CN218463869U - Unmanned vehicles undercarriage and hatch door linkage jack - Google Patents

Abstract

The utility model relates to the technical field of aircraft undercarriage, in particular to an unmanned aerial vehicle undercarriage and cabin door linkage retraction mechanism, which comprises an undercarriage with one end connected with a body and a retraction actuating component respectively hinged with the undercarriage and the body; the retractable actuating assembly comprises a retractable actuating cylinder and a connecting rod mechanism; the undercarriage comprises an upper support column and a lower support column, wherein one end of the upper support column is fixedly connected with the airframe; the link mechanism is respectively hinged with the upper support column and the lower support column of the landing gear; the lower strut is connected with the cabin door through a rope; the cabin door is hinged with the fuselage, an elastic element is arranged between the cabin door and the fuselage, and the elastic element is respectively hinged with the cabin door and the fuselage. The utility model discloses the pillar is as the partly of jack, through rope, elastic component, receive and release the mutually supporting of actuating the subassembly down, can effectual realization receive and release to the pillar down, further realize that the linkage of undercarriage hatch door receives and releases to realize the linkage of undercarriage and hatch door in the narrow and small space of nose and receive and release the function.

Description

Unmanned vehicles undercarriage and hatch door linkage jack

Technical Field

The utility model relates to an aircraft undercarriage technical field, more specifically say, relate to an unmanned vehicles undercarriage and hatch door linkage jack.

Background

An unmanned aerial vehicle has double capabilities of water take-off and landing and land airport take-off and landing, and can be suitable for more use scenes. When taking off and landing on a land airport, the landing gear needs to be kept to be completely put down and locked in a ground state so as to bear loads of the airplane during taking off and landing and ground sliding; during air flight, the landing gear needs to be completely folded up and stored in the aircraft body, the cabin door is closed, the aerodynamic appearance of the aircraft is kept complete, the flight resistance of the aircraft is reduced, and the flight performance and the fuel efficiency of the aircraft are improved. When taking off and landing on water, the aircraft landing gear uses the ship-shaped body to slide on the water surface to complete the taking off and landing operation, and the landing gear needs to be completely folded and stored in the body and close the cabin door of the aircraft, so that the unfavorable resistance and safety risk of the operation on water caused by the exposure of the landing gear and the opening of the cabin door are avoided.

There are two common landing gear and door retraction techniques:

firstly, the undercarriage and the cabin door respectively use a set of independent retraction mechanism and retraction actuation assembly, the undercarriage integrally rotates around a main rotating shaft of the undercarriage, and sequential retraction operation of the undercarriage and the cabin door is completed through multi-process sequential control, the undercarriage retraction mode has the advantages of large required retraction space, large length and size of the undercarriage cabin, complex sequential control system, poor reliability and heavy structural weight;

and secondly, a retraction actuating component is arranged on an inclined stay bar arranged on the side of the undercarriage, the whole undercarriage rotates around a main rotating shaft of the undercarriage, the undercarriage and the cabin door are hinged and connected through a connecting rod mechanism, and the cabin door is driven to close and open in the retraction process of the undercarriage, so that the required retraction space of the undercarriage is large, the length of the undercarriage cabin is large, the transmission line of the undercarriage and the cabin door linkage retraction mechanism is long, and the rigidity of the connecting rod mechanism and the body supporting structure thereof directly influences whether the opening and closing state of the cabin door meets the design requirements or not, and even influences whether the linkage retraction function of the undercarriage and the cabin door can be smoothly realized.

As an example of the current application in the field of unmanned aircraft landing gear, the common problems of these two retraction mechanisms are: firstly, the space size of an aircraft landing gear body, particularly a nose, is small, and the length size of a storage cabin required by the landing gear is large, so that the arrangement of the landing gear, particularly the nose landing gear, is very difficult; secondly, the force transmission path of the connecting rod mechanism is too long, and the rigidity of the connecting rod mechanism is poor due to the lightweight design, so that the cabin door cannot be opened in place, and the gap between the cabin door and the structure of the machine body is too large when the cabin door is closed, so that the pneumatic appearance of the machine body is influenced.

SUMMERY OF THE UTILITY MODEL

The utility model aims to solve the technical problem that a unmanned vehicles undercarriage and hatch door linkage jack is provided, this undercarriage pillar design is separable structural style from top to bottom, and lower pillar is part of jack, through rope, elastic component, receive and release mutually supporting of actuating the subassembly, can effectual realization to undercarriage lower pillar part receive and release, further realize that the linkage of undercarriage hatch door receives and releases to can realize the linkage of undercarriage and hatch door in the narrow and small space of aircraft nose and receive and release the function.

The utility model provides a solution that technical problem adopted is:

an unmanned aerial vehicle undercarriage and cabin door linkage retraction mechanism comprises an undercarriage one end of which is connected with a body, and retraction actuating components respectively hinged with the undercarriage and the body; the undercarriage comprises an upper support column and a lower support column, wherein one end of the upper support column is fixedly connected with the undercarriage body, and the lower support column is hinged with the other end of the upper support column and serves as a retraction mechanism; the retractable actuating assembly is hinged with the upper support column and the lower support column of the landing gear respectively; the lower strut is connected with the cabin door through a rope; the cabin door is hinged with the fuselage, an elastic piece is arranged between the cabin door and the fuselage, and the elastic piece is respectively hinged with the cabin door and the fuselage.

The utility model discloses a rope, elastic component, receive and release and actuate mutually supporting of subassembly, can effectual realization to the undercarriage pillar part receive and release down, further realize the linkage of undercarriage hatch door and receive and release to realize the linkage of undercarriage and hatch door and receive and release the function in the narrow and small space of aircraft nose.

The process of folding the undercarriage and the cabin door comprises the following steps:

when the undercarriage is in a fully-down state, after an instruction of receiving the undercarriage is received, the retraction actuation assembly drives the lower support column hinged with the retraction actuation assembly to rotate clockwise around a hinged joint of the lower support column and the upper support column, so that the lower support column moves clockwise and retracts towards the front of the aircraft, and finally the lower support column is fully retracted into an undercarriage cabin of the aircraft nose;

in the process that the lower strut of the undercarriage is folded up in the forward direction, the rope connected with the lower strut drives the cabin door to rotate inwards around a hinged joint of the cabin door and the fuselage, and meanwhile, the elastic piece is compressed, and finally the cabin door is closed. After the landing gear and the cabin door are folded in place, the piston rod of the retraction actuating assembly is locked, so that the landing gear and the cabin door are kept in a state of being folded all the time in flight.

Otherwise, the landing gear and the cabin door are put down:

when the undercarriage is put down, a piston rod in the retraction actuating component contracts, so that a lower support column hinged with the retraction actuating component rotates anticlockwise around a hinged joint of the lower support column and the upper support column, the lower support column moves anticlockwise, a rope is changed from a tensioning state to a loosening state at the moment, the pneumatic resistance of the cabin door is overcome under the action of the thrust of an elastic piece and the self weight of the cabin door, the cabin door rotates outwards around the hinged joint of the cabin door and the undercarriage, the cabin door is opened, and when the undercarriage upper support column and the undercarriage lower support column are close to one side and are completely attached to one another, the undercarriage lower support column is completely put down, and the cabin door is completely opened;

in some possible embodiments, in order to effectively realize the folding of the landing gear strut, the requirement on the retraction space is reduced;

the upper support column comprises a support column which is connected with the machine body and is hinged with the retractable actuating component, and a retractable upper support piece which is arranged on the outer side of the support column;

the lower support comprises a wheel fork connecting piece, a wheel assembly arranged on the wheel fork connecting piece, and a folding and unfolding support piece hinged with the folding and unfolding upper support piece and arranged on the wheel assembly.

In some possible embodiments, in order to ensure that the upper support column and the lower support column can be in effective contact and centered when the undercarriage is put down, the direction is stable when the undercarriage is sliding, and the load can be effectively transferred when the undercarriage is used;

the one end that the fuselage was kept away from to the support post is provided with the V type and docks the groove, the pillar is still including installing on receiving down support piece and with the V type boss of V type butt joint groove adaptation down.

In some possible embodiments, in order to effectively realize the articulation of the upper strut and the lower strut, and enable the lower strut to realize the rotation around the articulation point under the driving of the retracting and activating assembly;

the retractable upper supporting piece comprises two groups of L-shaped plates I which are symmetrically arranged and are clamped on the outer side of the supporting upright post through bolts;

the retractable lower supporting member comprises two groups of L-shaped plates II which are symmetrically arranged and are clamped on the wheel fork connecting member through bolts.

In some of the possible embodiments, the first and second,

the support post comprises a post body and an upper V-shaped butt joint cam arranged at one end far away from the machine body and the bottom of the post body, wherein the upper V-shaped butt joint cam is provided with a V-shaped butt joint groove.

In some possible embodiments, in order to effectively realize the fixation of the upper V-shaped butt cam;

one end of the supporting upright post, which is far away from the machine body, is provided with a threaded hole, and the top of the upper V-shaped butt joint cam is arranged in the threaded hole;

the support upright post is also provided with a pin hole which is communicated with the threaded hole;

an upper connecting piece is sleeved on the outer side of the supporting upright post, and is provided with a large hole and a small hole which are coaxial, wherein the diameter of the small hole is smaller than that of the pin; when the supporting upright post is fixedly connected with the upper connecting piece, the axes of the large hole, the small hole and the pin hole are collinear.

In some possible embodiments, in order to effectively realize that the retraction actuating assembly drives the lower support column to rotate around a hinge point between the lower support column and the upper support column, the upper support column and the lower support column are folded, and therefore the retraction of the landing gear is realized;

the retractable actuating assembly comprises a retractable actuating cylinder and a connecting rod mechanism, wherein one end of the retractable actuating cylinder is hinged with the machine body, and the connecting rod mechanism is arranged at the other end of the retractable actuating cylinder and is respectively hinged with the upper support and the lower support.

In some of the possible embodiments of the present invention,

the connecting rod mechanism comprises an upper connecting rod and a lower connecting rod, one end of the upper connecting rod is hinged to the upper support, the other end of the lower connecting rod is hinged to the lower support, and the upper connecting rod is hinged to one end, far away from the machine body, of the retractable actuating cylinder.

In some possible embodiments, the door is opened or closed for efficient implementation;

the cabin door is provided with a joint and is hinged with a rotating shaft arranged on the body through the joint; the elastic part is a gas spring, and two ends of the elastic part are respectively hinged with the machine body and the joint.

In some possible embodiments, in order to achieve an effective closure of the hatch door by means of the cooperation of the lower strut with the elastic member;

the airplane wheel assembly comprises a wheel fork assembly connected with the wheel fork connecting piece and an airplane wheel installed on the wheel fork assembly; one end of the rope is connected with the wheel fork assembly.

Compared with the prior art, the beneficial effects of the utility model are that:

the landing gear strut is designed into an upper strut and a lower strut which can be separated up and down, the structure of the traditional landing gear is changed, the landing gear strut is respectively hinged with the upper strut and the lower strut through the retractable actuating component, and the lower strut is driven to rotate around the hinged joint of the upper strut and the lower strut through the retractable actuating component, so that the retraction of the lower strut is mainly realized; the structure of a retractable actuating assembly formed by the retractable actuating cylinder and the four-bar mechanism is compact; therefore, the requirement on the retraction space of the undercarriage is small, and the length size of the nose undercarriage cabin is greatly reduced; and a single linear retractable actuating assembly is adopted as a power source, so that the safety and reliability are high.

Compare in prior art with the great whole root pillar of undercarriage length dimension receive and release, the utility model discloses well four-bar linkage that forms's connecting rod length is little, and light in weight, and can show the demand that reduces the undercarriage to the length dimension of accomodating the cabin, help realizing the linkage of undercarriage and hatch door in the narrow and small space of nose and receive and release.

The utility model can realize the machine cycle when the landing gear is put down by the matching of the upper V-shaped butt cam and the V-shaped boss, ensure that the direction of the front wheel is in the neutral position when the unmanned aerial vehicle lands, and ensure the stable direction when the unmanned aerial vehicle slides on the ground; meanwhile, the upper V-shaped butt-joint cam and the V-shaped boss realize the transmission of ground load through the combined action of the upper V-shaped butt-joint cam and the V-shaped boss, the connecting rod retracting mechanism and the retracting actuator cylinder.

The utility model realizes the linkage retraction function of the undercarriage and the cabin door thereof through the iron chain and the gas spring; when the landing gear is folded, the tensile force is transmitted through the iron chain to drive the cabin door to be closed, the tensile rigidity of the iron chain is high, the force transmission mode is direct, the path is short, the cabin door can be effectively ensured to be tightly closed, the appearance of the aircraft body is complete, and the resistance to air flight and water gliding is reduced; when the undercarriage is put down, the cabin door is automatically opened through the thrust of the air spring, and the load of the retractable actuating cylinder is reduced.

The utility model discloses can effectually make its hatch door of undercarriage accomplish through the single pressurized strut that receive and releases and receive and release control, it is few to receive and release the system resource demand, and the control logic has been simplified to the reduction system complexity, improves the reliability that the undercarriage received and released.

Drawings

FIG. 1 is a schematic view of the structure relationship of the present invention;

fig. 2 is a schematic structural view of an upper middle pillar according to the present invention;

fig. 3 is a cross-sectional view of an upper middle support according to the present invention;

FIG. 4 is a schematic structural view of the upper middle support, the upper retractable support, the upper connecting member, and the upper V-shaped docking cam of the present invention when assembled;

fig. 5 is a schematic structural view of the upper middle support, the upper retractable support, the upper connecting member, and the upper V-shaped docking cam of the present invention;

FIG. 6 is a schematic structural view of the lower support member, the V-shaped boss, the fork assembly and the wheel of the present invention;

FIG. 7 is a schematic view showing the connection relationship between the retractable supporting member, the retractable upper supporting member and the retractable actuating member when the undercarriage of the present invention is lowered;

FIG. 8 is a schematic view showing the connection relationship between the retracting and extending support member, the retracting and extending upper support member, and the retracting and extending actuating member during the retracting process of the landing gear of the present invention;

FIG. 9 is a schematic view showing the connection relationship between the retractable lower support member, the retractable upper support member, and the retractable actuating assembly when the undercarriage of the present invention is retracted;

fig. 10 is a schematic structural view of the door, the landing gear, the rope and the elastic member after the landing gear of the utility model is put down;

fig. 11 is a schematic structural view of the cabin door, the landing gear, and the body of the landing gear of the present invention after the landing gear is housed in the landing gear bay;

fig. 12 is a schematic structural view of the undercarriage and the airframe when the undercarriage is down;

wherein: 1-an upper support column, 11-a support upright column, 12-a retractable upper support piece, 13-an upper V-shaped butt joint cam, 14-an upper connecting piece, 141-a small hole, 142-a large hole, 15-a pin, 2-a lower support column, 21-a retractable lower support piece, 22-a V-shaped boss, 23-a wheel fork component, 24-a lower connecting piece, 25-an airplane wheel, 26-a wheel fork connecting piece, 3-a rope, 4-an elastic piece, 10-a retractable actuating component, 100-a retractable actuating cylinder, 101-an upper connecting rod, 102-a lower connecting rod, 103-a connecting shaft and 20-a cabin door.

Detailed Description

In the present invention, unless otherwise explicitly specified or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrated; either directly or indirectly through intervening media, either internally or in any other relationship. Reference herein to "first," "second," and similar words, does not denote any order, quantity, or importance, but rather are used to distinguish one element from another. Also, the use of the terms "a" or "an" and the like do not denote a limitation of quantity, but rather denote the presence of at least one. In the implementation of the present application, "and/or" describes an association relationship of associated objects, which means that there may be three relationships, for example, a and/or B, which may mean: a exists alone, A and B exist simultaneously, and B exists alone. In the description of the embodiments of the present application, the meaning of "a plurality" means two or more unless otherwise specified. For example, the plurality of positioning posts refers to two or more positioning posts. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.

The present invention will be described in detail below.

As shown in fig. 1-12:

a linkage retraction mechanism of an unmanned aerial vehicle undercarriage and a cabin door 20 is used for realizing linkage retraction of the undercarriage and the cabin door 20; comprises an undercarriage with one end connected with an airframe and a retractable actuating component 10 hinged with the undercarriage and the airframe respectively;

the undercarriage comprises an upper support column 1 and a lower support column 2, wherein one end of the upper support column 1 is fixedly connected with the airframe, and the lower support column 2 is hinged with the other end of the upper support column 1; the retraction actuating component 10 is respectively hinged with the upper support column 1 and the lower support column 2;

the upper pillar 1 is vertically arranged and fixedly connected with the machine body; the upper supporting column is always kept in a vertical state in the processes of the landing gear and the retraction; the upper prop 1 is not retracted;

the lower strut 2 is connected with the cabin door 20 through a rope 3;

the cabin door 20 is hinged with the fuselage, an elastic element 4 is arranged between the cabin door 20 and the fuselage, and the elastic element 4 is respectively hinged with the cabin door 20 and the fuselage.

The working principle is as follows:

and in the process of retracting the landing gear and the cabin door 20, the landing gear is in a fully-down state in an initial state, and after an instruction of retracting the landing gear is received, the retracting and releasing actuating assembly 10 controls the lower strut 2 hinged with the retracting and releasing actuating assembly to rotate clockwise around a hinged joint of the lower strut 2 and the upper strut 1, so that the lower strut 2 moves clockwise and retracts forwards in the aviation direction, and finally the landing gear and the cabin door are fully retracted into a landing gear cabin of a nose. In the process that the lower support post 2 of the undercarriage is folded up in the forward direction, the rope 3 connected to the lower support post 2 drives the cabin door 20 to rotate inwards around a hinge point of the cabin door and the fuselage, and meanwhile, the elastic piece 4 is compressed, and finally the cabin door 20 is closed; after the landing gear and the door 20 are retracted to the proper position, the piston rod of the retraction actuation assembly 10 is locked, so that the landing gear and the door 20 are always retracted in flight, and the rope 3 is tensioned.

The landing gear and the cabin door 20 are put down, namely the landing gear is retracted in a landing gear retraction cabin of the fuselage in an initial state; when the undercarriage is put down, the retractable actuating component 10 drives the lower support column 2 hinged with the retractable actuating component to rotate around a hinged joint of the lower support column 2 and the upper support column 1 in the anticlockwise direction, the lower support column 2 moves along the anticlockwise direction, at the moment, the rope 3 is changed from a tensioned state to a relaxed state, the pneumatic resistance of the cabin door 20 is overcome under the action of the thrust of the elastic piece 4 and the dead weight of the cabin door 20, the cabin door 20 rotates outwards around the hinged joint of the cabin door and the undercarriage, the cabin door 20 is opened, and when the undercarriage upper support column 1 and the undercarriage lower support column 2 are close to one side and are completely attached to one another, the undercarriage lower support column 2 is completely put down, and the cabin door 20 is completely opened;

compared with the prior art, the utility model effectively realizes the retraction of the upright post part of the undercarriage through the matching of a set of retraction actuating component 10, a rope 3 and an elastic part 4, and simultaneously drives the cabin door 20 to be linked to realize opening and closing, and the utility model discloses only part (lower support 2) in the upright post of the undercarriage is retracted, thereby reducing the retraction space requirement of the undercarriage and extension, and greatly reducing the height and length size of the retraction and extension cabin of the nose undercarriage; and the single linear retractable actuating component 10 is adopted as a power source, so that the safety and the reliability are high.

Preferably, the rope 3 is an iron chain, a steel rope or the like, and the elastic member 4 is a compression spring or a gas spring.

In some possible embodiments, in order to effectively realize the retraction and extension of the lower support column 2 of the undercarriage, the requirement on retraction and extension space is reduced;

the upper strut 1 comprises a support upright 11 connected with the machine body and hinged with the retractable actuating component 10 and a retractable upper support 12 arranged on the outer side of the support upright 11;

the lower strut 2 comprises a wheel fork connecting piece 26, a wheel assembly arranged on the wheel fork connecting piece 26, and a folding lower supporting piece 21 hinged with the folding upper supporting piece 12 and arranged on the wheel assembly; the wheel assembly is located below the stowing upper support 12.

The support upright 11 and the lower support 2 are hinged through the retractable upper support 12 and the retractable lower support 21 to realize the hinging of the upper support 1 and the lower support 2; because the retraction actuating assembly 10 is respectively hinged with the upper support 1 and the lower support 2, the retraction actuating assembly can effectively control the lower support 2 to rotate around a hinged point of the retraction lower support 21 and the retraction upper support 12; thereby realizing the change of the angle between the lower support column 2 and the upper support column 1 and realizing the retraction of the lower support column of the landing gear; compare among the prior art to the great whole root undercarriage pillar of length dimension around its rotation axis rotation with the fuselage realize the undercarriage receive and release, the utility model discloses only do the part (lower support 2) in the undercarriage pillar and receive and release, make like this receive and release the in-process less to the demand in space that receives and releases.

In some possible embodiments, in order to ensure that when the landing gear is lowered, the upper support column 1 and the lower support column 2 can be effectively butted and the aircraft can be in a return, ensure the stability of the flight direction during taxiing and ensure that the load can be effectively transferred during use;

the one end that the fuselage was kept away from to support column 11 is provided with the V type and docks the groove, pillar 2 still including installing on receiving down support piece 21 and with the V type boss 22 of butt joint groove adaptation down.

When the landing gear is put, the lower support column 2 rotates anticlockwise around the hinged point of the lower support column and the upper support column 1 to drive the V-shaped boss 22 to rotate towards the V-shaped butt joint groove; when the supporting upright post 11 is coaxial with the lower support post 2, the top of the V-shaped boss 22 butt-joints the mortise and tenon in the V-shaped butt-joint groove; like this will effectually guarantee that support post 11 and lower pillar 2 can effectual centering, adopt the butt of V profile simultaneously for the contact surface is bigger, can be effectual with the vertical load, course load and the lateral load transmission of ground effect pillar 2 down to the fuselage structurally, direction stability when can also effectual assurance landing and ground motion.

In some possible embodiments, in order to effectively realize the articulation of the upper strut 1 and the lower strut 2, and enable the lower strut 2 to realize the rotation around the articulation point under the driving of the retractable actuating assembly 10;

the retractable upper supporting part 12 comprises two groups of L-shaped plates I which are symmetrically arranged and are clamped on the outer side of the supporting upright post 11 through bolts;

the folding-down support part 21 comprises two groups of L-shaped plates II which are symmetrically arranged and clamped on the wheel fork connecting piece 26 through bolts.

In some possible embodiments, in order to avoid the V-shaped butt groove and the V-shaped boss 22 from being worn seriously after a long time use, so that the support upright 11 and the lower upright 2 cannot be positioned and centered normally;

the support column 11 comprises a column body which is vertically arranged and one end of which is connected with the machine body, and an upper V-shaped butt joint cam 13 which is arranged at one end of the column body far away from the machine body and the bottom of which is provided with a V-shaped butt joint groove _.

The V-shaped boss 22 is fixed on the wheel fork connecting piece 26 through two positioning pins and a fastening bolt, and the V-shaped surface of the V-shaped boss is matched with the V-shaped butt joint groove of the upper V-shaped butt joint cam 13;

the V-shaped butt joint cam 13 is arranged at one end of the support upright post 11 far away from the machine body, a V-shaped butt joint groove is formed in the bottom of the support upright post, and the top of the V-shaped boss 22 is matched with the V-shaped butt joint groove; therefore, the novel electric heating wire can be replaced after being used for a long time, and the condition that the novel electric heating wire cannot be normally used due to serious abrasion is avoided;

in some possible embodiments, in order to effectively achieve the fixing of the upper V-shaped docking cam 13,

one end of the support upright post 11, which is far away from the machine body, is provided with a threaded hole, and the top of the upper V-shaped butt-joint cam 13 is arranged in the threaded hole; the threaded hole and the support upright post 11 are coaxially arranged; the top of the upper V-shaped butt-joint cam 13 is provided with a thread boss matched with the thread hole;

the support upright post 11 is also provided with a pin hole which is communicated with the threaded hole; the axis of the pin hole is vertical to the axis of the threaded hole, and the threaded boss is provided with a through hole communicated with the pin hole;

when the upper V-shaped butt-joint cam 13 is installed, firstly, the threaded boss is in threaded connection with the threaded hole, the through hole is communicated with the pin hole, and then one end of the pin 15 sequentially penetrates through the pin hole and the through hole, so that the upper V-shaped butt-joint cam 13 is fixed;

preferably, the pin holes are arranged in two groups and coaxially;

the outer side of the supporting upright post 11 is sleeved with an upper connecting piece 14, the upper connecting piece 14 is provided with a large hole 142 and a small hole 141 which are coaxial, and the diameter of the small hole 141 is smaller than that of the pin 15; when the support post 11 is fixedly connected with the upper connecting piece 14, the axes of the large hole 142 and the small hole 141 are collinear with the axis of the pin hole.

As shown in fig. 4 and 5, when the upper V-shaped docking cam 13 is installed, one end of the pin 15 sequentially passes through the large hole 142, the pin hole, and the through hole, and then enters into the other pin hole; after the assembly is finished, the upper connecting piece 14 is rotated to enable the small hole 141 to rotate 180 degrees to the position of the original large hole 142, and the upper connecting piece 14 is fixed, so that the pin 15 cannot be withdrawn from the pin hole; the reliability of threaded connection between the upper V-shaped butt-joint cam 13 and the support upright 11 is ensured.

An annular cavity is formed between the upper V-shaped butt-joint cam 13 and the bottom of the upper support 12, and the upper connecting piece 14 is sleeved outside the support column 11 and is located in the annular cavity.

In some possible embodiments, in order to effectively realize that the retraction actuation assembly 10 drives the lower strut 2 to rotate around the hinge point of the lower strut and the upper strut 1, so as to realize the folding of the upper strut 1 and the lower strut 2, and further realize the retraction of the landing gear;

the retractable actuating assembly 10 comprises a retractable actuating cylinder 100 with one end hinged with the machine body and a link mechanism which is arranged at the other end of the retractable actuating cylinder 100 and is respectively hinged with the upper support column 1 and the lower support column 2.

The retractable actuating cylinder 100 adopts the existing equipment and comprises a cylinder body and a piston rod in transmission connection with the cylinder body; the specific internal structure thereof is not detailed here;

as shown in fig. 7-9, when the undercarriage under the ground needs to be retracted into the retraction bay, the piston rod extends, the driving link mechanism drives the lower support 2 to rotate clockwise around the hinge point of the upper retraction support 12 and the lower retraction support 21, and retract in the forward direction, so as to retract the lower support 2, and the lower support 2 drives the bay to rotate inwards in the rotating process, and finally, the lower support is completely retracted into the nose undercarriage bay and simultaneously closes the bay door 20;

in some possible embodiments, in order to effectively realize that the lower strut 2 is driven by the retracting actuator 100 through the connecting assembly, the lower strut 2 is driven, and then the lower strut 2 of the landing gear is put down or retracted while the cabin door 20 is driven to link, so as to realize the opening and closing of the cabin door;

the link mechanism comprises an upper link 101 with one end hinged with the upper connecting piece 14 in the upper pillar 1 and a lower link 102 with one end hinged with the lower pillar 2 and the other end hinged with the upper link 101, wherein the upper link 101 is hinged with one end of the retractable actuating cylinder 100 far away from the machine body.

As shown in fig. 7 to 9, the upper link 101, the lower link 102, the retractable upper support 12, and the retractable lower support 21 form a four-bar linkage; the upper connecting rod 101 is provided with a connecting shaft 103 hinged with a piston rod of the retractable actuating cylinder 100; the connecting shaft 103 is located between a hinge point of the upper connecting rod 101 and the upper connecting piece 14 and a hinge point of the upper connecting rod 101 and the lower connecting rod 102 and is close to one side of the hinge point of the upper connecting rod 101 and the lower connecting rod 102; the four-bar linkage is driven to move by the extension or contraction of the piston rod of the retractable actuator cylinder 100, so that the undercarriage lower strut 2 and the cabin door 20 are driven to complete retraction or retraction operation.

When the undercarriage is in a down state, the piston rod of the retractable actuating cylinder 100 is in a locked state, the undercarriage upper strut 1 and the undercarriage lower strut 2 are meshed through the upper V-shaped butting cam 13 and the V-shaped boss 22 to complete butting, the undercarriage wheels 25 are centered and kept, the direction stability of the unmanned aerial vehicle during landing and ground movement is ensured, and meanwhile, the vertical load, the course load and the lateral load of the wheels 25 acted on the ground are transmitted to a fuselage structure.

In the utility model, the lower upright post 2 of the landing gear is only retracted, so that each connecting rod in the formed connecting rod mechanism has short length and light weight; therefore, the requirement of the landing gear on the length size of the containing cabin is remarkably reduced, and the linked folding and unfolding of the landing gear and the cabin door 20 in a narrow space of the nose is facilitated.

In some possible embodiments, in order to effectively realize the opening or closing of the cabin door 20 under the driving of the elastic piece 4, the retraction actuating assembly and the lower upright post 2;

the cabin door 20 is provided with a joint, and the cabin door 20 is hinged with a rotating shaft arranged on the fuselage through the joint; the elastic part 4 is an air spring, and two ends of the elastic part are respectively hinged with the machine body and the joint.

One end of the joint is arranged on the cabin door 20, the other end of the joint is hinged with the body through a rotating shaft, and the gas spring is connected with the joint; when the undercarriage lower column 2 is down, the gas spring will provide thrust to the door 20;

the lower strut 2 is connected with the cabin door 20 through an iron chain; when the undercarriage is put down, the piston rod is contracted, the lower support column 2 rotates along the hinged point in the anticlockwise direction, the iron chain is changed from the original tensioning state to the loosening state, at the moment, the air spring applies thrust to the cabin door 20, the pneumatic resistance of the cabin door 20 is overcome under the action of the thrust and the dead weight of the cabin door 20, the left cabin door 20 and the right cabin door 20 rotate outwards around the rotating shaft of the cabin door 20, the cabin door 20 is opened, after the upper V-shaped butt-joint cam 13 of the undercarriage upper support column 1 is in butt joint with the V-shaped boss 22 in the lower support column 2, the undercarriage lower support column 2 is completely put down, the cabin door 20 is completely opened, and the undercarriage is put down.

In some possible embodiments, in order to achieve an effective closure of the hatch 20, effectively by means of the cooperation of the lower strut 2 with the elastic element 4;

the wheel assembly comprises a wheel fork assembly 23 connected with a wheel fork connecting piece 26, and a wheel 25 arranged on the wheel fork assembly 23; one end of the cable 3 is connected to a fork assembly 23.

In the prior art, the cabin door 20 is divided into two parts which are hinged with the body through the matching of a joint and a rotating shaft; the wheel fork assembly 23 is connected with the wheel fork connecting piece to form a U-shaped structure with a downward opening, two sides of the U-shaped structure are connected with the cabin doors 20 through the ropes 3 respectively, and the wheel 25 is rotatably installed in an open slot of the U-shaped structure.

In order to facilitate the installation of the V-shaped boss 22, a lower connecting piece 24 is arranged on the lower folding supporting piece 21; the lower support 21 is hinged with the lower connecting rod 102 through the lower connecting piece 24, and the V-shaped boss 22 is arranged on the lower connecting piece 24.

When the landing gear is retracted, the rope 3 is connected with the cabin door 20 and the wheel fork assembly 23, so that the cabin door 20 can be driven to move by the transmitted pulling force, and the linked retraction operation of the landing gear and the cabin door 20 is realized; in order to ensure that the cabin door 20 is in a completely closed state when the landing gear is retracted to the proper position, the number of iron chain rings and the direction of the rotary lug bolt can be properly adjusted to change the action length of the iron chain; when the landing gear is lowered, the thrust of the gas spring and the weight of the door 20 overcome the pneumatic resistance of the door 20, pushing the door 20 to open automatically with the landing gear.

Preferably, the fork assembly 23 is provided with an earring bolt, and the cable 3 is connected to the fork assembly 23 through the earring bolt.

When the doors 20 are two groups, the elastic members 4 are divided into two groups and are respectively in transmission connection with joints connecting the two groups of doors 20, and when the undercarriage is put down, thrust is effectively applied to the two groups of doors 20, so that the doors 20 are opened;

the utility model can be used for the linkage retraction of the front landing gear and the cabin door, and can also be used for the linkage retraction of the main landing gear and the cabin door;

furthermore, the locking flange is sleeved on the outer side of one end, close to the body, of the supporting upright 11, the locking flange is matched with the flange pin through a locking nut sleeved on the inner side of the supporting upright 11 to be fixed to the locking flange, and the locking flange is fixedly connected with the body through the locking flange, so that when the locking flange is used as a nose landing gear, the moment of a turning steering engine can be transmitted to control the front wheel to turn.

The present invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification, and to any novel method or process steps or any novel combination of features disclosed.

Claims (10)

1. An unmanned aerial vehicle undercarriage and cabin door linkage retraction mechanism comprises an undercarriage one end of which is connected with a body, and a retraction actuating component (10) which is respectively hinged with the undercarriage and the body; the landing gear is characterized by comprising an upper support column (1) and a lower support column (2), wherein one end of the upper support column (1) is fixedly connected with a machine body, and the other end of the lower support column (2) is hinged with the other end of the upper support column (1);

the retractable actuating assembly (10) is hinged with the upper support column (1) and the lower support column (2) respectively; the lower strut (2) is connected with the cabin door (20) through a rope (3);

an elastic piece (4) is arranged between the cabin door (20) and the body, and the elastic piece (4) is hinged with the cabin door (20) and the body respectively.

2. The unmanned aerial vehicle landing gear and cabin door linkage retraction mechanism according to claim 1, wherein the upper strut (1) comprises a support column (11) connected with the body and hinged with the retraction actuation assembly (10), and a retraction upper support member (12) installed outside the support column (11);

the lower strut (2) comprises a wheel fork connecting piece (26), a wheel assembly arranged on the wheel fork connecting piece (26), and a folding and unfolding lower supporting piece (21) which is hinged with the folding and unfolding upper supporting piece (12) and is arranged on the wheel assembly.

3. The unmanned aerial vehicle landing gear and cabin door linkage retraction mechanism according to claim 2, wherein one end of the support column (11) far away from the fuselage is provided with a V-shaped butt-joint groove;

the lower strut (2) further comprises a V-shaped boss (22) which is arranged on the wheel fork connecting piece (26) and matched with the V-shaped butt joint groove.

4. The unmanned aerial vehicle landing gear and door linkage stowing and releasing mechanism according to claim 3,

the retractable upper supporting piece (12) comprises two groups of L-shaped plates I which are symmetrically arranged and are clamped on the outer side of the supporting upright post (11) through bolts;

the folding-down supporting piece (21) comprises two groups of L-shaped plates which are symmetrically arranged and clamped on the wheel fork connecting piece (26) through bolts.

5. An unmanned aerial vehicle landing gear and door coordinated retraction and release mechanism according to claim 3, wherein the support upright (11) comprises an upright body, an upper V-shaped docking cam (13) mounted at an end of the upright body remote from the fuselage and provided with a V-shaped docking slot.

6. The mechanism of claim 5, wherein the end of the supporting upright (11) far away from the fuselage is provided with a threaded hole, and the top of the upper V-shaped butt-joint cam (13) is arranged in the threaded hole;

the supporting upright post (11) is also provided with a pin hole, and the pin hole is communicated with the threaded hole;

an upper connecting piece (14) is sleeved on the outer side of the supporting upright post (11), a large hole (142) and a small hole (141) which are coaxial are formed in the upper connecting piece (14), and the diameter of the small hole (141) is smaller than that of the pin (15); when the support upright post (11) is fixedly connected with the upper connecting piece (14), the axes of the large hole (142), the small hole (141) and the pin hole are collinear.

7. An unmanned aerial vehicle landing gear and door coordinated retraction and release mechanism according to any one of claims 1 to 6, wherein the retraction actuator assembly (10) comprises a retraction actuator (100) having one end hinged to the fuselage, and a linkage mechanism provided at the other end of the retraction actuator (100) and hinged to the upper strut (1) and the lower strut (2) respectively.

8. The mechanism of claim 7, wherein the linkage comprises an upper link (101) hinged to the upper strut (1) at one end, and a lower link (102) hinged to the lower strut (2) at one end and to the upper link (101) at the other end, wherein the upper link (101) is hinged to the end of the retraction actuator (100) remote from the fuselage.

9. The undercarriage and door linkage assembly according to any one of claims 1-6 wherein a joint is provided on the door (20), the door (20) is hinged to a pivot provided on the fuselage by the joint, and the resilient member (4) is a gas spring, and both ends of the gas spring are hinged to the fuselage and the joint, respectively.

10. An unmanned aerial vehicle landing gear and door linkage stowing and releasing mechanism according to any one of claims 2 to 6, wherein the wheel assembly includes a fork assembly (23) connected to a fork connection (26), a wheel (25) mounted on the fork assembly (23); one end of the rope (3) is connected with the wheel fork assembly (23).

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