UAV and rudder disassembly and assembly structure

Abstract

The present invention discloses an unmanned aerial vehicle (UAV) and a rudder disassembly and assembly structure, belonging to the field of aviation aircraft structure design. The rudder disassembly and assembly structure is provided with a quick-release pin device. The quick-release pin device is composed of a latch, a spring, a fixing flange, a slot frame and an end rib guide hole, etc., so that not only can the rudder be quickly disassembled and assembled, but also can be quickly disassembled and assembled without the aid of tools. The disassembly and assembly process is simple. The rudder disassembly and assembly structure is reliable, and the additional structural weight can be used as a static balance counterweight for the rudder. The rudder disassembly and assembly structure solves the problem of the rudder being able to be replaced quickly and conveniently when the rudder is damaged, and has strong practical application value.

Description

Technical Field

[0001] The present invention belongs to the field of aviation vehicle structure design, and in particular relates to a UAV and a control surface disassembly and assembly structure. Background Art

[0002] UAV control surfaces are dynamic surfaces within the aircraft platform subsystem, such as ailerons, rudders, and elevators. They are typically capable of rotating around a fixed axis, generating differential aerodynamic loads and providing the drone with roll, yaw, and pitch. For conventionally designed UAVs, control surfaces are typically installed on the trailing edges of the main wing and stabilizer surfaces, connected to them via structural or mechanical components. Control surfaces are typically part of the wing or stabilizer airfoil, occupying a spanwise position according to the overall layout. Because they are rotating components and have aerodynamic shape requirements, they generally have installation requirements such as a heading step difference and a scissor difference, requiring high installation precision. Usually there are three main ways to install rudders. One is to use the trailing edge ribs arranged at both ends of the rudder as hanging point joints. The trailing edge ribs make the rudder shaft installation features, and use hole / bushing or hole / joint bearing combination to reduce rotational friction. This form has the problem of inconvenient installation. It is necessary to retain installation channels on both sides of the rudder station, and disassembly and assembly are carried out through bolts or connectors; one is to arrange a hanging point joint on the leading edge of the rudder, and arrange an installation joint on the rear beam or trailing edge of the wing or stabilizer to which it belongs, using a single or double ear connection form, and the shaft needs to use fasteners or non-standard steel shafts. This method requires more installation parts, and tools are needed for disassembly and assembly; one is a non-detachable rudder, which is mostly used on small UAVs. It uses a bendable composite structure or carbon tube to connect to the main wing surface. The disadvantage is that the rudder cannot be replaced separately after it is damaged. Summary of the Invention

[0003] In order to solve the above problems, the present invention discloses a UAV and a rudder disassembly and assembly structure. The technical solution adopted by the present invention is:

[0004] A rudder assembly and disassembly structure for a drone, comprising: a rudder, an outer trailing edge hanging point rib, an inner trailing edge hanging point rib, and a main wing rear wall; the rudder assembly and disassembly structure also comprises: a rudder surface, an outer trailing edge hanging point rib, an inner trailing edge hanging point rib, and a main wing rear wall; the rudder surface assembly and disassembly structure also comprises: a rudder surface front beam and an end rib; the two end ribs are respectively connected vertically and in the same direction to the two sides of the rudder surface front beam; the outer trailing edge hanging point rib and the inner trailing edge hanging point rib are respectively connected to the outer sides of the two end ribs; the rudder surface covers the outside of the internal frame structure; the main wing rear wall is located on the outer side of the rudder surface front beam; the rudder surface assembly and disassembly structure also comprises a quick-release pin device, which is provided at the connection between the end rib and the rudder surface front beam The quick-release pin device includes: a latch, a fixing flange, an end rib guide hole and a joint bearing, the outer ring of the joint bearing is connected to the outer trailing edge hanging rib or the inner trailing edge hanging rib, the fixing flange is fixedly connected to the outer side of the end of the front beam of the rudder, a flange hole is provided on the fixing flange, and an end rib guide hole is provided on the end rib on the same side of the fixing flange at a position opposite to the flange hole, the latch passes through the flange hole and the end rib guide hole, and the latch can be adjusted to extend and retract the outer surface of the end rib and be fixed. When the latch extends out of the outer surface of the end rib, the protruding part of the latch is connected to the inner ring of the joint bearing.

[0005] Furthermore, the latch is provided with a blocking portion, which divides the latch into a long portion and a short portion, and a handle perpendicular to the latch is provided at the blocking portion.

[0006] The cam is secured to the rear of the latch and has an L-shaped guide hole that is adapted to lock the latch pin when the latch is in a locked position.

[0007] Furthermore, a spring is sleeved on the outside of the pin between the flange hole and the blocking portion, and the supporting points at both ends of the spring are the edges of the flange hole and the blocking portion on the opposite side. As the pin slides back and forth between the flange hole and the end rib guide hole, the compression degree of the spring also changes accordingly, and the handle can be stopped at the short side. At this time, the spring is in a highly compressed state, and the end of the short part is flush with the outer outlet of the end rib guide hole.

[0008] Furthermore, the blocking portion is an annular continuous protrusion or an annular spaced protrusion at the position of the latch.

[0009] Furthermore, the quick-release pin device is arranged on one side of the front beam of the rudder.

[0010] Furthermore, the free end of the short portion is connected to the spherical bearing, and the spherical bearing is connected to the outer trailing edge hanging point rib or the inner trailing edge hanging point rib on this side.

[0011] Furthermore, the rotation angle range of the spherical bearing is ±22.5°, calculated with the normal position being 0°.

[0012] Furthermore, the material used for the quick-release pin device is aluminum alloy.

[0013] A UAV comprises the UAV control surface disassembly and assembly structure.

[0014] The present invention has the following beneficial effects:

[0015] The present invention provides a design for a quick disassembly and assembly structure of a drone rudder, which not only realizes the quick disassembly and installation of the rudder, but also can realize quick disassembly and installation without the aid of tools. The disassembly and installation process is simple. The rudder disassembly and assembly structure is safe and reliable, and the additional structural weight can be used as a static balance weight for the rudder. The rudder disassembly and assembly structure solves the problem of quick and convenient replacement of the rudder individually when the rudder is damaged, and has strong practical application value. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of the overall exterior of a UAV rudder assembly and disassembly structure according to the present invention;

[0017] Figure 2 This is a schematic diagram of the position of the joint bearings of a UAV rudder disassembly and assembly structure of the present invention;

[0018] Figure 3 This is a schematic diagram of the composition of a rudder surface disassembly and assembly structure of a UAV rudder surface of the present invention;

[0019] Figure 4 A schematic diagram of a latch for a UAV rudder assembly and disassembly structure according to the present invention;

[0020] Figure 5 This is a schematic diagram of a pin of a UAV rudder disassembly and assembly structure according to the present invention being installed on a joint bearing;

[0021] Figure 6 This is a schematic diagram of the pin handle of the UAV rudder disassembly and assembly structure of the present invention moving along the slide groove;

[0022] Figure 7This is a schematic diagram of the disengagement of the latch and the joint bearing of the UAV rudder disassembly and assembly structure of the present invention;

[0023] Figure 8 This is a schematic diagram of the disassembly of the rudder surface of a UAV rudder surface disassembly structure according to the present invention after rotation.

[0024] The numbers in the figure are: main wing rear wall - 1, rudder surface - 2, inner trailing edge hanging point rib - 3, outer trailing edge hanging point rib - 4, joint bearing - 5, end rib - 6, slot frame - 7, rudder front beam - 8, fixing flange - 9, latch - 10, spring - 11, baffle - 12, handle - 13. DETAILED DESCRIPTION

[0025] In order to better understand the technical solution of the present invention, the embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0026] As shown in the figure, Figure 1 This is a schematic diagram of the overall exterior of a UAV rudder assembly and disassembly structure according to the present invention; Figure 2 This is a schematic diagram of the position of the joint bearings of a UAV rudder disassembly and assembly structure of the present invention; Figure 3 This is a schematic diagram of the composition of a rudder surface disassembly and assembly structure of a UAV rudder surface of the present invention; Figure 4 A schematic diagram of a latch for a UAV rudder assembly and disassembly structure according to the present invention; Figure 5 This is a schematic diagram of a pin of a UAV rudder disassembly and assembly structure according to the present invention being installed on a joint bearing; Figure 6 This is a schematic diagram of the pin handle of the UAV rudder disassembly and assembly structure of the present invention moving along the slide groove; Figure 7 This is a schematic diagram of the disengagement of the latch and the joint bearing of the UAV rudder disassembly and assembly structure of the present invention; Figure 8 This is a schematic diagram of the disassembly of the rudder surface of a UAV rudder surface disassembly structure according to the present invention after rotation.

[0027] The UAV rudder assembly and disassembly structure includes: a rudder surface 2, an outer trailing edge hanging point rib 4, an inner trailing edge hanging point rib 3, and a main wing rear wall 1. The rudder surface disassembly and assembly structure also includes an internal frame structure: a rudder front beam 8 and an end rib 6. The two end ribs 6 are respectively connected to the two sides of the rudder front beam 8 vertically and in the same direction. The outer trailing edge hanging point rib 4 and the inner trailing edge hanging point rib 3 are respectively connected to the outside of the two end ribs 6. The rudder surface 2 covers the outside of the internal frame structure. The main wing rear wall 1 is located on the outside of the rudder front beam 8. The rudder surface disassembly and assembly structure also includes a quick-release pin device, which is provided at the connection between the end rib 6 and the rudder front beam 8. The quick-release pin device It includes: a latch 10, a fixing flange 9, an end rib guide hole and a spherical bearing 5, the outer ring of the spherical bearing 5 is connected to the outer trailing edge hanging rib 4 or the inner trailing edge hanging rib 3, the fixing flange 9 is fixedly connected to the outer side of the end of the front beam 8 of the rudder, the fixing flange 9 is provided with a flange hole, and an end rib guide hole is provided on the end rib 6 on the same side of the fixing flange 9 at a position opposite to the flange hole, the latch 10 passes through the flange hole and the end rib guide hole, and the latch can be adjusted to extend and retract the outer surface of the end rib 6 and be fixed. When the latch 10 extends out of the outer surface of the end rib 6, the protruding part of the latch 10 is connected to the inner ring of the spherical bearing 5.

[0028] The latch 10 is provided with a baffle 12, which divides the latch into a long part and a short part. A handle 13 is provided at the position of the baffle 12 and is perpendicular to the latch 10. The disassembly and assembly structure is also provided with a slot frame 7, which is fixed to the leading edge skin of the rudder and the end rib 6. An L-shaped slide is provided on the slot frame 7. The long part passes through the flange hole, and the short part passes through the end rib guide hole. A spring 11 is sleeved on the outside of the latch 10 between the flange hole and the baffle. The fulcrums at both ends of the spring 11 are the edges on the opposite side of the flange hole and the baffle 12 respectively. The handle 13 passes through the L-shaped slide. The long side of the L-shaped slide is parallel to the axial direction of the latch, and the short side of the L-shaped slide is perpendicular to the axial direction of the latch. Along the The sliding handle 13 on the long side of the slide groove can enable the pin 10 to slide back and forth between the flange hole and the end rib guide hole, and the compression degree of the spring also changes accordingly. The handle can be stuck at the short side. At this time, the spring is in a high compression state, and the end of the short part is flush with the outer outlet of the end rib guide hole. When the handle is located at the end of the long side away from the short side, the short part extends out of the end rib guide hole, and the protruding part of the short part is inserted into the inner ring of the joint bearing 5. The outer ring of the joint bearing 5 is connected to the outer rear edge hanging point rib 4 or the inner rear edge hanging point rib 3.

[0029] The blocking portion 12 is a continuous annular protrusion or annular spaced protrusions at the position of the latch 10. The quick-release pin assembly is disposed on one side of the rudder front beam 8. The free end of the short portion is connected to the spherical bearing 5, which is connected to the outer trailing edge attachment rib 4 or the inner trailing edge attachment rib 3 on that side. The rotation angle range of the spherical bearing 5 is ±22.5°, calculated with the normal position being 0°. The quick-release pin assembly is made of aluminum alloy.

[0030] A UAV comprising the UAV rudder disassembly and assembly structure.

[0031] The embodiments of the present invention are further described above with reference to the accompanying drawings, but the present invention is not limited to the described embodiments. It is apparent 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 the changes still fall within the scope of protection of the present invention.

Claims

1. A rudder assembly and disassembly structure for an unmanned aerial vehicle (UAV), comprising a rudder surface, an outer trailing edge attachment rib, an inner trailing edge attachment rib, and a main wing rear wall. The rudder surface assembly and disassembly structure further comprises an internal frame structure, a rudder front beam, and end ribs, wherein two end ribs are respectively connected perpendicularly and in the same direction to two sides of the rudder front beam, the outer trailing edge attachment rib and the inner trailing edge attachment rib are respectively connected to the outer sides of the two end ribs, the rudder surface covers the exterior of the internal frame structure, and the main wing rear wall is located outside the rudder front beam. The structure is characterized in that: The rudder surface disassembly and assembly structure also includes a quick-release pin device, which is provided at the connection between the end rib and the rudder surface beam, and the quick-release pin device includes a latch, a fixing flange, an end rib guide hole and a joint bearing, the outer ring of the joint bearing is connected to the outer trailing edge hanging point rib or the inner trailing edge hanging point rib, and the fixing flange is fixedly connected to the outer side of the end of the rudder surface beam, the fixing flange is provided with a flange hole, and an end rib guide hole is provided on the end rib on the same side of the fixing flange at a position directly opposite to the flange hole, the latch passes through the flange hole and the end rib guide hole, and the latch can be adjusted to extend and retract the outer surface of the end rib and be fixed, and when the latch extends out of the outer surface of the end rib, the protruding part of the latch is connected to the inner ring of the joint bearing; The latch is provided with a blocking portion, which divides the latch into a long portion and a short portion, and a handle perpendicular to the latch is provided at the blocking portion; The cam is secured to the rear of the latch and has an L-shaped slot where the latch is located, and the cam is secured to the rear of the latch and has an L-shaped slot where the latch is located.

2. The UAV control surface disassembly and assembly structure according to claim 1, characterized in that: The supporting points at both ends of the spring are the edges of the flange hole and the opposite side of the barrier portion respectively. As the pin slides back and forth between the flange hole and the end rib guide hole, the compression degree of the spring also changes accordingly. The handle can be stopped at the short side. At this time, the spring is in a highly compressed state, and the end of the short portion is flush with the outer outlet of the end rib guide hole.

3. The UAV control surface disassembly and assembly structure according to claim 2, characterized in that: The blocking portion is an annular continuous protrusion or an annular spaced protrusion at the position of the latch.

4. The UAV control surface disassembly and assembly structure according to claim 1, characterized in that: The quick-release pin device is arranged on one side of the front beam of the rudder.

5. The UAV control surface disassembly and assembly structure according to claim 1, characterized in that: The free end of the short portion is connected to the spherical bearing, and the spherical bearing is connected to the outer trailing edge hanging point rib or the inner trailing edge hanging point rib.

6. The UAV control surface disassembly and assembly structure according to claim 5, characterized in that: The rotation angle range of the spherical joint bearing is ±22.5°, calculated with the normal position being 0°.

7. The UAV control surface disassembly and assembly structure according to any one of claims 1 to 6, characterized in that: The material used for the quick-release pin device is aluminum alloy.

8. A drone, characterized by: The UAV comprises the UAV control surface disassembly and assembly structure according to any one of claims 1 to 6.

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