CN217805238U

CN217805238U - Wing unlocking mechanism

Info

Publication number: CN217805238U
Application number: CN202221506006.2U
Authority: CN
Inventors: 张莹; 张科; 张晓攀; 赵志孝; 王鹏; 马琪; 沈洋; 严飞
Original assignee: Xian Lingkong Electronic Technology Co Ltd
Current assignee: Xian Lingkong Electronic Technology Co Ltd
Priority date: 2022-06-16
Filing date: 2022-06-16
Publication date: 2022-11-15
Anticipated expiration: 2032-06-16

Abstract

The utility model discloses a wing unlocking mechanism, which comprises a body end face, wherein the body end face is connected with a fairway disc parallel to the body end face, the fairway disc is connected with the body end face through a shaft, the wing unlocking mechanism also comprises an upper wing assembly and a lower wing assembly which are sequentially sleeved on the shaft of the fairway disc, the upper wing assembly and the lower wing assembly are movably connected with the shaft, the shaft is also sleeved with a torsional spring, and two ends of the torsional spring are respectively connected with the upper wing assembly and the lower wing assembly; spring plungers are respectively arranged on the upper end surface of the upper wing assembly and the end surface of the fuselage, and holes matched with the spring plungers are respectively arranged on the lane disk and the lower wing assembly; the utility model discloses regard as the locking mechanical system after controlling the wing expansion with lane dish and mature product spring plunger, simple structure is reliable, and is small, and easily replacement, unblock are simple, guarantee that the aircraft retrieves back quick folding wing, accomplish the recovery of aircraft.

Description

Wing unlocking mechanism

Technical Field

The utility model belongs to the technical field of the folding wing locking mechanical system of aircraft, a wing span locking mechanical system is unblanked is related to.

Background

In recent years, the technology of the aircraft is rapidly developed, and the aircraft is widely applied to various industries and fields, particularly the military field. Different from a conventional aircraft, compared with other fixed-wing aircraft, a barrel type missile-borne folding wing aircraft has many advantages, such as small volume, light weight, convenience in transportation and carrying, and various launching platforms, while the most critical technology of the barrel type missile-borne aircraft is a wing folding and unfolding mechanism, and the folding mechanism needs to be reliably and rapidly unfolded after being taken out of a barrel and can be reliably locked after being unfolded; most of the existing aircraft folding wings and unfolding locking mechanisms are not designed with end face bearings, locking mechanisms and buffering mechanisms, so that the problems that the unfolding speed of the wings is greatly influenced when the existing aircraft folding wings are unfolded, the wings are not stable after being unfolded due to unreliable locking, and the wings are damaged due to the fact that the unfolding speed is high and no buffering mechanism exists are caused.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing a wing locking mechanical system that unlocks has solved the background art current aircraft folding wing and the problem that expandes locking mechanical system exists.

The technical scheme adopted by the utility model is that the wing locking mechanism comprises a machine body end surface and a lane disc, wherein a lane disc shaft extends into a groove arranged on the machine body end surface; the aircraft wing assembly comprises a spherical track disc shaft, an upper wing assembly and a lower wing assembly, wherein the spherical track disc shaft is sleeved with the upper wing assembly and the lower wing assembly; and a torsion spring is arranged on the ball way disc shaft, and a spring plunger and a thrust bearing are respectively arranged on the upper end surface of the upper wing component and the end surface of the machine body.

The utility model discloses a characteristics still lie in:

the end face of the machine body is parallel to the surface of the fairway disc, and the fairway disc shaft extends into the groove of the end face of the machine body and then is fixedly connected with the groove through a bolt;

wherein, two ends of the torsion spring are respectively connected with the upper wing component and the lower wing component; holes matched with the spring plungers are respectively formed in the fairway disc and the lower wing assembly;

wherein, the ball path disc and the lower wing component are respectively provided with a ball path disc waist-shaped groove and a lower end surface waist-shaped groove along the displacement track of the spring plunger, and the holes are respectively positioned in the ball path disc waist-shaped groove and the lower end surface waist-shaped groove of the lower wing component;

wherein, one end of the upper wing component and one end of the lower wing component are respectively provided with a rotating shaft, the upper wing component and the lower wing component are movably sleeved on a shaft of the ball way disc through the rotating shafts, and the sleeved parts of the upper wing component and the lower wing component and the shaft are also provided with deep groove ball bearings;

one side of the rotating shaft of the upper wing assembly, which is close to the ball way disc, is provided with a thrust bearing parallel to the rotating shaft, and one side of the rotating shaft of the lower wing assembly, which is close to the end face of the fuselage, is provided with a thrust bearing sleeved on the shaft of the ball way disc;

the torsion spring is positioned between the upper wing assembly and the lower wing assembly, grooves are formed in the upper wing assembly and the lower wing assembly, the torsion spring is positioned in the grooves, and mounting holes connected with two ends of the torsion spring are respectively formed in the grooves of the upper wing assembly and the lower wing assembly;

wherein, one side of the upper wing component close to the lower wing component is provided with a boss, and the surface of the lower wing component is provided with an arc-shaped groove embedded with the boss along the displacement track of the boss;

wherein, one side of the ball way disc positioned on the shaft is also connected with a limit buffer column parallel to the shaft, and the joints of the lower wing assembly and the upper wing assembly with the shaft are also respectively provided with a stop dog matched with the limit buffer column.

The utility model has the advantages that:

the wing span unlocking mechanism of the utility model drives the left wing and the right wing to be unfolded simultaneously by the torsion spring of the central arm, and the torsion spring torsion arms are respectively assembled with the mounting holes on the left wing and the right wing, so that the wing span unlocking mechanism is simple and reliable to mount and has small dependence on the environment; the fairway disc and the mature product spring plunger are used as locking mechanisms after the left wing and the right wing are unfolded, the structure is simple and reliable, the size is small, the replacement is easy, the unlocking is simple, the wings can be folded quickly after the aircraft is recovered, and the recovery of the aircraft is finished; the thrust bearing and the deep groove ball bearing which are mature products are used for reducing the frictional resistance in the wing unfolding process, and the rapidity and the synchronism in the wing unfolding process are ensured; the whole wing unfolding and locking mechanism is high in integration level, simple in mechanism, small in size and simple in assembly, and the requirements of a telescopic aircraft on folding wings are met by adopting mature component products.

Drawings

Fig. 1 is a schematic view of a wing spreading structure in a wing spreading unlocking mechanism of the present invention;

FIG. 2 is a cross-sectional view of a wing span lock locking mechanism of the present invention;

fig. 3 is a schematic structural view of a lower wing assembly in a wing span unlocking mechanism of the present invention.

In the figure, 1, an upper wing assembly, 2, a lower wing assembly, 3, a ball way disc, 4, a limiting buffer column, 5, a spring plunger, 6, a stop dog, 7, a hole in a waist-shaped groove on the lower end surface of the lower wing assembly, 8, a hole in a waist-shaped groove of the ball way disc, 9, a torsion spring, 10, a thrust bearing, 11, a deep groove ball bearing, 12, a machine body end surface, 13, a waist-shaped groove of the ball way disc, 14, a waist-shaped groove on the lower end surface of the lower wing assembly, 15, a boss, 16, an upper wing torsion spring mounting hole position and 17, and the upper wing assembly spring plunger is mounted.

Detailed Description

The present invention will be described in detail with reference to the accompanying drawings and specific embodiments.

The utility model provides a locomotive span locking mechanism, as shown in figure 1 and figure 2, including last wing subassembly 1, lower wing subassembly 2, lane dish 3, spacing buffering post 4, torsional spring 9, thrust bearing 10, deep groove ball bearing 11, spring plunger 5, specifically include following several parts:

1. designing a wing unfolding mechanism:

the folding wing comprises an upper wing component 1 and a lower wing component 2, a fairway disc 3 is connected to a fuselage end face 12 through a shaft, the fairway disc 3 is parallel to the fuselage end face 12, the shaft is perpendicular to the fairway disc 3, the upper wing component 1 and the lower wing component 2 are respectively sleeved on the shaft, the lower wing component 2 is arranged close to the fuselage end face 12, the upper wing component 1 is arranged close to the fairway disc 3, one side of the lower wing component 2 close to the fuselage end face 12 and one side of the upper wing component 1 close to the fairway disc 3 are respectively provided with a thrust bearing 10, the thrust bearings 10 are sleeved on the shaft of the fairway disc 3, a torsion spring 9 is arranged in grooves of the upper wing component 1 and the lower wing component 2, mounting holes of the torsion spring 9 are arranged in the grooves, one end of the torsion spring 9 is arranged in the mounting hole in the groove of the upper wing component 1, the other end of the torsion spring 9 is arranged in the mounting hole in the groove of the lower wing component 2, and the torsion spring 9 is completely arranged in the two grooves after combination; one part of the rotating shaft of the left wing and the right wing is connected with the shaft on the lane disc 3 through a deep groove ball bearing 11; the wing unfolding mechanism is simple and reliable in design structure, and the problem that the wing unfolding process is slow due to large friction force in the unfolding process of the unfolding mechanism is solved;

a boss 15 is further arranged on one end face, attached to the lower wing assembly 2, of the upper wing assembly 1, an arc-shaped groove is formed in the end face, close to the upper wing assembly 1, of the lower wing assembly 2, the boss 15 is embedded in the arc-shaped groove, and the arc-shaped groove can play a guiding role in the process of wing spreading and closing;

as shown in fig. 3, taking the structure of the upper wing assembly 1 as an example, one end of the upper wing assembly 1 is provided with a rotating shaft, a deep groove ball bearing 11 is embedded in the rotating shaft, an upper wing torsion spring mounting hole site 16 connected with the end of the torsion spring 9 is arranged on the upper wing assembly 1, and an upper wing assembly spring plunger mounting site 17 for mounting the spring plunger 5 is reserved on the end surface of the upper wing assembly 1;

2. designing a buffer mechanism:

the limiting buffer column 4 is perpendicular to the end faces of the machine body, the fairway disc 3 and the upper and lower wing components, when the upper and lower wings are unfolded in place, the stop blocks 6 on the upper and lower wings are blocked by the limiting buffer column 4, and the rubber ring sleeved on the limiting buffer column 4 plays a buffer role;

3. the design of a locking mechanism:

the wing unfolding locking mechanism further comprises spring plungers 5, one spring plunger 5 is used on the upper end face of the upper wing assembly 1 and is fixed at an upper wing assembly spring plunger mounting position 17 of the upper end face of the upper wing assembly 1 through a threaded hole, and the other spring plunger 5 is used on a fuselage end face 12 and is fixed on the fuselage end face 12 through a threaded hole; a fairway disc waist-shaped groove 13 on the fairway disc 3 presses the round head part of the spring plunger 5 on the upper end surface of the upper wing assembly 1, so that the spring plunger 5 is in a compressed state, when the wings are unfolded in place, the spring plunger 5 enters a hole 8 on the fairway disc waist-shaped groove, and the unfolded upper wing assembly 1 is locked; the lower end surface waist-shaped groove 14 of the lower wing component presses the round head part of the spring plunger 5 on the end surface 12 of the fuselage to enable the spring plunger 5 to be in a compressed state, when the wing is unfolded in place, the spring plunger 5 on the end surface 12 of the fuselage enters the hole 7 on the lower end surface waist-shaped groove of the lower wing component, and the lower wing component 2 which is unfolded in place is locked; the fairway disc waist-shaped groove 13 and the lower end face waist-shaped groove 14 of the lower wing component are both grooves formed along the displacement track of the spring plunger 5 in the motion process of the wing, and the locking mechanism is replaceable and low in replacement cost.

Claims

1. A wing span unlocking mechanism comprises a machine body end surface (12) and a fairway disc (3), and is characterized in that a shaft of the fairway disc (3) extends into a groove arranged on the machine body end surface (12); the aircraft wing assembly comprises a fairway disc (3) and is characterized by further comprising an upper wing assembly (1) and a lower wing assembly (2) which are sequentially sleeved on a fairway disc (3) shaft, wherein the upper wing assembly (1) and the lower wing assembly (2) are movably connected with the fairway disc (3) shaft; the shaft of the lane plate (3) is provided with a torsion spring (9), and the upper end surface of the upper wing component (1) and the machine body end surface (12) are respectively provided with a spring plunger (5) and a thrust bearing (10).

2. The wing span unlocking mechanism of claim 1, wherein the fuselage end face (12) is parallel to the surface of the fairway disc (3), and the shaft of the fairway disc (3) is fixedly connected with the fuselage end face (12) through a bolt after extending into a groove of the fuselage end face.

3. The wing span unlocking mechanism of claim 2, wherein both ends of the torsion spring (9) are respectively connected to the upper wing component (1) and the lower wing component (2); holes matched with the spring plungers (5) are respectively formed in the lane disc (3) and the lower wing assembly (2).

4. The wingspan unlocking mechanism according to claim 3, characterized in that a fairway disc kidney-shaped groove (13) and a lower wing component lower end face kidney-shaped groove (14) are respectively formed in the fairway disc (3) and the lower wing component (2) along the displacement track of the spring plunger (5), and the holes are respectively positioned in the fairway disc kidney-shaped groove (13) and the lower wing component lower end face kidney-shaped groove (14).

5. The wing span unlocking mechanism of the airplane according to claim 1, characterized in that one end of the upper wing component (1) and one end of the lower wing component (2) are respectively provided with a rotating shaft, the upper wing component (1) and the lower wing component (2) are movably sleeved on a shaft of the fairway disc (3) through the rotating shafts, and the sleeved parts of the upper wing component (1) and the lower wing component (2) and the shaft are further provided with deep groove ball bearings (11).

6. The wing span unlocking mechanism of the aircraft according to claim 5, characterized in that a thrust bearing (10) parallel to the rotating shaft is arranged on one side of the rotating shaft of the upper wing component (1) close to the fairway disc (3), and a thrust bearing (10) sleeved on the shaft of the fairway disc (3) is arranged on one side of the rotating shaft of the lower wing component (2) close to the end face (12) of the aircraft body.

7. The wing span unlocking mechanism of claim 3, wherein the torsion spring (9) is located between the upper wing component (1) and the lower wing component (2), the upper wing component (1) and the lower wing component (2) are both provided with a groove, the torsion spring (9) is located in the groove, and the grooves of the upper wing component (1) and the lower wing component (2) are respectively provided with a mounting hole connected with two ends of the torsion spring (9).

8. The wing span unlocking mechanism of claim 1, wherein a boss (15) is arranged on one side of the upper wing assembly (1) close to the lower wing assembly (2), and an arc-shaped groove embedded with the boss (15) is formed in the surface of the lower wing assembly (2) along the displacement track of the boss (15).

9. The wing span unlocking mechanism of the aircraft according to claim 1, wherein one side of the fairway disc (3) on the shaft is further connected with a limit buffer column (4) parallel to the shaft, and the joints of the lower wing component (2) and the upper wing component (1) with the shaft are further respectively provided with a stop (6) matched with the limit buffer column (4).