CN211223838U

CN211223838U - Folding wing mechanism

Info

Publication number: CN211223838U
Application number: CN201921807999.5U
Authority: CN
Inventors: 赵昕亮; 李永泽; 钱立新; 卢永刚
Original assignee: General Engineering Research Institute China Academy of Engineering Physics
Current assignee: General Engineering Research Institute China Academy of Engineering Physics
Priority date: 2019-10-25
Filing date: 2019-10-25
Publication date: 2020-08-11
Anticipated expiration: 2029-10-25

Abstract

The utility model discloses a folding wing mechanism, which comprises a folding wing and a folding mechanism for providing power for the unfolding of the folding wing and limiting the unfolding; the folding mechanism comprises a limiting buffer column; the folding wings are blocked by the limiting buffer posts when being unfolded to the maximum limit. The utility model drives the upper and lower wings to be unfolded simultaneously by a central arm torsional spring, and the torsion arms are respectively assembled with the torsional spring mounting holes on the wing roots of the upper and lower wings, so that the installation is simple and reliable, and the dependence on the environment is small; the locking pin assembly is used as a locking mechanism after the wing surface is opened, the structure is simple, the size is small, the reliability is high, the replacement is easy, the unlocking is simple, the wings can be quickly folded after the unmanned aerial vehicle is recovered, and the recovery of the unmanned aerial vehicle is finished; the needle roller end surface bearing which is a mature product is used for friction drag reduction, so that the friction drag in the opening process is reduced, and the rapidity and the synchronism in the opening process are ensured; the whole folding mechanism is high in integration level, simple in mechanism, small in size, simple to assemble and easy and convenient to operate, and meets the requirement of the cylinder type launching unmanned aerial vehicle on the folding wings.

Description

Folding wing mechanism

Technical Field

The utility model belongs to the technical field of the aircraft, concretely relates to folding wing mechanism.

Background

The cylinder type launching folding wing unmanned aerial vehicle belongs to the technical field of aircrafts, is small in size, can be carried by an individual soldier, can enter a combat area quickly, is high in control performance with advantages such as flexible tactics and the like, and is suitable for anti-terrorism and urban wars.

The prior individual patrol missile of the American army adopts a cylindrical launching folding wing unmanned aerial vehicle scheme, wherein the total weight of the cylindrical missile is less than 3kg in a 'spring knife' series, the carrying capacity of the missile is about 320g, the killing power is small, and mainly comprises hitting personnel and unarmored vehicles. The mature product in the short-range round fly ammunition of the Israel hero series is hero 30, the power of the product is equivalent to that of a spring knife, and a cylindrical launching folding unmanned aerial vehicle scheme is also adopted.

The CH-901 series of flying missiles which have finished military and trade export projects in China also adopt a cylindrical launching folding unmanned aerial vehicle scheme. The total weight of the medium-sized patrol flying cartridge is 9kg and 6kg, the predicted warhead is less than 1kg, the simple armor protection vehicle is mainly hit, the light patrol flying cartridge is 3kg, the reconnaissance is mainly used, the power prediction of the carried warhead is equivalent to that of a spring knife, and the attacking personnel and the unarmored vehicle are mainly used.

One of the key technologies of the drum type launch drone is the folding wing: the wing surface part of the folding wing is required to have high rigidity and light weight, and has small deformation under the action of flight load; the folding wing root part is required to be light in material weight, good in machining performance and high in strength, and can bear impact force in the movement process of the unfolding locking mechanism; the airfoil portion and the root portion are required to be securely bonded and fixed.

One of the key technologies of the drum launch drone is to deploy a locking mechanism: the folding wings need to be reliably, rapidly and synchronously unfolded under the action of an unfolding and locking mechanism after being taken out of the cylinder, and are reliably locked after being unfolded in place; the unfolding locking mechanism is required to have small installation clearance, high assembly rigidity and small friction resistance between moving interfaces.

Most of folding wings and unfolding locking mechanisms of existing unmanned aerial vehicles are not provided with end face bearings, locking mechanisms and buffering mechanisms. Some folding wings are complex in design and do not balance the relationship between rigidity and weight; in order to improve the assembly rigidity of the wings, some unfolding mechanisms generally adopt larger installation pretightening force, so that the sliding friction resistance is larger in the unfolding process of the wings, and the unfolding process of the wings is slow and asynchronous; some locking mechanisms have complex structures and are unreliable in locking, or wings have large shaking amount after locking, so that the flight is unstable; some locking mechanisms are not replaceable or are costly to replace.

To solve the above problems, the folding wing mechanism has been developed by the present inventor.

Disclosure of Invention

The present invention is directed to provide a folding wing mechanism to solve the above problems.

The utility model discloses a following technical scheme realizes above-mentioned purpose:

the folding wing mechanism comprises a folding wing and a folding mechanism which is used for providing power for the unfolding of the folding wing and limiting the unfolding.

Specifically, the folding mechanism includes:

limiting the buffer column; the folding wings are blocked by the limiting buffer posts when being unfolded to the maximum limit.

The limiting buffer column is vertically arranged on the aircraft body and is vertical to the folding wings.

Specifically, the folding mechanism includes:

a torsion spring; the folding wing includes wing assembly and lower wing assembly, overlaps from top to bottom with the first end of wing assembly down for the first end of wing assembly, and the torsional spring setting is between the first end of wing assembly and the first end of wing assembly down on the wing assembly.

Specifically, grooves capable of containing a part of torsion springs are formed in the first end of the upper wing assembly and the first end of the lower wing assembly, torsion spring mounting holes are formed in the grooves, one end of each torsion spring is arranged in the corresponding torsion spring mounting hole of the upper wing assembly, and the other end of each torsion spring is arranged in the corresponding torsion spring mounting hole of the lower wing assembly; the two grooves are combined for placing the torsion spring into the whole body.

Specifically, the folding mechanism includes:

and the limiting assembly is used for limiting the rotation center lines of the upper wing assembly and the lower wing assembly.

Specifically, spacing subassembly includes a gag lever post, at the equal vertical through-hole that is provided with of the first end of last wing subassembly and the first end of wing subassembly down, and the one end of gag lever post is fixed on the organism, and the through-hole that the gag lever post passed on the wing subassembly sets up with the through-hole on the wing subassembly down.

Specifically, the folding mechanism comprises an upper cover used for limiting the upper wing component and the lower wing component to be incapable of moving along the vertical direction, and the upper cover covers the upper portion of the first end of the upper wing component and is fixed on the limiting buffer column.

Specifically, the upper cover and the upper wing assembly, and the upper wing assembly and the lower wing assembly are connected through needle roller end face bearings.

Specifically, the folding wing mechanism further comprises a lock pin assembly, the lock pin assembly is used for locking the relative positions of the machine body, the upper wing assembly and the lower wing assembly after the upper wing assembly and the lower wing assembly are unfolded to the absolute position, and locking the relative positions of the machine body, the upper wing assembly and the lower wing assembly after the upper wing assembly and the lower wing assembly are folded.

The beneficial effects of the utility model reside in that:

the utility model discloses a folding wing mechanism:

1. the upper wing and the lower wing are driven to be unfolded simultaneously by a central arm torsion spring, and the torsion arms are respectively assembled with the torsion spring mounting holes on the wing roots of the upper wing and the lower wing, so that the installation is simple and reliable, and the dependence on the environment is small;

2. the locking pin assembly is used as a locking mechanism after the wing surface is opened, the structure is simple, the size is small, the reliability is high, the replacement is easy, the unlocking is simple, the wings can be quickly folded after the unmanned aerial vehicle is recovered, and the recovery of the unmanned aerial vehicle is finished;

3. the needle roller end surface bearing of a mature product is used for friction drag reduction, so that the friction resistance in the opening process is reduced, and the rapidity and the synchronism in the opening process are ensured.

4. Whole folding mechanism integrated level is high, and the mechanism is simple and small, the assembly is simple and easy and simple to handle, adopts ripe subassembly product more, accords with the demand of cylinder transmission unmanned aerial vehicle to folding wing.

Drawings

FIG. 1 is an axial side view of the folded wing mechanism of the present application in an unfolded state;

FIG. 2 is a side view of the folding wing mechanism of the present application in a contracted state;

FIG. 3 is an isometric view of a lower wing assembly of the present application;

FIG. 4 is a cross-sectional view of the folding mechanism of the present application;

FIG. 5 is a rotary cross-sectional view of the folding mechanism of the present application;

FIG. 6 is a schematic structural view of a locking pin assembly of the present application, wherein a is a cross-sectional view and b is a bottom view;

FIG. 7 is a schematic view of the construction of a needle end bearing of the present application;

FIG. 8 is a schematic structural view of a torsion spring of the present application;

fig. 9 is a schematic view of a connection structure of the limiting buffer column, the upper cover and the folding wing mounting base in the present application.

In the figure: 1. the structure of the novel airplane comprises an airplane body, 2, a limiting buffer column, 3, a lock pin assembly, 4, a screw, 5, an upper wing assembly, 6, a lower wing assembly, 7, sandwich foam, 8, a carbon fiber composite material, 9, a lower wing root, 10, an upper cover, 11, an upper wing root, 12, a needle roller end surface bearing, 13, an annular steel sheet, 14, a torsion spring, 15, a folding wing mounting base, 16, a lock pin cylinder body, 17, a lock pin spring, 18, a conical head pin, 19, a lock pin hole, 20 and a torsion spring mounting hole.

Detailed Description

The present invention will be further explained with reference to the accompanying drawings:

as shown in fig. 1 to 5, the folding wing mechanism includes a folding wing, a folding mechanism for providing power for unfolding the folding wing and limiting the unfolding limit.

As shown in fig. 1, 2, 4, 9, in some embodiments, the folding mechanism comprises:

a limiting buffer column 2; the folding wings are blocked by the limiting buffer posts 2 when being unfolded to the maximum limit.

As shown in fig. 1 and 2, in some embodiments, the limit bumper 2 is vertically disposed on the body 1 of the aircraft, and the limit bumper 2 is vertical to the folding wing.

As shown in fig. 4, 5, and 8, in some embodiments, the folding mechanism comprises:

a torsion spring 14; the torsion spring 14 adopts a central arm structure, the folding wing comprises an upper wing component 5 and a lower wing component 6, the first end of the upper wing component 5 and the first end of the lower wing component 6 are overlapped up and down, and the torsion spring 14 is arranged between the first end of the upper wing component 5 and the first end of the lower wing component 6.

In some embodiments, the folding wings may be a combination of sets of upper wing assemblies 5 and lower wing assemblies 6, such as a four wing aircraft;

in this embodiment, when the folding wings are in the folded state, the torsion spring 14 is in a compressed state; the power which can fully unfold the folding wings can be provided, and the power can overcome the friction force, wind resistance and other forces on the unfolding of the folding wings; when the folding wing is completely unfolded, the torsion spring 14 can be still in a compressed state, or can just restore to a normal state, but the physical performance of the torsion spring 14 needs to ensure that the folding wing does not fold under the action of wind resistance or other small external resistance, and when the folding wing is stored, the folding wing needs to be assisted by hands or instruments;

as shown in fig. 3, 4 and 5, in some embodiments, a groove is formed in each of the first end of the upper wing assembly 5 and the first end of the lower wing assembly 6, and a torsion spring mounting hole 20 is formed in each of the grooves, one end of the torsion spring 14 is disposed in the torsion spring mounting hole 20 of the upper wing assembly 5, and the other end of the torsion spring 14 is disposed in the torsion spring mounting hole 20 of the lower wing assembly 6; the two grooves are combined for placing the torsion spring 14 in all. The grooves in this embodiment are located below the first end of the upper wing assembly 5 (upper wing root 11) and above the first end of the lower wing assembly 6 (lower wing root 9);

in some embodiments, one end of the torsion spring 14 is fixedly disposed in the torsion spring mounting hole 20 of the upper wing assembly 5, and the other end of the torsion spring 14 is fixedly disposed in the torsion spring mounting hole 20 of the lower wing assembly 6;

in some embodiments, the folding mechanism comprises:

and the limiting assemblies are used for limiting the rotation center lines of the upper wing assembly 5 and the lower wing assembly 6.

In some embodiments, the limiting component includes a limiting rod, through holes are vertically formed at the first end of the upper wing component 5 and the first end of the lower wing component 6, one end of the limiting rod is fixed on the machine body 1, and the limiting rod passes through the through holes on the upper wing component 5 and the through holes on the lower wing component 6.

As shown in fig. 1, 2, 4, 5 and 9, in some embodiments, the folding mechanism includes an upper cover 10 for limiting the upper wing assembly 5 and the lower wing assembly 6 from moving in the vertical direction, and the upper cover 10 covers the upper portion of the first end of the upper wing assembly 5 and is fixed on the limit bumper post 2.

As shown in fig. 4, 5 and 9, in some embodiments, the lower end of the middle portion of the upper cover 10 is provided with a downward convex pillar, which is hollow, and the present application further includes a folding wing mounting base 15, wherein the body 1 and the folding wing mounting base 15 are integrally formed by a composite material process, and bear load as a rigid whole; the upper end of the middle part of the folding wing installation base 15 is provided with an upward convex column which is also hollow, the convex column on the upper cover 10 and the convex column on the folding wing installation base 15 are combined to form a structure with the same function as the limiting component, and the structure passes through the through hole on the upper wing component 5 and the through hole on the lower wing component 6 to be arranged for limiting the rotation center line of the upper wing component 5 and the lower wing component 6. The arrangement of the structure reduces the arrangement of parts, so that the structure is simpler; the convex columns are preferably cylinders, so that smooth rotation of the upper wing assembly 5 and the lower wing assembly 6 can be guaranteed; the first ends of the upper wing assembly 5 and the lower wing assembly 6 are formed into 1/2 round structures, so that the normal rotation of the upper wing assembly 5 and the lower wing assembly 6 is not blocked.

As shown in fig. 1, 4 and 9, in some embodiments, the upper cover 10 is screwed to the folding wing mounting base 15 at its middle position by four screws 4; the limiting buffer column 2 also penetrates through the screw 4 from top to bottom and then is in threaded connection with the folding wing mounting base 15; the installation mode is convenient to disassemble and assemble, and parts are convenient to replace.

As shown in fig. 4 and 5, the upper cover 10 and the upper wing assembly 5, and the upper wing assembly 5 and the lower wing assembly 6 are connected by needle end bearings 12. As shown in fig. 7, a specific structure of the needle end face bearing 12 is shown;

in some embodiments, a folding wing mounting base 15 is provided, and a needle end bearing 12 is also provided between the lower wing assembly 6 and the folding wing mounting base 15.

In some embodiments, the parts of the upper wing assembly 5 and the lower wing assembly 6 connected by the needle end face bearing 12 are provided with annular steel sheets 13, which aim to strengthen the structure and avoid friction damage;

as shown in fig. 1 and 5, in some embodiments, the folding wing mechanism further includes a locking pin assembly 3, the locking pin assembly 3 is used for locking the body 1 to the upper wing assembly 5 and the lower wing assembly 6 after the upper wing assembly 5 and the lower wing assembly 6 are unfolded to the maximum position, and for locking the body 1 to the upper wing assembly 5 and the lower wing assembly 6 after the upper wing assembly 5 and the lower wing assembly 6 are folded.

As shown in fig. 6 and 5, in some embodiments, the locking pin assembly 3 includes a locking pin barrel 16, a locking pin spring 17, a conical head pin 18; the lock pin barrel 16 is formed into a structure with a hollow middle part and an opening at one end, and the lock pin spring 17 is arranged inside the lock pin barrel 16 and is clamped to be incapable of moving out of the lock pin barrel 16; the first end of the conical head pin 18 is also provided with a stepped structure, and the first end of the conical head pin 18 is clamped in the lock pin cylinder 16, so that the conical head pin 18 cannot be completely separated from the lock pin cylinder 16; the conical head pin 18 can be slidably arranged in the lock pin cylinder 16, and when the lock pin spring 17 is in a normal state, the conical head pin 18 is in the topmost limit position;

the head part of the upper end of the conical head pin 18 is designed to be 12-degree conical, so that the pin head and the lock pin hole 19 can be guaranteed to be in gapless fit, no swing exists after the wing surface is locked, and the conical head pin 18 cannot slide out of the lock pin hole 19 under the action of impact load.

As shown in fig. 5, the lower wing assembly 6 and the upper cover 10 are provided with locking pin holes 19, and the body 1 and the upper wing assembly 5 are provided with reserved mounting holes for mounting the locking pin cylinder 16; when the upper wing assembly 5 and the lower wing assembly 6 are positioned in the launching tube or in the process of expanding to the absolute position, the lock pin spring 17 is always in a compressed state, the conical head pin 18 is contracted into the lock pin tube body 16, the conical head pin 18 of the lock pin assembly 3 positioned at the lower part is contacted with the lower surface of the lower wing assembly 6, and the conical head pin 18 of the lock pin assembly 3 positioned at the upper part is contacted with the lower surface of the edge of the upper cover 10; after the upper wing assembly 5 and the lower wing assembly 6 are unfolded to the maximum position, the conical head pin 18 protrudes out of the locking pin cylinder 16 under the elastic force of the locking pin spring 17 and is respectively inserted into the locking pin hole 19 of the lower wing assembly 6 and the locking pin hole 19 of the upper cover 10.

In some embodiments, the unmanned aerial vehicle generally does not need to be recovered, but if the unmanned aerial vehicle needs to be recovered, the unmanned aerial vehicle is inserted down from the upper part of the lock pin hole 19 through a rod body, the conical head pin 18 is pushed into the lock pin cylinder 16, and the upper wing assembly 5 and the lower wing assembly 6 can be rotated to complete the folding state recovery of the wing and the recovery.

In some embodiments, the outer wall of the lock pin cylinder 16 is provided with threads, and a reserved mounting hole for mounting the lock pin cylinder 16 is cooperatively formed on both the body 1 and the upper wing assembly 5, and the reserved mounting hole is a threaded hole, and the lock pin cylinder 16 is screwed into the threaded hole for mounting.

As shown in fig. 1, 2 and 4, the limit buffer column 2 is made of soft buffer material and is used for limiting the opening angle of the airfoil and buffering and attenuating the rotation impact load of the airfoil, so as to reduce the impact load on the lock pin assembly 3.

As shown in fig. 3, the lower wing assembly 6 is shown in an axial side view, wherein a sandwich foam 7, a carbon fiber composite material 8 and a lower wing root 9 are included, wherein the sandwich foam 7 improves the rigidity of the elastic composite material, and the lower wing root 9 is made of a high-strength duralumin material. The components also comprise a sandwich foam 7, a carbon fiber composite material 8 and an upper wing root 11. The upper wing assembly 5 and the lower wing assembly 6 are integrally formed by autoclave; the foam sandwich material, the carbon fiber skin and the aluminum wing root are integrally formed, so that the light weight and good rigidity of the wing surface part are ensured. The aluminum material machine of the wing root part has good manufacturability, and a complex unfolding and locking mechanism can be designed;

as shown in fig. 2, in some embodiments, the lateral sides of the upper wing assembly 5 and the lower wing assembly 6 are provided with a blocking structure, and when the upper wing assembly 5 and the lower wing assembly 6 are unfolded to be perpendicular to the machine body 1, the blocking structure is blocked on the limiting buffer column 2, so that the upper wing assembly 5 and the lower wing assembly 6 cannot be unfolded continuously;

in other embodiments, the structure of the stop is not required, but abrasion between the upper wing assembly 5, the lower wing assembly 6 and the limit bumper 2 due to shaking may occur.

The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims

1. The folding wing mechanism comprises folding wings and is characterized by also comprising a folding mechanism and a limiting buffer column, wherein the folding mechanism is used for providing power for unfolding the folding wings and limiting the unfolding limit; when the folding wings are unfolded to the limit, the folding wings are blocked by the limit buffer posts.

2. The folding wing mechanism of claim 1, wherein the limit bumper is vertically disposed on the body of the aircraft, and the limit bumper is perpendicular to the folding wing.

3. The folding wing mechanism of claim 1, characterized in that the folding mechanism comprises:

4. The folding wing mechanism according to claim 3, wherein a groove for placing a part of the torsion spring is formed in each of the first end of the upper wing assembly and the first end of the lower wing assembly, and a torsion spring mounting hole is formed in each of the grooves, one end of the torsion spring is placed in the torsion spring mounting hole of the upper wing assembly, and the other end of the torsion spring is placed in the torsion spring mounting hole of the lower wing assembly; the two grooves are combined for placing the torsion spring into the whole body.

5. The folding wing mechanism according to any of claims 1-4, characterized in that the folding mechanism comprises:

6. The folding wing mechanism according to claim 5, wherein the limiting component comprises a limiting rod, the first end of the upper wing component and the first end of the lower wing component are vertically provided with through holes, one end of the limiting rod is fixed on the machine body, and the limiting rod passes through the through holes on the upper wing component and the through holes on the lower wing component.

7. The folding wing mechanism according to claim 6, wherein the folding mechanism includes an upper cover for limiting the upper wing assembly and the lower wing assembly from moving in a vertical direction, the upper cover covering the upper portion of the first end of the upper wing assembly and being fixed to the position-limiting buffer column.

8. The folding wing mechanism of claim 7, wherein the upper cover and the upper wing assembly, and the upper wing assembly and the lower wing assembly are connected by needle end bearings.

9. The folding wing mechanism of claim 8, further comprising a locking pin assembly for locking the body relative to the upper wing assembly and the lower wing assembly after the upper wing assembly and the lower wing assembly are unfolded to the maximum position, and locking the body relative to the upper wing assembly and the lower wing assembly after the upper wing assembly and the lower wing assembly are folded.