CN111232187B

CN111232187B - Wing spar connecting joint with locking function

Info

Publication number: CN111232187B
Application number: CN201911140667.0A
Authority: CN
Inventors: 许铠通; 李盛; 刘青; 周子鸣; 李康伟; 黄晓龙; 张达; 邬华明
Original assignee: Hubei Institute Of Aerospacecraft
Current assignee: Hubei Institute Of Aerospacecraft
Priority date: 2019-11-20
Filing date: 2019-11-20
Publication date: 2021-06-08
Anticipated expiration: 2039-11-20
Also published as: CN111232187A

Abstract

This patent provides a spar attach fitting with locking function. The wing beam locking device comprises a fixed section wing beam supporting seat, a movable section wing beam supporting seat, a locking pipe clamp, a locking rotating rod, a locking rocker and a rocker locking component. The wing beam supporting seats are respectively arranged in the fixed section wing and the movable section wing, and the main wing beam and the auxiliary wing beam are fixedly connected with the wing beam supporting seats in the fixed section wing; a wing beam supporting seat in the movable section wing is provided with a locking pipe clamp, and a rocker locking component is arranged on a wing beam supporting seat in the fixed section; the locking swivel is arranged on the locking pipe clamp and the locking rocker is arranged on the locking swivel. The locking rocker is rotated to drive the locking rotating rod, so that the locking pipe clamp can be tightly pressed and locked, and the movable section and the fixed section of the wing are locked and fastened. After the locking rocker is locked, the locking rotating rod can be prevented from loosening and rotating during flying, and the movable section wing and the fixed section wing can be firmly locked. The unmanned aerial vehicle has the advantages of light weight, small volume, high connection speed, simplicity in operation, reliability in connection and small influence on the flight performance of the unmanned aerial vehicle.

Description

Wing spar connecting joint with locking function

Technical Field

The invention belongs to the technical field of mechanical design and aircrafts, and particularly relates to a mechanism for quickly connecting and detaching wing sections of a small unmanned aerial vehicle.

Background

In recent years, various unmanned aerial vehicles, especially small unmanned aerial vehicles, are rapidly developed in civilian directions. However, most unmanned aerial vehicles have large wingspans, and if the unmanned aerial vehicles are integrally boxed and transported, the unmanned aerial vehicles occupy very much and waste space, and the transportation and carrying of the unmanned aerial vehicles are affected, so that the unmanned aerial vehicles need to be transported in sections and assembled on a flying site. The wing component is one of the most important components on the unmanned aerial vehicle, and directly influences the flight performance of the unmanned aerial vehicle. The problem that installation time is long exists in current wing panel connection technology, has influenced the speed of unmanned aerial vehicle flight scene equipment.

Disclosure of Invention

The invention aims to provide a mechanism for quickly disassembling and assembling wing sections of a small unmanned aerial vehicle, which is used for solving the problem that the existing small unmanned aerial vehicle is inconvenient to assemble and disassemble on site.

In order to achieve the purpose, the invention provides the following technical scheme:

the utility model provides a mechanism of unmanned aerial vehicle wing panel quick assembly disassembly, is including settling the fixed section wing spar supporting seat and the activity section wing spar supporting seat in the wing panel, locking pipe clamp, locking bull stick, locking rocker and rocker hasp subassembly. The two wing beam supporting seats (a fixed section wing beam supporting seat and a movable section wing beam supporting seat) are respectively arranged in a fixed section wing and a movable section wing, and a main wing beam and an auxiliary wing beam are fixedly connected with wing beam supporting seats in the fixed section wing; a wing beam supporting seat in the movable section wing is provided with a locking pipe clamp, and the locking rotating rod is arranged in a through hole and a right-hand thread through hole in the locking pipe clamp; the rocker locking assembly is arranged on the fixed section spar supporting seat; the locking rocker is arranged on the locking rotating rod, one end of the locking rocker is provided with a raised head matched with the rocker locking assembly, and the other end of the locking rocker is in rotating fit with the locking rotating rod;

circular through holes which are matched and connected with the main wing beam and the auxiliary wing beam are arranged on the fixed section wing beam supporting seat and the movable section wing beam supporting seat, wherein the fixed section wing beam supporting seat is fixedly connected with the main wing beam and the auxiliary wing beam;

the rocker locking component consists of a locking support, a locking rocker, a locking roller, a roller fulcrum, a rocker fulcrum and a torsion spring;

the locking rotating rod is connected with the locking pipe clamp in a threaded fit mode, the locking rocker is connected with the locking rotating rod through a pin shaft, and the locking rocker and the locking rotating rod can rotate relatively around the pin shaft;

the locking rotating rod is provided with a raised head used for being matched with the rocker locking assembly in a locking way and a small handle which is convenient for rotating the locking rocker by hand in a flying field;

as a preferred technical scheme of the invention, the metal parts of various mechanisms in the joint are made of aluminum alloy;

as the preferred technical scheme of the invention, the locking pipe clamp is fixedly connected with the movable spar supporting seat through a screw;

as a preferred technical scheme of the invention, the rocker locking assembly is fixedly connected with the fixed spar supporting seat through a screw.

The invention has the following advantages:

the invention can provide a method for disassembling and assembling the unmanned aerial vehicle in blocks, solves the problems of transportation space waste and inconvenience in carrying and transportation of the existing unmanned aerial vehicle during integral transportation, and can realize quick disassembly and assembly of the unmanned aerial vehicle on a flight site and improve the assembly efficiency of the unmanned aerial vehicle. Spar attach fitting quality is light, and is small, easy operation, connect reliably, and is less to unmanned aerial vehicle flight performance's influence simultaneously.

Drawings

FIG. 1 is a general schematic view of a spar joint in a locked condition; in the figure, 1 is a fixed section wing beam supporting seat, 2 is a movable section wing beam supporting seat, 3 is a locking pipe clamp, 4 is a locking rotating rod, 5 is a locking rocker, and 6 is a rocker locking assembly.

FIG. 2 is a schematic view of a fixed section spar support and a movable section spar support base;

FIG. 3 is a schematic view of the locking tube clamp;

FIG. 4 is a schematic view of the locking pipe clamp, locking swivel and locking rocker installation;

FIG. 5 is a schematic view of the locking pipe clamp, locking swivel and locking rocker mounted from another perspective;

FIG. 6 is a schematic view of the rocker latch assembly;

FIG. 7 is a general schematic view of a connection joint of the spar in a loosened state.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments.

The embodiment of the invention is shown in figure 1 and mainly comprises a fixed section wing beam supporting seat 1 and a movable section wing beam supporting seat 2 which are arranged in a wing section, a locking pipe clamp 3, a locking rotating rod 4, a locking rocker 5 and a rocker locking assembly 6.

As shown in fig. 2, the fixed-section spar support base 1 is provided with a connecting hole 12 for connecting with a main spar, a connecting hole 11 for connecting with an auxiliary spar, a lightening hole 13 for lightening weight, a threaded through hole 14 for connecting with a fixed-section wing and a threaded through hole 15 for connecting with the rocker latch assembly 6. As shown in figure 1, the main wing beam and the auxiliary wing beam connected with the fixed section wing beam supporting seat 1 are in a circular tube shape.

As shown in fig. 2, the movable spar support base 2 is provided with a connection hole 22 connected with the main spar, a connection hole 21 connected with the auxiliary spar, and the movable spar support base 2 is provided with a lightening hole 23 for lightening, a threaded through hole 24 for connecting with the movable spar, and a threaded through hole 25 for connecting with the locking pipe clamp 3.

The two tubular spars penetrate through the connecting

holes

11 and 12 on the fixed section spar supporting seat 1 and extend for a certain length so as to be matched and connected with the movable section spar supporting seat 2. After the two spars penetrate through the connecting

holes

11 and 12 on the fixed section spar supporting seat 1, the two spars are bonded and fixedly connected with the fixed section spar supporting seat 1 in an adhesive mode.

As shown in fig. 3, the locking pipe clamp 3 is provided with a through hole 31, a right-handed threaded through hole 32 and a threaded through hole 33, a middle slotted round hole 34 is used for passing through the main spar, the diameter of the middle slotted round hole is slightly larger than the outer diameter of the main spar, and as shown in fig. 5, the locking pipe clamp 3 is fixedly connected with the movable section spar support base 2 through an inner hexagon screw 35.

As shown in fig. 4, the bottom end of the locking rotary rod 4 is provided with a right-hand thread, which is screwed into the threaded through hole 32 at the bottom of the locking pipe clamp 3. The locking rocker 5 is connected with the locking rotating rod 4 through a pin shaft, the locking rocker 5 and the locking rotating rod 4 can rotate relatively around the pin shaft, the locking rocker 5 rotates clockwise (as shown in figure 7) through holding a small handle 52 on the locking rocker 5 by hand to drive the locking rotating rod 4 to rotate, and due to the effect of a thread pair between the locking rotating rod 4 and the locking pipe clamp 3, an inter-shaft 41 on the locking rotating rod 4 can enable the locking pipe clamp 3 to compress and deform, so that a main wing beam is clamped and fixed, at the moment, the fixed section wing beam supporting seat 1 and the movable section wing beam supporting seat 2 are fixedly connected together through the main wing beam, and further the fixed connection between the movable section wing and the fixed section wing is realized.

As shown in fig. 6, the rocker latch assembly 6 is composed of a latch holder 61, a latch rocker 62, a latch roller 63, a roller fulcrum 64, a rocker fulcrum 65, and a torsion spring 66. The rocker locking component 6 is fixedly connected with the fixed section wing beam supporting seat 1 through an inner hexagon screw. The torsion spring 66 can bring the 2 latch roller pivots 64 of the 2 latch rocker arms 62 closer together, so that the 2 latch rollers 63 of the rocker latch assembly 6 are held together in an unstressed condition. The roller fulcrum 64 may be a nylon material.

As shown in fig. 1, after the movable wing section and the fixed wing section are clamped and fixedly connected, the locking rocker 5 can be broken downwards, so that the raised head 51 on the locking rocker 5 is buckled into the lock catch assembly 6 (i.e., the raised head 51 is buckled into the middle of the 2 lock catch rollers 63), and thus the locking rocker 5 is locked, and the locking rocker 5 is prevented from swinging back and forth when the unmanned aerial vehicle flies, so that the joint is loosened or the flight performance of the unmanned aerial vehicle is influenced. Meanwhile, if the locking rocker 5 cannot be conveniently buckled into the lock catch assembly 6, the fixed positions of the movable section wing and the fixed section wing are not proper, the locking pipe clamp 3 needs to be loosened, and the movable section wing is fixed again after the position of the movable section wing is adjusted again.

As shown in fig. 7, when the movable wing needs to be detached, the locking pipe clamp 3 can be loosened by buckling the locking rocker 5 and reversely rotating the locking rocker 5, so that the movable wing can be conveniently detached.

Claims

1. A wing spar connecting joint with a locking function comprises a fixed section wing spar supporting seat, a movable section wing spar supporting seat, a locking pipe clamp, a locking rotating rod, a locking rocker and a rocker locking assembly, wherein the fixed section wing spar supporting seat and the movable section wing spar supporting seat are arranged in a wing of a fixed section, the locking rotating rod, the locking rocker and the rocker locking assembly; the locking pipe clamp is arranged on the movable section wing beam supporting seat, and the rocker locking assembly arranged on the fixed section wing beam supporting seat can be matched with the locking rocker arranged on the locking rotating rod on the locking pipe clamp arranged on the movable section wing beam supporting seat.

2. A spar attachment joint with locking as claimed in claim 1 wherein a locking clamp is located on the movable section spar support, the rocker latch assembly is located on the fixed section spar support, and the locking turn bar is located in a through hole in the locking clamp and a right hand threaded through hole.

3. A spar joint according to claim 1 having a locking function, wherein a locking rocker is arranged on said locking beam, the locking rocker being provided with a nose at one end for cooperation with a rocker latch assembly and being rotatably engaged with the locking beam at the other end.

4. A spar joint according to claim 1 or 2 or 3 with locking wherein the rocker latch assembly consists of a latch abutment, a latch rocker, a latch roller, a roller fulcrum, a rocker fulcrum, and a torsion spring; the rocker locking component is fixedly connected with the fixed section wing beam supporting seat.

5. A spar joint according to claim 1 wherein the fixed spar support blocks and the movable spar support blocks are provided with circular through holes for mating connection with the main and auxiliary spars, wherein the fixed spar support blocks are fixedly connected to the main and auxiliary spars.

6. A spar joint according to claim 1, 2 or 3, wherein the locking swivel is in screw-fit connection with a locking pipe clamp, and the locking rocker is in pin connection with the locking swivel.

7. A spar joint according to claim 1 having a locking function, wherein lightening holes are provided in the fixed spar support and the movable spar support for lightening.

8. A spar attachment joint according to claim 1 or 2, wherein the locking pipe clamp is arranged by means of screws on the movable section spar support foot.

9. A spar joint according to claim 1 wherein the rocker latch assembly is fixedly attached to the fixed section spar support base by means of socket head cap screws.