CN217864690U - Arm folding mechanism and aircraft - Google Patents

Abstract

The application relates to an arm folding mechanism and an aircraft. The machine arm folding mechanism comprises at least one machine arm component and a driving mechanism in transmission connection with the machine arm component; the horn subassembly includes two horns, and actuating mechanism includes driving piece and two link assembly, and the power take off end of driving piece is connected with two horns through two link assembly respectively, and the driving piece is used for driving two horns through two link assembly and folds or expand for the fuselage of aircraft. The scheme that this application provided, two horn folds simultaneously or expandes can be controlled to every driving piece, compares with the correlation technique, has simplified the structure, has reduced the quantity of driving piece, has consequently reduced the weight of aircraft, also the cost is reduced.

Description

Arm folding mechanism and aircraft

Technical Field

The application relates to the technical field of aviation, especially, relate to horn folding mechanism and aircraft.

Background

The wings of the aerocar need a large span in the flying state to meet the requirement of lift force, and when the flying state is converted into the land traveling state, in order to reduce the occupation of land area and meet related road regulations, the horn or the wings need to be folded to be close to the car body.

In the related art, in order to meet the requirement of a blade running space, a plurality of multi-rotor aircrafts are generally designed to extend a horn and a rotor out of a certain distance from an airframe, so that the aircrafts occupy a large space and cause certain difficulty in land movement or transportation; some aircrafts are manually folded, and the manual folding has certain requirements on preparation and inspection work before and after the aircrafts fly, so that the user experience is poor; some aircraft, while employing automatic folding, have the following disadvantages: 1) The number of actuators driving the wing to fold or unfold is high, which leads to the increase of the weight and cost of the aircraft and the reduction of reliability; 2) The locking mode is unreliable after the wing is unfolded, and the stability is poor; 3) The folding process is not pulled by a single actuator, so that the folding reliability is low; 3) Generally, hydraulic drive is adopted, a hydraulic system needs to be configured, and the weight, the complexity and the cost are high.

Therefore, the wing folding system of the aircraft in the related art has high structural complexity, heavy weight, and low reliability.

SUMMERY OF THE UTILITY MODEL

In order to solve or partially solve the problems existing in the related art, the application provides the arm folding mechanism, which simplifies the structure, reduces the number of driving pieces, reduces the weight of an aircraft and reduces the cost.

This application first aspect provides an arm folding mechanism, includes:

the driving mechanism is in transmission connection with the machine arm assembly;

the horn subassembly includes two horns, actuating mechanism includes driving piece and two link assembly, the power take off end of driving piece is respectively through two link assembly and two the horn is connected, the driving piece is used for through two link assembly drives two the horn is folding or is expanded for the fuselage of aircraft.

In one embodiment, the robot arm assembly further comprises a mounting frame, two arm connecting parts are arranged at the part of the mounting frame corresponding to each group of arm assemblies, and the two arms are rotatably connected to the two arm connecting parts; the driving piece drives the two machine arms to rotate relative to the mounting rack through the two connecting rod assemblies respectively;

when the machine arm rotates towards a direction far away from the mounting rack, the machine arm is in a spreading state; when the horn rotates in a direction close to the mounting bracket, the horn is in a folded state.

In one embodiment, the connecting rod assembly includes a first connecting end, a second connecting end and a driving connecting end, the first connecting end is connected with the mounting frame, the second connecting end is connected with the arm, and the driving connecting end is connected with the power output end of the driving member.

In one embodiment, the linkage assembly includes a first rod, a second rod, and a third rod;

the two opposite ends of the first rod body and the second rod body are connected, the two opposite ends of the first rod body and the second rod body are respectively arranged as the first connecting end and the second connecting end, one end of the third rod body is connected between the two ends of the first rod body, and the other end of the third rod body is arranged as the driving connecting end.

In one embodiment, the movement ranges of the first rod, the second rod and the third rod are in the same plane.

In one embodiment, when the first rod and the second rod rotate to be along the same straight line, the connecting rod assembly is in a locking state; and/or

When the third rod body rotates to the direction perpendicular to the running direction of the driving piece, the connecting rod assembly is in a locking state.

In an embodiment, the second rod body is connected with the horn through a second connecting piece, the second connecting piece is provided with an adapter, one end of the adapter is rotatably connected with the second connecting piece through a first rotating shaft, the other end of the adapter is rotatably connected with the second rod body through a second rotating shaft, and the first rotating shaft is perpendicular to the second rotating shaft.

In one embodiment, the driving member includes a main body and a telescopic member disposed on the main body, and an end of the telescopic member far away from the main body is connected to the driving connection end.

In one embodiment, the robot further comprises a mounting rack, the mounting rack comprises a first beam body and at least two second beam bodies vertically connected with the first beam body, and two arms of each arm assembly are respectively connected to two ends of each second beam body; the driving piece is fixed on the first beam body, and the running direction of the driving piece is along the length direction of the first beam body.

The present application provides in a second aspect an aircraft, comprising:

the fuselage, the fuselage is installed as above horn folding mechanism.

The technical scheme provided by the application can comprise the following beneficial effects:

the horn folding mechanism that the application provides, including at least one horn subassembly and drive mechanism in drive connection with horn subassembly; the horn subassembly includes two horns, actuating mechanism includes driving piece and two link assembly, the power take off end of driving piece is connected with two horns through two link assembly respectively, the driving piece is used for driving two horns through two link assembly and folds or expand for the fuselage of aircraft, every driving piece can control two horns and fold or expand simultaneously, compare with the correlation technique, the structure has been simplified, the quantity of driving piece has been less, consequently, the weight of aircraft has been reduced, the cost is also reduced.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the application.

Drawings

The foregoing and other objects, features and advantages of the application will be apparent from the following more particular descriptions of exemplary embodiments of the application as illustrated in the accompanying drawings wherein like reference numbers generally represent like parts throughout the exemplary embodiments of the application.

FIG. 1 is a schematic structural view of an arm folding mechanism shown in an embodiment of the present application in an unfolded state;

FIG. 2 is a schematic view of the folding mechanism of the boom shown in the embodiment of FIG. 1 in a folded position;

FIG. 3 is a schematic structural diagram illustrating a linkage assembly of the boom fold mechanism in a folded position according to one embodiment of the present application;

FIG. 4 is a schematic structural diagram illustrating an arm folding mechanism according to an embodiment of the present application during an unfolding process;

FIG. 5 is a schematic structural view of a boom fold mechanism shown in an embodiment of the present application in a fully unfolded state;

FIG. 6 is an enlarged partial schematic view at K of FIG. 5;

FIG. 7 is a schematic structural diagram illustrating an alternative view of the folding mechanism of the present application in an unfolded state;

FIG. 8 is a schematic structural view of an arm folding mechanism shown in another embodiment of the present application in an unfolded state;

FIG. 9 is a schematic structural view of the arm folding mechanism shown in the embodiment of FIG. 8 in a folded state;

fig. 10 is a schematic view illustrating an installation structure of the horn folding mechanism according to an embodiment of the present application.

Reference numerals: 1. a horn; 2. a mounting frame; 3. a connecting rod assembly; 4. a drive member; 5. a rotor motor; 6. a rotor blade; 7. a load; 101. a connector; 201. a boom connecting portion; 301. a first rod body; 302. a second rod body; 303. a third rod body; 304. a first connecting member; 401. a main body; 402. a telescopic shaft; 403. a pin shaft; 102. a second connecting member; 112. an adaptor; 122. and a hinged shaft.

Detailed Description

Embodiments of the present application will be described in more detail below with reference to the accompanying drawings. While embodiments of the present application are illustrated in the accompanying drawings, it should be understood that the present application may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

It should be understood that although the terms "first," "second," "third," etc. may be used herein to describe various information, these information should not be limited to these terms. These terms are only used to distinguish one type of information from another. For example, first information may also be referred to as second information, and similarly, second information may also be referred to as first information, without departing from the scope of the present application. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise.

In the description of the present application, it is to be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientation or positional relationship indicated in the drawings for convenience in describing the present application and for simplicity in description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated in a particular manner, and are not to be considered limiting of the present application.

Unless expressly stated or limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can include, for example, fixed connections as well as removable connections or combinations; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.

The wing folding systems of the aircraft in the related art have high structural complexity, heavy weight and low reliability. To above-mentioned problem, this application embodiment provides an arm folding mechanism, has reduced the quantity of driving piece, consequently has reduced the weight of aircraft, also the cost is reduced simultaneously.

The technical solutions of the embodiments of the present application are described in detail below with reference to the accompanying drawings.

FIG. 1 is a schematic structural view of an arm folding mechanism shown in an embodiment of the present application in an unfolded state; fig. 2 is a schematic structural view of the folding mechanism of the arm shown in the embodiment of fig. 1 in a folded state.

Referring to fig. 1 and 2, the present application provides an arm folding mechanism, including at least one arm assembly and a driving mechanism in transmission connection with the arm assembly; the horn subassembly includes two horns 1, and actuating mechanism includes driving piece 4 and two link assembly 3, and the power take off end of driving piece 4 is connected with two horns 1 through two link assembly 3 respectively, and driving piece 4 is used for driving two horns 1 through two link assembly 3 and folds or expand for the fuselage of aircraft.

According to the scheme provided by the application, each driving piece 4 can control the two arms 1 to be folded or unfolded simultaneously, compared with the related art, the structure is simplified, the number of the driving pieces is reduced, the weight of the aircraft is reduced, and the cost is also reduced.

The arm folding mechanism of the embodiment can be applied to multi-rotor aircrafts, fixed-wing aircrafts with folded wings and flying automobiles needing to be switched between a flying state and a land-going state.

The solution of the embodiments of the present application is described below using a multi-rotor aircraft as an example.

In this embodiment, a plurality of rotors of aircraft link to each other with the fuselage through a plurality of horn 1 respectively, and a plurality of horn 1 are folded to being close to the fuselage after, and the rotor can be folded to the fuselage along with horn 1 together, can reduce many rotor aircraft's space and occupy.

Referring to fig. 1, the folding mechanism of the horn further includes a mounting frame 2, the mounting frame 2 is "i" shaped, and the direction shown by the arrow in fig. 1 is the front of the aircraft. In some embodiments, the aircraft is provided with a plurality of horn 1 assemblies, for example two horn 1 assemblies, two horn 1 assemblies being provided at different parts of the aircraft, for example, one set of horn 1 assemblies being provided at the front side of the mounting frame and the other set of horn 1 assemblies being provided at the rear side of the aircraft; or one group of the components of the horn 1 is arranged on the left side of the aircraft, and the other group of the components of the horn 1 is arranged on the right side of the aircraft. It will be appreciated that in other embodiments, more than two sets of the components of the horn 1, such as three or four sets, may be provided according to actual needs. When the plurality of groups of the horn assemblies can be folded towards opposite directions, the occupied space after folding is reduced.

Referring to fig. 3, in some embodiments, two horn connecting portions 201 are provided at a portion of the mounting frame corresponding to each horn 1 assembly, the two horns are respectively provided with a connecting head 101, and the two horns are respectively rotatably connected to the two horn connecting portions 201 through the respective connecting heads 101.

The driving piece 4 respectively drives the two machine arms 1 to rotate relative to the mounting rack through the two connecting rod assemblies 3; when the machine arm 1 rotates towards a direction far away from the mounting rack, the machine arm 1 is in an unfolded state; when the arm 1 rotates in a direction close to the mounting frame, the arm 1 is in a folded state.

Referring to fig. 4, in some embodiments, the mounting frame 2 includes a first beam 21 and at least two second beams 22 vertically connected to the first beam 21, and when there are two second beams 22, the two second beams 22 are respectively disposed at two ends of the first beam 21, so that the mounting frame 2 has an "i" shape. In some embodiments, the first beam 21 is connected to a middle portion of the second beam 22, and the second beam 22 is symmetrical about the first beam 21.

The first beam 21 has a length direction corresponding to the fore-aft direction of the aircraft and is disposed along the center line of the fuselage, so that the first beam 21 is also referred to as the center main beam of the aircraft, and the two second beams 22 are also referred to as the horn 1 mounting beams.

In some embodiments, the connecting rod assembly includes a first connecting end, a second connecting end and a driving connecting end, the first connecting end is hinged to the mounting frame, the second connecting end is hinged to the arm 1, the driving connecting end is hinged to the power output end of the driving element 4, when the driving element 4 operates, the driving connecting end can be driven to move, and when the driving connecting end moves, the whole connecting assembly can be driven to move.

Fig. 3 is a schematic structural diagram of the link assembly when the folding mechanism of the horn 1 is in a folded state according to an embodiment of the present application.

Referring to FIG. 3, in some embodiments, the linkage assembly is formed from a plurality of rods connected together. In one implementation, the connecting rod assembly includes a first rod 301, a second rod 302, and a third rod 303; the first rod 301 is also called an adapter rod, the second rod 302 is also called a tail rod, and the third rod 303 is also called a driving rod.

The two opposite ends of the first rod body 301 and the second rod body 302 are hinged, the two opposite ends of the first rod body 301 and the second rod body 302 are respectively set as a first connecting end and a second connecting end, one end of the third rod body 303 is hinged between the two ends of the first rod body 301, and the other end of the third rod body 303 is set as a driving connecting end.

The corresponding connecting rod assemblies of the two arms 1 of each arm assembly are identical in structure, and the motion ranges of the first rod 301, the second rod 302 and the third rod 303 are located on the same plane, and the plane is perpendicular to the height direction of the aircraft.

In some embodiments, the driving member 4 comprises a main body 401 and a telescopic member disposed on the main body 401, and an end of the telescopic member remote from the main body 401 is connected to the driving connection end. In one implementation, the driving member 4 may be an electric ram, and the telescoping member may be a telescoping shaft 402 of the electric ram.

It is understood that the driving member 4 is not limited to an electric push rod, and in other embodiments, the driving member 4 may also be various mechanisms for converting electric energy into linear motion through a motor, such as a matching mechanism of a rotating motor and a ball screw, a matching mechanism of a reduction motor and a gear rack, a matching mechanism of a reduction motor and a synchronous belt, a matching mechanism of a reduction motor and a crank-slider mechanism, a reduction motor, a matching mechanism of a reel and a steel wire, and the like.

In some embodiments, the mounting frame is provided with a first connecting member 304, the first connecting member 304 may be provided on the first beam 21 of the mounting frame 2, and the first rods 301 of the two link assemblies are respectively hinged to the first connecting member 304. The first connecting member 304 is disposed in the operating direction of the telescopic shaft 402 of the electric push rod, and the telescopic shaft 402 passes through the first connecting member 304 and then is connected to the two third rod bodies 303, for example, hinged by a pivot pin, and the axial direction of the pivot pin is perpendicular to the moving plane of the connecting rod assembly.

In some embodiments, the first connecting member 304 includes a linear bearing and connecting tabs disposed on two sides of the linear bearing, the first rod 301 of the two link assemblies are respectively hinged to the connecting tabs on the two sides, the telescopic shaft 402 of the electric push rod passes through the linear bearing and can slide relative to the linear bearing, and the end of the telescopic shaft 402 away from the main body 401 is rotatably connected to the third rod 303 of the two link assemblies.

In this embodiment, the machine arm 1 is provided with the second connecting member 102, and the second rod 302 of the two link assemblies are respectively hinged to the second connecting members 102 on the two machine arms 1. The two connecting rod assemblies corresponding to the two machine arms 1 are bilaterally symmetrical by taking the axial lead of the telescopic shaft 402 as a symmetrical shaft, the structures and the layouts of the left connecting rod assembly and the right connecting rod assembly are consistent, the connecting rod assemblies only have one degree of freedom of movement in a plane (namely an XY plane) perpendicular to the height direction Z of the aircraft, when the telescopic shaft 402 axially moves relative to the main body 401, the movement of the two connecting rod assemblies keeps synchronous, and then the two machine arms 1 are synchronously folded or unfolded.

Fig. 4 illustrates a movement process of the link assembly by taking one of the booms 1 as an example, a direction indicated by an arrow in fig. 4 is a movement direction of each component, when the telescopic shaft 402 of the electric push rod is retracted backward, the third rod 303 rotates counterclockwise relative to the first link 304, at this time, the third rod 303 pushes the first rod 301 to move in a direction away from the first link 304, the first rod 301 and the second rod 302 rotate around the hinge point C, at this time, the first rod 301 pushes the second rod 302 to rotate around the hinge point E, and finally, the second rod 302 transmits a force to the boom 1 through the second link 102, so as to push the boom 1 to move in a direction away from the mounting bracket 2, so that the boom 1 is unfolded relative to the mounting bracket.

In this embodiment, the connection and force transmission principles of the two link assemblies in the same group are similar, and when the telescopic shaft 402 of the electric push rod contracts, the two link assemblies can be driven to move in the above manner at the same time, so that the two booms 1 are synchronously unfolded.

Referring to fig. 8, when the first rod 301 and the second rod 302 rotate to be along the same straight line, the hinge point B between the first rod 301 and the first beam 21, the hinge point C between the first rod 301 and the second rod 302, and the hinge point E between the second rod 302 and the horn 1 are collinear, and at this time, the connecting rod assembly can lock the horn 1 in the unfolded state, and in the unfolded state, because the second rod 302 of the connecting rod assembly outwards supports the horn 1, the horn 1 can be kept in the non-folded state, i.e., the locked state, during flight.

Referring to fig. 4, 5 and 8, in the present embodiment, when the two booms 1 of each boom assembly are in the fully extended state, the straight lines of the first rod 301 and the second rod 302 of the two link assemblies respectively follow two waists of the virtual isosceles triangle BE1E 2; the two connecting portions of the boom 1 are arranged along the base E1E2 of the virtual isosceles triangle, and the connecting portion of the first beam 21 and the second beam 22 corresponds to the middle point G of the base E1E2 of the virtual isosceles triangle.

In this embodiment, the hinge point B between the first rod 301 and the first beam 21, the hinge point E1 or E2 between the second rod 302 and the horn 1, and the connection G between the first beam 21 and the second beam 22 correspond to three vertexes of a virtual right triangle BE1G or BE 2G. According to the stability of the triangle, the operation of the first rod 301 and the second rod 302 reaches a critical point state, also called a dead point state, and self-locking is realized.

Referring to fig. 5, when the arm 1 generates a moment load in the direction of arrow M, a force along the axial direction of the second rod 302 can support the arm 1, and the force is finally transmitted to the first beam 21 through the hinge point B of the first rod 301 and the first beam 21. When the hinge point E1/E2, the hinge point C and the hinge point B are completely collinear, the loads on the second rod body 302 and the first rod body 301 are distributed only along the straight line where the hinge points E1CB and E2CB are located, so that the relative position of the link assembly is not damaged and is always maintained, and thus a self-locking state is achieved.

In this embodiment, considering the manufacturing and assembling errors and the influence of vibration, the hinge point ECB may not be completely along the same straight line in practice, an angle θ is formed between the second rod 302 and the first rod 301, the axial force along the third rod 303 is proportional to sin θ, and since the angle θ caused by the manufacturing and assembling errors is very small, for example, generally less than 1 degree, sin θ approaches 0, and the force on the third rod 303 is very small. Meanwhile, when the horn 1 is in a fully unfolded state, the third rod 303 is perpendicular to the driving shaft of the electric push rod, and at this time, the operation of the third rod 303 also reaches a critical point state, which is also called a dead point state, so that self-locking is realized. In the critical point state, the third rod 303 does not receive a force along the axial direction thereof, so that the third rod 303 does not move when the horn 1 is loaded, the position state of the third rod 303 is not changed, and the whole connecting rod assembly reaches a self-locking state.

In addition, since the axial force on the third rod 303 is finally transmitted to the first beam 21 through the first connecting member 304, when the two booms 1 are completely unfolded, through the critical point design of the two connecting rod assemblies, when the aircraft is in flight, the load of the two booms 1 swinging in the horizontal direction is completely transmitted to the first beam 21 of the mounting frame 2 through the two rod assemblies in the self-locking state, and the two connecting rod assemblies are kept in the locking state. Therefore, the connecting rod assembly plays a role in driving transmission force for unfolding and folding the machine arm 1 and also plays a role in locking the unfolded machine arm 1, and the locking principle of the unfolded machine arms 1 on the left side and the right side is similar. Therefore, in the present embodiment, only one driving element 4 is used, so that the two booms 1 are synchronously unfolded or folded, and the two booms 1 are kept in the locked state after being unfolded, so that the boom folding mechanism of the present embodiment has a simpler structure, has higher reliability, and reduces the cost.

It can be seen from the above embodiments that, in the solution provided in this embodiment, since the first rod 301 and the second rod 302 are in a set of critical states when they are collinear, and the third rod 303 and the telescopic shaft 402 are in another set of critical states when they are perpendicular, the design scheme that the boom 1 is locked in the unfolded and rotated state is realized by reaching the critical state (and the dead point state) when the link assembly moves, that is, the redundant locking design scheme of the double dead points is realized, and the structural stability of the boom 1 after being unfolded is improved.

Referring to fig. 1 and fig. 7, the horn 1 of the present embodiment may be a long cantilever, the end of the horn 1 away from the mounting bracket is mounted with a motor 5 for driving a rotor blade 6 to rotate, when the aircraft is in a flight state, a rotor load acts on the end of the horn 1 away from the mounting bracket, so that when the aircraft is in a flight or static state, the horn 1 is easily deformed in a vertical direction under the action of the flight load or the gravity of a rotor system, and thus, the position of the second connecting member 102 in the vertical direction is easily changed, and is not coplanar with the connecting rod assembly, which easily causes a risk of the connecting rod jamming.

Referring to fig. 6 and 7, in this embodiment, the second rod 302 is connected to the horn 1 through the second connector 102, the adaptor 112 is disposed on the second connector 102 of the horn 1, one end of the adaptor 112 is rotatably connected to the second connector 102 through the first rotating shaft 122, the other end is rotatably connected to the second rod 302 through the second rotating shaft, the first rotating shaft 122 is perpendicular to the second rotating shaft, that is, the second rod 302 is not directly vertically hinged to the horn 1, but is vertically hinged to the adaptor 112, and then horizontally hinged to the second connector 102 fixed to the horn 1 through the first rotating shaft 122 disposed along the horizontal direction through the adaptor 112. Due to the design, the error value existing between the projection distance of the hinge point B and the hinge point E1/E2 on the transverse plane (namely the XY plane) caused by the deformation of the horn 1 and the sum of the lengths of the actual second rod body 302 and the actual first rod body 301 can be eliminated, the phenomenon that the connecting rod assembly cannot be retracted due to the fact that the horn 1 is deformed after flying or the connecting rod assembly is blocked when the horn 1 has assembly errors is avoided, and the folding reliability of the horn 1 is improved.

Referring to fig. 8 and 9, in other embodiments, the arm folding mechanism may further include three sets of arm assemblies, two sets of arm assemblies being disposed at the rear side of the mounting rack, and the other set of arm assemblies being disposed at the front side of the mounting rack. It can be understood that four or more sets of the horn assemblies can be provided according to actual requirements, and the two horns 1 of each set of the horn assemblies are driven by one driving piece 4, so that the structure is simplified, and the cost is reduced.

In other embodiments, the folding mechanism of the horn of this embodiment may not be limited to be applied to folding or unfolding of the horn 1, and in other embodiments, may also be applied to synchronous wing stowing on both sides of a fixed-wing aircraft.

Referring to fig. 10, the horn 1, the transmission mechanism and the mounting bracket 2 of the present embodiment are assembled into an integral structure, and the structural stability is better, so that the present embodiment can be applied to different installation scenarios, for example, different loads 7 can be connected below the mounting bracket 2, and the loads 7 can be a cargo compartment, a passenger cabin, a traveling chassis, and the like.

The folding mechanism for the horn 1 provided by the present application is described above, and accordingly, the present application also provides an aircraft provided with the folding mechanism for the horn 1 as described in the above embodiments.

The aircraft of this embodiment can be many rotor crafts, and a plurality of rotors of aircraft link to each other with the fuselage through a plurality of horn 1 respectively, and behind a plurality of horn 1 folding to being close to the fuselage, the rotor can be folded to the fuselage along with horn 1 together, can reduce many rotor crafts's space occupation.

The aircraft arm folding mechanism comprises at least one aircraft arm component and a driving mechanism in transmission connection with the aircraft arm component; the horn subassembly includes two horns 1, and actuating mechanism includes driving piece 4 and two link assembly, and the power take off end of driving piece 4 is connected with two horns 1 through two link assembly respectively, and driving piece 4 is used for driving two horns 1 through two link assembly and folds or expand for the fuselage of aircraft. The scheme that this application provided, every driving piece 4 can control two horn 1 and fold or expand, can accomodate horn 1, compares with the correlation technique, has simplified the structure, has reduced the quantity of driving piece, consequently has reduced the weight of aircraft, the while also the cost is reduced.

Having described embodiments of the present application, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the disclosed embodiments. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen in order to best explain the principles of the embodiments, the practical application, or improvements made to the technology in the marketplace, or to enable others of ordinary skill in the art to understand the embodiments disclosed herein.

Claims (10)

1. An arm folding mechanism, comprising:

the driving mechanism is in transmission connection with the machine arm assembly;

the horn subassembly includes two horns, actuating mechanism includes driving piece and two link assembly, the power take off end of driving piece is respectively through two link assembly and two the horn is connected, the driving piece is used for through two link assembly drives two the horn is folding or is expanded for the fuselage of aircraft.

2. The horn folding mechanism of claim 1, wherein:

the mounting frame is provided with two horn connecting parts at the positions corresponding to each group of horn assemblies, and the two horns are rotatably connected to the two horn connecting parts; the driving piece drives the two machine arms to rotate relative to the mounting rack through the two connecting rod assemblies respectively;

when the machine arm rotates towards a direction far away from the mounting rack, the machine arm is in a spreading state; when the horn rotates in a direction close to the mounting bracket, the horn is in a folded state.

3. The horn folding mechanism of claim 2, wherein:

the connecting rod assembly comprises a first connecting end, a second connecting end and a driving connecting end, the first connecting end is connected with the mounting frame, the second connecting end is connected with the machine arm, and the driving connecting end is connected with the power output end of the driving piece.

4. The horn folding mechanism of claim 3, wherein:

the connecting rod assembly comprises a first rod body, a second rod body and a third rod body;

the two opposite ends of the first rod body and the second rod body are connected, the two opposite ends of the first rod body and the second rod body are respectively arranged as the first connecting end and the second connecting end, one end of the third rod body is connected between the two ends of the first rod body, and the other end of the third rod body is arranged as the driving connecting end.

5. The horn folding mechanism of claim 4, wherein:

the motion ranges of the first rod body, the second rod body and the third rod body are in the same plane.

6. The horn folding mechanism of claim 4, wherein:

when the first rod body and the second rod body rotate to be along the same straight line, the connecting rod assembly is in a locking state; and/or

When the third rod body rotates to the direction perpendicular to the running direction of the driving piece, the connecting rod assembly is in a locking state.

7. The horn folding mechanism of claim 4, wherein:

the second body of rod pass through the second connecting piece with the horn links to each other, the second connecting piece is equipped with the adaptor, the one end of adaptor with rotate through first pivot between the second connecting piece and be connected, the other end with rotate through the second pivot between the second body of rod and be connected, first pivot with the second pivot is mutually perpendicular.

8. The horn folding mechanism of claim 3, wherein:

the driving piece comprises a main body and a telescopic piece arranged on the main body, and one end, far away from the main body, of the telescopic piece is connected with the driving connecting end.

9. The horn folding mechanism of claim 2, wherein:

the mounting frame comprises a first beam body and at least two second beam bodies vertically connected with the first beam body, and two machine arms of each machine arm assembly are respectively connected to two ends of each second beam body; the driving piece is fixed on the first beam body, and the running direction of the driving piece is along the length direction of the first beam body.

10. An aircraft, characterized in that it comprises:

a fuselage, said fuselage being fitted with an arm folding mechanism as claimed in any one of claims 1 to 9.

Images