parallel to the missile. When the rudder surface is perpendicular to the missile, it is in a folded state, and the torsion spring stores the elastic force needed to unfold the rudder surface. Compared to existing technologies, the structure of this invention is simpler. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the structure of this utility model.

[0017] Figure 2 This is a cross-sectional view of Embodiment 1 of the present utility model.

[0018] Figure 3 This is a cross-sectional view of Embodiment 2 of the present invention.

[0019] In the diagram: 1-rudder shaft, 2-rudder surface, 3-rudder surface shaft, 4-torsion spring, 5-set screw, 6-pressure bar, 7-limiting groove, 8-retaining ring, 9-screw. Detailed Implementation

[0020] The following further describes specific embodiments of the present invention in conjunction with the accompanying drawings. It should be noted that the descriptions of these embodiments are intended to aid understanding of the present invention and do not constitute limitations on the present invention. Furthermore, the technical features involved in the various embodiments of the present invention described below may be combined with one another as long as they do not conflict with one another.

[0021] It should be noted that in the description of this utility model, the terms "upper", "lower", "left", "right", "front", "rear", etc., indicate the orientation or positional relationship based on the description of the structure of this utility model shown in the accompanying drawings. They are only for the convenience of describing this utility model and 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. Therefore, they should not be construed as limitations on this utility model.

[0022] The terms "first" and "second" in this technical solution are merely designations for corresponding structures that are identical or similar, or that perform similar functions. They do not represent an arrangement of the importance of these structures, nor do they imply any ranking, comparison of size, or other meaning.

[0023] Furthermore, unless otherwise explicitly specified and limited, the terms "installation" and "connection" should be interpreted broadly. For example, a 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 structures. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the overall concept and the specific context of the solution.

[0024] Example 1

[0025] A rudder structure includes a rudder shaft 1, a rudder surface 2, a rudder surface shaft 3, and a torsion spring 4.

[0026] The root of the rudder shaft 1 is used to connect to the servo motor, and the tip of the rudder shaft 1 has an axial through groove. The axial through groove has two parallel and oppositely arranged side walls, and the axis of the rudder shaft 1 is located in the plane of symmetry between the two side walls. The width of the axial through groove is approximately equal to the thickness of the root of the rudder surface 2, so that the root of the rudder surface 2 can extend into the axial through groove and move within it.

[0027] The rudder shaft 1 also has a radial through hole that passes through the axial through groove. The axis of the radial through hole intersects perpendicularly with the axis of the rudder shaft 1. Thus, when the rudder surface shaft 3 is inserted into the radial through hole, the rudder surface shaft 3 can be inserted into the rudder shaft 1 in a manner that passes through the axial through groove. In addition, the root of the rudder surface 2 also has a shaft hole that matches the rudder surface shaft 3, so that the rudder surface 2 can move in the axial through groove by rotating around the axis of the rudder surface shaft 3.

[0028] A stop structure is also provided between the rudder surface shaft 3 and the rudder shaft 2. The rudder surface shaft 3 is prevented from axially moving or circumferentially rotating relative to the rudder shaft 2 by the setting of this stop structure.

[0029] In this embodiment, the stop structure includes a threaded hole formed on the rudder shaft 1 and communicating with the radial through hole, and a set screw 5 screwed into the threaded hole. Typically, the threaded hole is perpendicular to the radial through hole, and a planar clamping platform is provided on the side wall of the rudder shaft 3 so that the set screw 5 can press against the clamping platform. In this way, the pressure given by the set screw 5 clamps the rudder shaft 3, thereby preventing the rudder shaft 3 from axially moving and circumferentially rotating relative to the rudder shaft 2.

[0030] The torsion spring 4 is sleeved on the rudder shaft 3, and the torsion spring 4 is fixed between the rudder 2 and the rudder shaft 3.

[0031] In this embodiment, the torsion spring 4 is configured to prevent axial movement and circumferential rotation relative to the rudder shaft 3. For example, both ends of the rudder shaft 3 protrude from both sides of the rudder shaft 1, and both ends of the torsion spring 4 are respectively fitted onto the sides of the rudder shaft 3 protruding from the rudder shaft 1 to prevent axial movement of the torsion spring 4 relative to the rudder shaft 3. A radially outward protruding pressure strip 6 is formed at the position opposite to the axial through groove in the axial direction of the torsion spring 4, and the pressure strip 6 is used to provide elastic force to the rudder 2.

[0032] In addition, a limiting groove 7 is provided on one of the end faces of the rudder shaft 3 that is exposed on the end face of the rudder shaft 1. The limiting groove 7 is set in the radial direction of the rudder shaft 3, and one end of the torsion spring 4 is correspondingly embedded in the limiting groove 7 to prevent the torsion spring 4 from rotating circumferentially relative to the rudder shaft 3.

[0033] The rudder structure provided in this embodiment of the utility model is used as follows:

[0034] In use, the control wing structure is mounted on an aircraft (such as a missile), and in the mounted state, the axis of control shaft 1 is perpendicular to the missile's axis. Before the missile takes flight, control surface 2 is in a folded state, meaning... Figure 1 Control surface 2 rotates upwards by 90°, and then control shaft 1 rotates by 90°, thus making control surface 2 parallel to the length direction of the missile. At this time, torsion spring 4 is compressed and stores elastic force, and control surface 2 is restricted by the missile storage box (tube) and cannot be deployed. When the missile is used, control surface 2 is no longer restricted and is deployed under the elastic force of torsion spring 4, causing control surface 2 to rotate to a position perpendicular to the missile axis. The deflection angle of control surface 2 can be adjusted by the servo motor on the missile driving the control shaft 1, thus enabling the control wing structure to function.

[0035] Example 2

[0036] Compared to Example 1, the stop structure in this example is different.

[0037] In this embodiment, the rudder shaft 3 includes a tip with a smaller diameter and a root with a larger diameter, and a stop step is formed at the connection between the two. The diameter of the tip of the rudder shaft 3 is smaller than the radial through hole on the rudder shaft 1, so that the tip of the rudder shaft 3 can pass through the radial through hole, while the diameter of the root of the rudder shaft 3 is larger than the radial through hole on the rudder shaft 1, so that the rudder shaft 3 can stop at the stop step when passing through the radial through hole.

[0038] Furthermore, near the stop step, the part where the rudder shaft 3 mates with the radial through hole has a non-circular cross section, such as a square, which prevents the rudder shaft 3 from rotating in the radial through hole, meaning that the rudder shaft 3 cannot rotate circumferentially relative to the rudder shaft 1.

[0039] In addition, the stop structure includes a retaining ring 8 and a screw 9 for fixing the retaining ring 8 to the rudder shaft 3. The diameter of the retaining ring 8 is larger than the diameter of the tip of the rudder shaft 3. The rudder shaft 1 is located between the retaining ring 8 and the stop step, so that the rudder shaft 3 cannot move axially under the restriction of the retaining ring 8 and the stop step.

[0040] The embodiments of the present invention are described in detail above with reference to the accompanying drawings, but the present invention is not limited to the described embodiments. It is clear to those skilled in the art that various changes, modifications, substitutions, and variations to these embodiments may be made without departing from the principles and spirit of the present invention, and these changes and modifications still fall within the scope of protection of the present invention.

Claims

1. A rudder wing structure, characterized in that: The system includes a rudder shaft, a rudder surface, a rudder surface shaft, and a torsion spring. The rudder shaft has an axial through groove at its tip that matches the root of the rudder surface. The rudder shaft also has a radial through hole that passes through the axial through groove. The rudder surface shaft is inserted into the radial through hole, and the root of the rudder surface has a shaft hole that matches the rudder surface shaft. A stop structure is also provided between the rudder surface shaft and the rudder shaft. The torsion spring is sleeved on the rudder surface shaft and is fixed between the rudder surface and the rudder surface shaft.

2. The rudder structure according to claim 1, characterized in that: The stop structure includes a threaded hole formed on the rudder shaft and connected to the radial through hole, and a set screw screwed into the threaded hole, the set screw being used to press against the rudder shaft.

3. The rudder structure according to claim 1, characterized in that: The stop structure includes a stop step disposed on the rudder shaft and having a diameter larger than the radial through hole. The stop structure also includes a retaining ring and a screw for fixing the retaining ring on the rudder shaft. The rudder shaft is located between the retaining ring and the stop step. The mating point between the radial through hole and the rudder shaft is a non-circular mating surface.

4. The rudder structure according to claim 3, characterized in that: The non-circular mating surface is square.

5. The rudder structure according to claim 3, characterized in that: The rudder shaft includes a smaller diameter tip and a larger diameter root, and the screw is screwed onto the tip of the rudder shaft.

6. The rudder structure according to claim 1, characterized in that: A limiting groove is provided on the end face of the rudder shaft, and one end of the torsion spring is fitted into the limiting groove to prevent the torsion spring from rotating circumferentially relative to the rudder shaft.

7. The rudder structure according to claim 6, characterized in that: The limiting slot is arranged along the radial direction of the rudder surface shaft.

8. The rudder structure according to claim 1, characterized in that: The two ends of the rudder shaft are exposed on both sides of the rudder shaft, and the two ends of the torsion spring are respectively sleeved on the two sides of the rudder shaft exposed on both sides of the rudder shaft to prevent the torsion spring from moving axially relative to the rudder shaft.

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