CN218858672U

CN218858672U - Folding rudder locking mechanism

Info

Publication number: CN218858672U
Application number: CN202222868237.4U
Authority: CN
Inventors: 董楠楠
Original assignee: China Airborne Missile Academy
Current assignee: China Airborne Missile Academy
Priority date: 2022-10-28
Filing date: 2022-10-28
Publication date: 2023-04-14
Anticipated expiration: 2032-10-28

Abstract

A locking mechanism of a folding rudder is characterized in that the folding rudder is formed by hinging an upper rudder body and a lower rudder body; the locking mechanism comprises a pin hole arranged on the upper rudder body, and a top pin, a pressure spring and a base which are arranged in a top pin hole of the lower rudder body; the base is provided with a shearing screw rod, and the shearing screw rod penetrates through the pressure spring and the ejector pin and then is in threaded connection with the nut, so that the pressure spring is in a pressed state; the upper rudder body impacts the nut when rotating, the shearing screw rod is cut off through the nut, and then the ejector pin is ejected in the pin hole of the upper rudder body under the action of the pressure spring. Because the shearing screw of base forms a coupling assembling after penetrating pressure spring, knock pin and nut spiro union, this coupling assembling can directly put into in the knock pin hole from the upper end of knock pin hole when the assembly, is favorable to reducing the degree of difficulty of assembly and maintenance. Particularly, when the upper rudder body is assembled, the upper rudder body is not interfered by upward pressing force of the ejector pin. In addition, the locking mechanism is beneficial to improving the integrity of the control surface and the stability of flight, and simultaneously reduces the processing difficulty of the rudder.

Description

Folding rudder locking mechanism

Technical Field

The utility model belongs to the technical field of the aircraft and specifically relates to a folding rudder locking mechanism is related to.

Background

In order to reduce the volume, the rudder of an aircraft needs to be designed to be foldable, and the foldable rudder needs to be capable of automatically unfolding when the aircraft is ejected from the launching tube.

As shown in fig. 1-3, the foldable rudder is composed of a lower rudder body and an upper rudder body, and the lower rudder body and the upper rudder body are hinged through a hinge shaft to realize the folding of the rudder. The lower rudder body is connected with a steering engine arranged in the aircraft shell so as to realize the rotation of the rudder. The lower rudder body is provided with a top spring and a top pin, the upper rudder body is provided with a pin hole corresponding to the top pin, and a torsion spring (not shown in the figure) is arranged between the lower rudder body and the upper rudder body. When the aircraft is ejected from the launching tube, the upper rudder body rotates around the hinged shaft under the action of the torsion spring, and the ejector pin is ejected into the pin hole at the moment, so that the folding rudder is completely unfolded. At present, the following problems exist in the existing folding rudder:

1. in order to enable the ejector pin to be smoothly ejected into the pin hole, a transition cambered surface needs to be processed on the upper rudder body, and therefore the processing difficulty of the upper rudder body is increased. Furthermore, a large gap must be left between the lower rudder body and the upper rudder body, which is detrimental to the stability of the rudder surface in flight.

2. When the rudder is folded or maintained, the ejector pin needs to be pulled out from the pin hole, and the rudder can be folded and maintained only by detaching the whole rudder from the steering engine at present.

3. Due to the jacking force of the jacking pin, the upper rudder body is interfered when being assembled with the lower rudder body.

SUMMERY OF THE UTILITY MODEL

In order to overcome not enough in the background art, the utility model discloses a folding rudder locking mechanism adopts following technical scheme:

a locking mechanism of a folding rudder is characterized in that the folding rudder is formed by hinging an upper rudder body and a lower rudder body; the locking mechanism comprises a pin hole arranged on the upper rudder body, and a top pin, a pressure spring and a base which are arranged in a top pin hole of the lower rudder body; the base is provided with a shearing screw rod, and the shearing screw rod penetrates through the pressure spring and the ejector pin and then is in threaded connection with the nut, so that the pressure spring is in a pressed state; when the upper rudder body rotates, the nut is impacted, the shearing screw rod is cut off through the nut, and then the ejector pin is ejected in the pin hole of the upper rudder body under the action of the pressure spring.

The technical scheme is further improved, the lower rudder body is provided with a hinged shaft, and the upper rudder body is hinged with the lower rudder body through the hinged shaft; the upper end surface of the lower rudder body is a concave cambered surface, and the concave cambered surface takes the axis of a hinged shaft as a rotation axis.

The technical scheme is further improved, and the lower rudder body is provided with a strip hole; the knock pin detachably is connected with the driving lever, and the driving lever can outwards run through the strip hole and can move up and down in the strip hole.

Further improve technical scheme, be equipped with radial screw hole on the knock pin, the driving lever can the spiro union in the screw hole.

Further improve technical scheme, be equipped with the circumference annular on the knock pin, the driving lever can inject in the circumference annular.

Further improve technical scheme, the reducing portion of shearing screw rod is located the oral area of knock-pin hole.

Owing to adopt above-mentioned technical scheme, compare the background art, the utility model discloses following beneficial effect has:

because the shear screw of base forms a coupling assembling after running through pressure spring, knock pin and nut spiro union, this coupling assembling can be directly put into in the knock pin hole from the upper end of knock pin hole when the assembly, is favorable to reducing the degree of difficulty of assembly and maintenance. Particularly, when the upper rudder body is assembled, the upper rudder body is not interfered by upward pressing force of the ejector pin.

The upper end surface of the lower rudder body is a concave cambered surface, and the concave cambered surface can reduce a gap between the lower rudder body and the upper rudder body, so that the stability of the rudder surface in flight can be improved. In addition, the upper rudder body part does not need to be processed with a transition cambered surface, so that the integrity of the rudder surface can be ensured, and the processing difficulty of the upper rudder body is reduced.

Drawings

Fig. 1 to 3 are schematic structural views of a conventional locking mechanism when a rudder body is unfolded.

Fig. 4-6 are schematic structural views of the locking mechanism when the upper rudder body is unfolded.

Fig. 7 is a schematic structural view of the locking mechanism when the rudder body is folded.

In the figure: 1. an upper rudder body; 11. a pin hole; 2. a lower rudder body; 21. hinging a shaft; 22. a strip hole; 23. a knock pin hole; 24. a concave arc surface; 3. an aircraft skin; 4. a steering engine; 5. a knock pin; 51. a threaded hole; 6. a pressure spring; 7. a base; 71. shearing the screw rod; 8. a nut; 9. a deflector rod.

Detailed Description

Preferred embodiments of the present invention will be described below with reference to the accompanying drawings. It should be understood by those skilled in the art that these embodiments are only for explaining the technical principle of the present invention, and are not intended to limit the scope of the present invention. It should be noted that in the description of the present invention, the terms "front", "back", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate directions or positional relationships based on those shown in the drawings, which are merely for convenience of description, but do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. It should also be noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly and include, for example, fixed or removable connections or integral connections; can be mechanically or electrically connected; either directly or indirectly through intervening media, or through both elements. The specific meaning of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

A locking mechanism of a folding rudder is shown in figures 4-6, and the folding rudder is formed by hinging an upper rudder body 1 and a lower rudder body 2. Specifically, the lower rudder body 2 is provided with an articulated shaft 21, and the upper rudder body 1 is articulated with the lower rudder body 2 through the articulated shaft 21 so as to realize the folding of the rudder. A torsion spring (not shown in the figure) is arranged between the lower rudder body 2 and the upper rudder body 1 and provides rotation power for the upper rudder body 1. Steering wheel 4 is fixed in aircraft shell 3, and lower rudder body 2 is connected with steering wheel 4, and steering wheel 4 is used for driving the rotation of rudder face.

The locking mechanism comprises a pin hole 11 arranged on the upper rudder body 1, and a knock pin 5, a pressure spring 6 and a base 7 which are arranged in a knock pin hole 23 of the lower rudder body 2. Specifically, as shown in fig. 4, the knock pin hole 23 is a through hole, the base 7 has a shear screw 71, and a reduced diameter portion of the shear screw 71 is broken by a shearing force. The shear screw 71 penetrates through the compression spring 6 and the ejector pin 5 and then is in threaded connection with the nut 8 to form a connecting assembly, and the compression spring 6 is in a compressed state in the connecting assembly. Thus, the connecting component can be directly put into the thimble hole 23 from the upper end of the thimble hole 23 during assembly, and particularly, the upper rudder body 1 is not interfered by the upward jacking force of the thimble 5 during assembly of the upper rudder body 1.

As shown in fig. 5, the upper end surface of the lower rudder body 2 is a concave arc surface 24, and the concave arc surface 24 takes the axis of the hinge shaft 21 as a rotation axis. The reduced diameter portion of the shear screw 71 is located at the mouth of the knock pin hole 23, and the nut 8 is located above the knock pin hole 23. When the upper rudder body 1 rotates, the upper rudder body 1 strikes against the nut 8, and the reduced diameter portion of the shear screw 71 is cut by the nut 8, and then the knock pin 5 is pushed into the pin hole 11 of the upper rudder body 1 by the compression spring 6. 3-6, the upper end surface of the lower rudder body 2 is designed into a concave cambered surface 24, so that a gap between the lower rudder body 2 and the upper rudder body 1 can be reduced, and the stability of the rudder surface in flight can be improved. Because the upper rudder body 1 part does not need to be processed with a transition cambered surface any more, the integrity of the control surface is ensured, and the processing difficulty of the upper rudder body 1 is reduced.

In order to facilitate the folding and maintenance of the rudder, as shown in fig. 7, a long hole 22 is provided on the lower rudder body 2, the lifting rod 9 is detachably connected to the knock pin 5, and the lifting rod 9 can penetrate through the long hole 22 outwards and can move up and down in the long hole 22. The driver 9 is used as an accessory tool and is connected with the ejector pin 5 only when being folded and maintained, so that the purpose of pressing the ejector pin 5 is achieved. In the present embodiment, a radial threaded hole 51 is provided in the knock pin 5, and the shift lever 9 is screwed into the threaded hole 51. The lifting lever 9 is pressed down to enable the ejector pin 5 to be pulled out of the pin hole 11, so that the upper rudder body 1 can be folded and detached for maintenance. Since the knock pin 5 can rotate, the screw hole 51 is not necessarily aligned with the elongated hole 22, and therefore, a circumferential ring groove can be further formed in the knock pin 5, and the shift lever 9 can be inserted into the circumferential ring groove of the knock pin 5 through the elongated hole 22, and the knock pin 5 can be removed from the pin hole 11 by pressing down the shift lever 9.

The details of which are not described in detail in the prior art. Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides a folding rudder locking mechanism, folding rudder is formed by last rudder body and lower rudder body are articulated, characterized by: the locking mechanism comprises a pin hole arranged on the upper rudder body, and a top pin, a pressure spring and a base which are arranged in a top pin hole of the lower rudder body; the base is provided with a shearing screw rod, and the shearing screw rod penetrates through the pressure spring and the ejector pin and then is in threaded connection with the nut, so that the pressure spring is in a pressed state; the upper rudder body impacts the nut when rotating, the shearing screw rod is cut off through the nut, and then the ejector pin is ejected in the pin hole of the upper rudder body under the action of the pressure spring.

2. The locking mechanism of claim 1, wherein: the lower rudder body is provided with a hinged shaft, and the upper rudder body is hinged with the lower rudder body through the hinged shaft; the upper end surface of the lower rudder body is a concave cambered surface, and the concave cambered surface takes the axis of a hinged shaft as a rotation axis.

3. The locking mechanism of claim 1, wherein: the lower rudder body is provided with a strip hole; the knock pin detachably is connected with the driving lever, and the driving lever can outwards run through the strip hole and can move up and down in the strip hole.

4. The locking mechanism of claim 3, wherein: the top pin is provided with a radial threaded hole, and the deflector rod can be screwed in the threaded hole.

5. The locking mechanism of claim 3, wherein: and a circumferential ring groove is formed in the top pin, and the deflector rod can be inserted into the circumferential ring groove.

6. The locking mechanism of claim 1, wherein: the reducing part of the shearing screw rod is positioned at the opening part of the top pin hole.