CN220786117U - Landing gear and aircraft - Google Patents

Abstract

The utility model relates to the field of aircrafts, and provides an undercarriage and an aircraft. The landing gear includes: the arm support assembly is used for being rotatably connected with the machine body, so that the vertical included angle between the arm support assembly and the machine body is adjustable; the support wheel is rotatably arranged on the mounting seat, and the mounting seat is rotatably arranged on the arm support assembly so that the movement direction of the support wheel is adjustable; the damping assembly comprises a first connecting piece, a second connecting piece and a damping block, wherein the first connecting piece is rotationally connected with the arm support assembly, the second connecting piece is used for being connected with the machine body, and the damping block is connected between the first connecting piece and the second connecting piece and transmits acting force between the first connecting piece and the second connecting piece. Realize the shock attenuation effect through first connecting piece and second connecting piece extrusion snubber block, need not to set up pipeline or oil circuit, snubber assembly's part quantity is few, and the structure is simpler compact, and the cost is cheaper to it is more convenient to maintain.

Description

Landing gear and aircraft

Technical Field

The utility model relates to the technical field of aircrafts, in particular to an undercarriage and an aircraft.

Background

The light sport aircraft is used as a novel general aircraft and has wide application prospect in the fields of flight training, private flight, public service flight and the like. However, in the design of landing gear for light sport-type aircraft, the design and optimization of shock absorbing structures has been a technical challenge.

The light sport type aircraft in the prior art generally adopts the landing gear with the oil-gas damping structure, and the oil-gas damping structure has the defects of heavy weight, high cost and more complicated maintenance operation.

Disclosure of Invention

The utility model provides a landing gear and an airplane, which are used for solving the defects of heavy weight, high cost and relatively complicated maintenance operation of an oil-gas shock absorption structure in the prior art, so as to achieve the purposes of reducing the weight of the shock absorption structure and simplifying the shock absorption structure.

The present utility model provides a landing gear comprising:

the arm support assembly is used for being rotatably connected with the machine body, so that the vertical included angle between the arm support assembly and the machine body is adjustable;

the support wheel is rotatably mounted on the mounting seat, and the mounting seat is rotatably mounted on the arm support assembly so that the movement direction of the support wheel is adjustable;

the damping assembly comprises a first connecting piece, a second connecting piece and a damping block, wherein the first connecting piece is rotationally connected with the arm support assembly, the second connecting piece is used for being connected with the machine body, and the damping block is connected between the first connecting piece and the second connecting piece and transmits acting force between the first connecting piece and the second connecting piece.

According to the landing gear provided by the utility model, the first connecting piece comprises the guide rod and the first supporting plate connected with the guide rod, and the guide rod is rotationally connected with the arm support assembly;

the second connecting piece comprises a second supporting plate which is used for being connected with the machine body, the second supporting plate is movably sleeved on the guide rod, the guide rod is provided with a limiting structure, and the limiting structure is arranged on one side, far away from the first supporting plate, of the second supporting plate and is used for axially limiting the second supporting plate;

the damping block is sleeved on the guide rod and is arranged between the first supporting plate and the second supporting plate.

According to the landing gear provided by the utility model, the damping assembly further comprises the base plate, the number of the damping blocks is at least two, and the base plate is arranged between any two adjacent damping blocks.

According to the landing gear provided by the utility model, the damping component further comprises the connector, the guide rod is in threaded connection with the connector, and the connector is in rotary connection with the arm support assembly.

The landing gear provided by the utility model further comprises a supporting seat, a supporting shaft and a shaft sleeve;

the support device comprises a support shaft, a support shaft assembly and a support shaft, wherein the number of the support seats is set to be a pair, the support seats are all used for being connected with the machine body, two ends of the support shaft are respectively connected with the pair of support seats, the support shaft is set to be a pair of shaft sleeves, the support shaft is sleeved with the support shaft, and the arm support assembly is rotationally connected with the shaft sleeves.

According to the landing gear provided by the utility model, the landing gear further comprises a locking piece, the supporting seat is provided with a supporting hole, the supporting shaft stretches into the supporting hole, and the locking piece penetrates through the hole wall of the supporting hole and is connected with the supporting shaft.

According to the landing gear provided by the utility model, the arm support assembly comprises the support leg rod and the connecting seat, wherein the connecting seat is detachably connected to one end of the support leg rod and is used for being rotatably connected with the landing gear body, and the other end of the support leg rod is detachably connected with the mounting seat.

According to the landing gear provided by the utility model, the connecting seat further comprises a first sleeve and a second sleeve, the first sleeve is perpendicular to and connected with the second sleeve, the first sleeve is used for being connected with the machine body in a rotating mode, and the landing leg rod is inserted into the second sleeve and connected with the second sleeve through a connecting piece.

According to the landing gear provided by the utility model, the mounting seat comprises the fork frame, the landing gear further comprises the third sleeve 8, the third sleeve 8 is sleeved on the outer side of the supporting leg rod and is connected with the supporting leg rod through the connecting piece, the fork frame is rotatably connected with the third sleeve 8, and the supporting wheel is rotatably mounted on the fork frame.

The utility model also provides an aircraft comprising a landing gear as described above.

According to the landing gear provided by the utility model, the cantilever crane assembly is rotationally connected with the machine body, the first connecting piece of the damping component is connected with the cantilever crane assembly, the second connecting piece of the damping component is connected with the machine body, and the damping block is connected between the first connecting piece and the second connecting piece, so that the impact received by the supporting wheel is transmitted to the cantilever crane assembly through the mounting seat in the process of taking off or landing of an airplane, the cantilever crane assembly approaches to the machine body, and in the process, the damping block between the first connecting piece and the second connecting piece is extruded by the first connecting piece and the second connecting piece, so that the damping block deforms, the impact action of the cantilever crane assembly is absorbed, and the problem that the cantilever crane assembly is broken due to too large instantaneous impact load is solved.

Compared with an oil-gas damping structure, the damping assembly provided by the utility model has the advantages that the damping effect is realized by extruding the damping blocks through the first connecting piece and the second connecting piece, a pipeline or an oil way is not required to be arranged, the number of parts of the damping assembly is small, the structure is simpler and more compact, the cost is lower, and the maintenance is more convenient.

In addition, through the rotary connection of the mounting seat provided with the supporting wheel and the arm support assembly, the running direction of the supporting wheel can be adjusted, so that the running direction of the aircraft on the ground can be adjusted conveniently.

The aircraft provided by the utility model comprises the landing gear provided by the utility model, so that all the advantages of the landing gear are simultaneously contained.

Drawings

In order to more clearly illustrate the utility model or the technical solutions of the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the utility model, and other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic structural view of a landing gear provided in some embodiments of the present utility model;

FIG. 2 is a schematic illustration of a shock absorbing assembly provided in some embodiments of the present utility model;

FIG. 3 is a schematic view of a shaft sleeve and support shaft connection provided in some embodiments of the present utility model;

FIG. 4 is a schematic view of a connection base provided in some embodiments of the present utility model;

fig. 5 is a schematic structural view of a mount provided in some embodiments of the present utility model.

Reference numerals:

1. a boom assembly; 101. a leg bar; 102. a connecting seat; 102a, a first sleeve; 102b, a second sleeve; 2. a mounting base; 3. a shock absorbing assembly; 301. a first connector; 301a, a guide rod; 301b, a first support plate; 302. a second connector; 303. a damper block; 304. a backing plate; 305. a connector; 306. a limit structure; 4. a support base; 5. a support shaft; 6. a shaft sleeve; 7. a locking member; 8. a third sleeve; 9. and a supporting wheel.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the present utility model more apparent, the technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some embodiments of the present utility model, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

Landing gear provided in an embodiment of the present utility model is described below in connection with fig. 1 to 5.

Specifically, the landing gear comprises a boom assembly 1, a mounting seat 2, a support frame and a shock absorbing assembly 3.

The arm support assembly 1 is used for being connected with the machine body in a rotating mode, and therefore the vertical included angle between the arm support assembly 1 and the machine body is adjustable. I.e. the rotation axis between the boom assembly 1 and the fuselage extends in a horizontal direction.

The supporting wheel 9 is rotatably installed on the mounting seat 2, for example, an axle is installed on the mounting seat 2, and the supporting wheel 9 is sleeved on the axle. The supporting wheel 9 is used for contacting with the ground when the aircraft runs on the ground, and plays a supporting role.

The mounting seat 2 is rotatably mounted on the arm support assembly 1 so that the movement direction of the supporting wheel 9 is adjustable. I.e. the axis of rotation between the mounting block 2 and the boom assembly 1 extends in a vertical direction.

The damper assembly 3 comprises a first connector 301, a second connector 302 and a damper block 303. The first connecting piece 301 is rotatably connected with the boom assembly 1, and the second connecting piece 302 is used for being connected with the machine body, for example, the second connecting piece 302 is connected with the machine body through a pin shaft. The damper block 303 is connected between the first link 301 and the second link 302, and transmits a force between the first link 301 and the second link 302. Optionally, the damper block 303 is provided in an elastic structure. For example, the shock absorbing block 303 is a rubber block, a silicone block, or an elastic plastic block.

In this embodiment, during the take-off or landing process of the aircraft, the impact received by the supporting wheel 9 is transmitted to the boom assembly 1 through the mounting seat 2, so that the boom assembly 1 approaches the aircraft body, in this process, the first connecting piece 301 and the second connecting piece 302 squeeze the shock-absorbing block 303 between them, and the shock-absorbing block 303 deforms, so as to absorb the impact action of the boom assembly 1, and further reduce the problem that the boom assembly 1 is broken due to too large instantaneous impact load.

So set up, for oil gas shock-absorbing structure, the damping module 3 of the utility model realizes the shock attenuation effect through the extrusion snubber block 303 of first connecting piece 301 and second connecting piece 302, need not to set up pipeline or oil circuit, the part quantity of damping module 3 is few, and the structure is simpler compact, and the cost is cheaper to it is more convenient to maintain.

In addition, the installation seat 2 provided with the supporting wheel 9 is rotatably connected with the arm support assembly 1, so that the running direction of the supporting wheel 9 can be adjusted, and the running direction of the aircraft on the ground can be adjusted conveniently.

In some embodiments provided by the present utility model, the first connecting member 301 includes a guide rod 301a and a first support plate 301b connected to the guide rod 301a, and the guide rod 301a is rotatably connected to the boom assembly 1.

The second connector 302 includes a second support plate for connection with the body, and the second support plate is movably sleeved on the guide rod 301a. The guide rod 301a is provided with a limiting structure 306, and the limiting structure 306 is disposed on one side of the second support plate far away from the first support plate 301b and is used for limiting the second support plate axially.

The shock-absorbing block 303 is sleeved on the guide rod 301a and is arranged between the first supporting plate 301b and the second supporting plate.

In this embodiment, when the boom assembly 1 is impacted to rotate upwards, the boom assembly 1 drives the guide rod 301a to move upwards, and the guide rod 301a drives the first support plate 301b to move upwards. When the first supporting plate 301b moves upwards, the damping block 303 between the first supporting plate and the second supporting plate can be extruded by the second supporting plate, so that the damping block 303 deforms, the impact action of the arm support assembly 1 is absorbed, and the problem that the arm support assembly 1 is broken due to too large instantaneous impact load is solved. By providing the stopper structure 306 on the guide rod 301a, the second support plate can be prevented from coming off along the guide rod 301a when the first support plate 301b and the second support plate press the damper block 303.

Optionally, the spacing structure 306 includes a spacing nut, a washer, and a rubber ring. The rubber ring sets up between gasket and second backup pad, and stop nut sets up in the gasket one side of keeping away from the rubber ring, stop nut and guide bar 301a threaded connection.

Optionally, the guide rod 301a is provided with a shoulder or a step surface, and the first support plate 301b is sleeved on the guide rod 301a and abuts against the shoulder or the step surface, and the shoulder or the step surface is disposed on one side of the first support plate 301b away from the second support plate. Of course, the first support plate 301b may be welded to the guide rod 301a.

In some embodiments provided by the present utility model, the shock absorbing assembly 3 further comprises a backing plate 304. The number of the damper blocks 303 is at least two, and a backing plate 304 is arranged between any two adjacent damper blocks 303. The damping effect of the damper assembly 3 can be improved by increasing the number of damper blocks 303. Through set up the gasket between snubber block 303, can disperse pressure for every snubber block 303 all atress is balanced, reduces the too big pressure of part and causes the harm to snubber block 303, prolongs snubber block 303's life.

In some embodiments provided by the present utility model, the shock absorbing assembly 3 further comprises a connector 305. The guide rod 301a is in threaded connection with the connector 305, and the connector 305 is in rotary connection with the arm support assembly 1. For example, the connector 305 is provided with a stud, and the guide rod 301a is provided with a threaded hole in threaded engagement with the stud, and vice versa.

In this embodiment, the length of the shock absorbing assembly 3 can be adjusted by adjusting the screwing length of the guide rod 301a and the connector 305, so as to adjust the ground stop angle of the aircraft, and maintain the aircraft in a proper posture.

Further, the shock absorbing assembly 3 further comprises a lock nut. For example, a lock nut is screwed with the stud of the joint head 305, and the lock nut abuts against the end face of the guide rod 301a to reduce the problem of loosening of the guide rod 301a and the joint head 305.

Optionally, the joint 305 is provided as a knuckle bearing. Specifically, a pin shaft is arranged on the arm support assembly 1, and a knuckle bearing is connected with the pin shaft. By providing the joint 305 as a knuckle bearing, the joint 305 is able to withstand large radial, axial loads or a combination of both radial and axial loads. In addition, the connector 305 has a aligning function, and can work normally when the different axiality is large.

In some embodiments provided by the present utility model, the landing gear further comprises a support base 4, a support shaft 5 and a bushing 6.

Wherein, the quantity of supporting seat 4 sets up to a pair of, and supporting seat 4 all is used for being connected with the fuselage. For example, the support base 4 is connected to the body by screws or bolts. Both ends of the support shaft 5 are respectively connected with a pair of support seats 4. The shaft sleeves 6 are arranged in a pair, the pair of shaft sleeves 6 are sleeved on the supporting shaft 5, the arm support assembly 1 is rotatably connected with the shaft sleeves 6, for example, the arm support assembly 1 is sleeved on the outer sides of the pair of shaft sleeves 6 and is rotatably connected with the shaft sleeves 6.

In the present embodiment, the support shaft 5 is supported by the pair of support bases 4, so that the support shaft 5 can receive a larger force. Through the arm support assembly 1 and the support shaft 5 through the shaft sleeve 6 in a rotating fit mode, abrasion of the support shaft 5 can be reduced, and the service life of the support shaft 5 is prolonged.

In some embodiments of the utility model provided, the landing gear further comprises a locking member 7, the support seat 4 is provided with a support hole, the support shaft 5 extends into the support hole, and the locking member 7 passes through the wall of the support hole and is connected with the support shaft 5. So set up, can subtract back shaft 5 and supporting seat 4 locking through retaining member 7, prevent that back shaft 5 from moving along axial or circumference, improve the steadiness of back shaft 5.

Optionally, the locking member is a screw or a pin.

In some embodiments provided by the present utility model, the boom assembly 1 includes a leg bar 101 and a connection mount 102.

Wherein, the connecting seat 102 detachably connects in the one end of landing leg pole 101, and the connecting seat 102 is used for rotating with the fuselage to be connected, and the other end of landing leg pole 101 is connected with mount pad 2 detachably. The arm support assembly 1 is processed and assembled in parts, so that the processing difficulty of the arm support assembly 1 is reduced, and in addition, the size of any part of the arm support assembly 1 can be changed, so that the arm support assemblies 1 with different specifications can be formed conveniently.

In some embodiments provided by the present utility model, the connection seat 102 includes a first sleeve 102a and a second sleeve 102b.

Wherein, the first sleeve 102a and the second sleeve 102b are vertical and connected, and the first sleeve 102a is used for being connected with the machine body in a rotating way. The leg bar 101 is inserted into the second sleeve 102b and connected to the second sleeve 102b by a connection. So arranged, the structure of the connecting seat 102 is simple.

Alternatively, the leg bar 101 is inserted into the second sleeve 102b and connected to the second sleeve 102b by a connector comprising: the connection member is provided as a screw connection member which passes through the second sleeve 102b and the leg bar 101 in sequence and connects the second sleeve 102b and the leg bar 101. For example, the threaded connection is provided as a screw or bolt.

Optionally, the first sleeve 102a and the second sleeve 102b are welded together. Further, the connection seat 102 further includes a reinforcing rod, and two ends of the reinforcing rod are welded to the first sleeve 102a and the second sleeve 102b respectively. By this arrangement, the strength of the connection between the first sleeve 102a and the second sleeve 102b can be improved, thereby improving the overall strength of the connection seat 102.

Optionally, the first sleeve 102a is rotatably sleeved on the outer side of the shaft sleeve 6, the shaft sleeve 6 is sleeved on the supporting shaft 5, two ends of the supporting shaft 5 are respectively connected with the two supporting seats 4, and the two supporting seats 4 are connected with the machine body.

Further, be equipped with the shaft shoulder on the outer circumference wall of axle sleeve 6, axle sleeve 6 stretches into in the first sleeve 102a to the shaft shoulder of axle sleeve 6 offsets with first sleeve 102 a's terminal surface, and the one side that the shaft shoulder kept away from first sleeve 102a offsets with corresponding supporting seat 4, so set up, can form axial spacing effect to axle sleeve 6, prevent that axle sleeve 6 from following axial displacement.

In some embodiments provided by the utility model, the mount 2 comprises a fork and the landing gear further comprises a third sleeve 8. The third sleeve 8 is sleeved outside the leg rod 101 and is connected with the leg rod 101 through a connecting piece, the fork frame is rotationally connected with the third sleeve 8, the supporting wheel 9 is rotationally arranged on the fork frame, namely, the supporting wheel 9 is rotationally arranged inside the fork frame.

Optionally, the third sleeve 8 is sleeved on the outer side of the leg bar 101 and connected with the leg bar 101 through a connecting piece comprises: the connection is provided as a threaded connection which in turn passes through the third sleeve 8 and the leg bar 101 and connects the third sleeve 8 and the leg bar 101. For example, the threaded connection is provided as a screw or bolt.

Optionally, the fork and the third sleeve 8 are connected by a connecting shaft. For example, the third sleeve 8 is provided with a connecting shaft, and the fork is provided with a cylinder rotatably fitted around the outer side of the connecting shaft.

The embodiment of the utility model also provides an aircraft.

Specifically, the aircraft includes landing gear as described above. It should be noted that the aircraft includes the landing gear, and all the advantages of the landing gear are also included, which will not be described herein.

Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present utility model, and are not limiting; although the utility model has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present utility model.

Claims (10)

1. A landing gear, comprising:

the arm support assembly (1) is used for being rotationally connected with the machine body, so that the vertical included angle between the arm support assembly (1) and the machine body is adjustable;

the support wheel is rotatably mounted on the mounting seat (2), and the mounting seat (2) is rotatably mounted on the arm support assembly (1) so that the movement direction of the support wheel is adjustable;

damping module (3), damping module (3) include first connecting piece (301), second connecting piece (302) and snubber block (303), first connecting piece (301) with cantilever crane assembly (1) rotates to be connected, second connecting piece (302) be used for with the fuselage is connected, snubber block (303) connect in first connecting piece (301) with between second connecting piece (302), and first connecting piece (301) with transfer effort between second connecting piece (302).

2. Landing gear according to claim 1, wherein the first connection (301) comprises a guide bar (301 a) and a first support plate (301 b) connected to the guide bar (301 a), the guide bar (301 a) being in rotational connection with the boom assembly (1);

the second connecting piece (302) comprises a second supporting plate which is used for being connected with the machine body, the second supporting plate is movably sleeved on the guide rod (301 a), the guide rod (301 a) is provided with a limiting structure (306), and the limiting structure (306) is arranged on one side, far away from the first supporting plate (301 b), of the second supporting plate and is used for axially limiting the second supporting plate;

the damping block (303) is sleeved on the guide rod (301 a) and is arranged between the first supporting plate (301 b) and the second supporting plate.

3. Landing gear according to claim 2, wherein the shock-absorbing assembly (3) further comprises a backing plate (304), the number of shock-absorbing blocks (303) being arranged in at least two, and the backing plate (304) being arranged between any adjacent two of the shock-absorbing blocks (303).

4. Landing gear according to claim 2, wherein the shock absorbing assembly (3) further comprises a connector (305), the guide rod (301 a) being in threaded connection with the connector (305), the connector (305) being in rotational connection with the boom assembly (1).

5. Landing gear according to any of claims 1 to 4, further comprising a support seat (4), a support shaft (5) and a bushing (6);

the support device comprises a support base (4), a pair of support bases (4), a support shaft (5) and a shaft sleeve (6), wherein the support bases (4) are arranged in a pair, the support bases (4) are all used for being connected with a machine body, the two ends of the support shaft (5) are respectively connected with the pair of support bases (4), the shaft sleeve (6) is arranged in a pair, the shaft sleeve (6) is sleeved on the support shaft (5), and the arm support assembly (1) is rotationally connected with the shaft sleeve (6).

6. Landing gear according to claim 5, further comprising a locking member (7), wherein the support seat (4) is provided with a support hole, the support shaft (5) extending into the support hole, the locking member (7) passing through the wall of the support hole and being connected to the support shaft (5).

7. Landing gear according to any of claims 1-4, wherein the boom assembly (1) comprises a leg bar (101) and a connection mount (102), the connection mount (102) being detachably connected to one end of the leg bar (101), the connection mount (102) being adapted for rotational connection with the fuselage, the other end of the leg bar (101) being detachably connected to the mounting mount (2).

8. Landing gear according to claim 7, wherein the connection seat (102) comprises a first sleeve (102 a) and a second sleeve (102 b), the first sleeve (102 a) and the second sleeve (102 b) being perpendicular and connected, the first sleeve (102 a) being intended to be in rotational connection with the fuselage, the leg bar (101) being inserted into the second sleeve (102 b) and connected to the second sleeve (102 b) by a connection.

9. Landing gear according to claim 7, wherein the mounting (2) comprises a fork, the landing gear further comprising a third sleeve (8), the third sleeve (8) being sleeved outside the leg bar (101) and being connected to the leg bar (101) by a connection, the fork being rotatably connected to the third sleeve (8), the support wheel being rotatably mounted to the fork.

10. An aircraft comprising a landing gear according to any one of claims 1 to 9.