CN116812142B - Undercarriage buffer gear and undercarriage - Google Patents
Undercarriage buffer gear and undercarriage Download PDFInfo
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- CN116812142B CN116812142B CN202310421029.6A CN202310421029A CN116812142B CN 116812142 B CN116812142 B CN 116812142B CN 202310421029 A CN202310421029 A CN 202310421029A CN 116812142 B CN116812142 B CN 116812142B
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- outer sleeve
- storage space
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- 239000000872 buffer Substances 0.000 title claims abstract description 94
- 230000000149 penetrating effect Effects 0.000 claims abstract description 4
- 230000003139 buffering effect Effects 0.000 claims description 51
- 239000003921 oil Substances 0.000 claims description 35
- 238000005192 partition Methods 0.000 claims description 20
- 239000010720 hydraulic oil Substances 0.000 claims description 14
- 238000013016 damping Methods 0.000 claims description 11
- 238000007789 sealing Methods 0.000 claims description 7
- 230000008602 contraction Effects 0.000 claims description 2
- 238000000926 separation method Methods 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 19
- 238000000034 method Methods 0.000 description 23
- 239000007789 gas Substances 0.000 description 10
- 238000007906 compression Methods 0.000 description 6
- 230000006835 compression Effects 0.000 description 5
- 230000005489 elastic deformation Effects 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 238000012856 packing Methods 0.000 description 2
- 229910000797 Ultra-high-strength steel Inorganic materials 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Classifications
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The application relates to a landing gear buffer mechanism and landing gear, which are applied to the technical field of landing gears, and comprise an outer sleeve and an inner sleeve, wherein the inner sleeve is slidably arranged in the outer sleeve, one end of the outer sleeve is provided with an end plate, a sliding hole for the inner sleeve to pass through is formed in the end plate in a penetrating manner, one end of the inner sleeve is connected with a bearing column after passing through the sliding hole, one end of the inner sleeve, far away from the bearing column, is provided with a pushing plate, and the pushing plate is positioned in the outer sleeve; a first buffer assembly is arranged between the pushing plate and the end plate, and the first buffer assembly stretches under the driving of the pushing plate. The application has the following effects: the first buffer assembly, the second buffer assembly and the third buffer assembly are matched for use, the three-level buffer effect is achieved, one-level or multi-level buffer can be automatically selected according to the received impact, the heat consumption is high, and the buffer efficiency is high.
Description
Technical Field
The application relates to the technical field of landing gears, in particular to a landing gear buffer mechanism and a landing gear.
Background
Landing gear is a support system necessary for aircraft take-off, landing, running, ground movement and parking, and is one of the main components of an aircraft. When an aircraft lands and takes off, the ground can generate great impact force and jolt vibration on the aircraft, and the structure and the safety performance of the aircraft are easily influenced, so that a buffer device is often arranged on a landing gear to reduce the impact and vibration load of the aircraft.
In the related art, an aircraft landing gear with a buffer device is provided, for example, chinese patent publication No. CN113716028A published by the national intellectual property agency in 11 of 2021 discloses a shock-absorbing landing gear and an unmanned aerial vehicle, when the unmanned aerial vehicle lands, the aircraft wheel receives impact from the ground, an upper supporting rod and a lower supporting rod jointly extrude a connecting spring in a spring sleeve, and the connecting spring generates elastic deformation to absorb impact energy and generate heat consumption, so that a shock-absorbing effect is achieved. In addition, the upper and lower both ends of connecting spring are all fixed with friction washers, and friction washers's outer wall and spring sleeve's inner wall contact produces frictional resistance when friction washers and spring sleeve move each other to produce the heat consumption, further promote shock attenuation effect.
The landing gear in the related art mainly relies on elastic deformation generated after the connecting spring receives pressure to absorb impact energy, and most of absorbed energy is converted into heat energy to be dissipated, but the connecting spring has small heat consumption effect and is easy to have the problem of low buffering efficiency.
Disclosure of Invention
In order to solve the problems that the landing gear in the related art mainly depends on deformation of a connecting spring to consume impact energy, and has small heat consumption effect and low buffering efficiency, the application provides a landing gear buffering mechanism and a landing gear.
In a first aspect, the present application provides a landing gear cushioning mechanism, which adopts the following technical scheme:
the landing gear buffer mechanism comprises an outer sleeve and an inner sleeve, wherein the inner sleeve is slidably arranged in the outer sleeve, one end of the outer sleeve is provided with an end plate, a sliding hole for the inner sleeve to pass through is formed in the end plate in a penetrating mode, one end of the inner sleeve passes through the sliding hole and then is connected with a bearing column, one end, far away from the bearing column, of the inner sleeve is provided with a pushing plate, and the pushing plate is positioned in the outer sleeve;
the pushing plate is characterized in that a first buffer assembly is arranged between the pushing plate and the end plate, a second buffer assembly and a third buffer assembly are further arranged in the outer sleeve, and the first buffer assembly, the second buffer assembly and the third buffer assembly stretch under the driving of the pushing plate.
Through adopting above-mentioned technical scheme, the aircraft takes off or landings in-process, thereby the force-bearing post will receive the impact from ground and drive inside sleeve and slide in outside sleeve, and first buffer assembly, second buffer assembly and third buffer assembly are flexible under the order of supporting the push pedal to consume vibration energy in flexible in-process, play the effect of buffering the impact force that the force-bearing post received. And the triple buffering is mutually matched, the needed buffering stage number can be automatically selected according to the size of the received impact, the grading buffering is realized, the larger impact can be absorbed, the slight vibration can be filtered, and the buffering effect is good.
Optionally, the first buffer assembly includes the cover and locates buffer extension spring on the inside sleeve lateral wall, buffer extension spring is located support the push pedal with between the end plate, buffer extension spring's one end is fixed support the push pedal on, the other end is fixed on the end plate.
Through adopting above-mentioned technical scheme, when pushing up the push pedal under inside telescopic drive, pushing up the push pedal and pulling buffering extension spring, buffering pressure spring atress takes place elastic deformation, exerts a pulling force towards the end plate direction to the push pedal all the time, and the impact force opposite direction that receives with pushing up the push pedal, offset each other, play cushioning effect.
Optionally, a guide sleeve is sleeved and fixed on the pushing plate, the guide sleeve is slidably mounted in the outer sleeve, an embedded groove is formed in the outer ring of the guide sleeve, the embedded groove is formed along the circumferential direction of the pushing plate, a sealing ring is embedded in the embedded groove, and the sealing ring is abutted against the inner wall of the outer sleeve.
Through adopting above-mentioned technical scheme, guide sleeve cup joints and fixes on the push pedal, has played the guide effect to the process of sliding of push pedal for the push pedal slides along outside telescopic length direction all the time. The sealing ring is embedded on the outer ring of the guide sleeve and abuts against the inner wall of the outer sleeve to play a role in sealing, so that the inside of the outer sleeve is in a sealing state.
Optionally, be equipped with the division board in the outer sleeve, the division board will the inside gas storage space and the oil storage space of dividing into of outer sleeve, be filled with hydraulic oil in the oil storage space, it is equipped with the damping hole to run through on the division board, the damping hole intercommunication gas storage space with the oil storage space, inside sleeve is located in the oil storage space.
Through adopting above-mentioned technical scheme, the force-bearing column receives the impact and slides, drives inside sleeve, push pedal and direction sleeve and slides, and the oil storage space is compressed, and the hydraulic oil of storing in the oil storage space is extruded into the gas storage space through the damping hole, produces the heat consumption in extrusion process, consumes impact energy.
Optionally, the second buffer assembly is arranged in the oil storage space, the second buffer assembly comprises a buffer pressure spring, one end of the buffer pressure spring is fixed on the partition plate, and the other end of the buffer pressure spring is fixed on the pushing plate;
be equipped with the guide bar in the oil storage space, the guide bar is followed the flexible direction setting of buffering pressure spring, the buffering pressure spring cover is located on the lateral wall of guide bar, the one end of guide bar passes be connected with the limiting plate behind the division board, the division board is dorsad be equipped with the confession on the face of buffering pressure spring the holding tank of limiting plate embedding, the limiting plate adaptation embedding behind the holding tank with the division board is fixed, the guide bar is dorsad the one end adaptation of limiting plate inserts in the inside sleeve.
Through adopting above-mentioned technical scheme, the force-bearing column receives the impact and moves to division board direction, and the thrust board compresses buffering pressure spring, and buffering pressure spring atress compression and apply a pressure towards force-bearing column direction to the thrust board, offset each other with the impact force that the force-bearing column received, play the cushioning effect.
Set up the guide bar in the oil storage space, on the lateral wall of guide bar was located to the buffering pressure spring cover, played the guide effect to the buffering pressure spring for the buffering pressure spring is when the atress, stretches out and draws back along self length direction all the time, is difficult for appearing buckling so that influence the condition of buffering effect.
Optionally, the third buffer assembly is located in the gas storage space, the third buffer assembly includes the piston piece, the periphery of piston piece with the inner wall in gas storage space supports and pastes, the piston piece dorsad one side of division board is equipped with reset spring, reset spring's one end is fixed on the piston piece, the other end is fixed on the inner wall of outside sleeve.
Through adopting above-mentioned technical scheme, hydraulic oil is extruded in the gas storage space, promotes the piston piece and slides, compresses reset spring, and reset spring applys the pressure to the division board direction to the piston piece simultaneously, promotes the piston piece to remove, produces the heat consumption in the reciprocating motion in-process of piston piece, plays the cushioning effect.
Optionally, the end plate is provided with a friction washer at the sliding hole, the friction washer is arranged along the circumference of the sliding hole and sleeved on the side wall of the inner sleeve, and the friction washer is adapted to block the gap between the side wall of the inner sleeve and the wall of the sliding hole.
Through adopting above-mentioned technical scheme, the inner circle of friction packing ring and the butt of inside telescopic lateral wall, inside sleeve slip in-process with friction packing ring relative motion, produce frictional resistance to produce the heat consumption, further promoted buffer efficiency.
Optionally, an anti-torsion assembly is disposed between the inner sleeve and the outer sleeve, and the anti-torsion assembly includes a pair of connecting rods hinged to each other, where one connecting rod is fixed on the outer sleeve, and the other connecting rod is fixed on the inner sleeve.
Through adopting above-mentioned technical scheme, in the buffering process, the connecting rod is fixed on outside sleeve or inside sleeve for inside sleeve is difficult for taking place to deflect in outside sleeve in the slip process, reduces inside sleeve deflection so that the aircraft slip process is obstructed the condition.
Optionally, the connecting rod comprises a pair of movable rods, a connecting spring and a connecting sleeve, wherein the connecting spring is arranged in the connecting sleeve, one end of one movable rod extends into the connecting sleeve and is connected with the connecting spring, and the other end of the movable rod is hinged with the movable rod on the other connecting rod; one end of the other movable rod extends into the connecting sleeve from the other end of the connecting sleeve and is connected with the connecting spring, and the other end of the other movable rod is hinged to the corresponding outer sleeve or inner sleeve.
Through adopting above-mentioned technical scheme, in the buffering process, a pair of movable rod coextrusion coupling spring, coupling spring atress compression produces the heat consumption, plays the cushioning effect.
In a second aspect, the present application provides an undercarriage applying an undercarriage buffer mechanism, which adopts the following technical scheme: the landing gear with the landing gear buffer mechanism comprises a connecting seat for connecting an aircraft, wherein the connecting seat is fixed on one end of the outer sleeve, which is far away from the bearing column, and one end of the bearing column, which is far away from the inner sleeve, is provided with an organic wheel.
Through adopting above-mentioned technical scheme, buffer gear passes through the connecting seat and installs on the aircraft, and the wheel is installed on the force-bearing post, and the aircraft takes off and the landing in-process wheel receives the impact from ground, and buffer gear buffers the impact of receiving.
In summary, the present application includes at least one of the following beneficial technical effects:
1. in the process of taking off or landing of the aircraft, the bearing column is impacted by the ground so as to drive the inner sleeve to slide in the outer sleeve, the first buffer component, the second buffer component and the third buffer component are driven by the pushing plate to stretch and retract, and consume vibration energy in the stretching process, so that the effect of buffering the impact force received by the bearing column is achieved, the triple buffering is matched with each other, the needed buffering stage number can be automatically selected according to the size of the impact, and the grading buffering is realized, so that larger impact can be absorbed, and slight vibration can be filtered;
2. the bearing column is impacted and slipped to drive the inner sleeve, the pushing plate and the guide sleeve to slip, the oil storage space is compressed, hydraulic oil stored in the oil storage space is extruded into the oil storage space through the damping hole, heat consumption is generated in the extrusion process, and impact energy is consumed;
3. set up the guide bar in the oil storage space, on the lateral wall of guide bar was located to the buffering pressure spring cover, played the guide effect to the buffering pressure spring for the buffering pressure spring is when the atress, stretches out and draws back along self length direction all the time, is difficult for appearing buckling so that influence the condition of buffering effect.
Drawings
FIG. 1 is a schematic view of a landing gear cushioning mechanism in an embodiment of the present application.
FIG. 2 is a cross-sectional view of a landing gear cushioning mechanism in an embodiment of the present application.
Fig. 3 is an enlarged view of a portion a in fig. 2.
Fig. 4 is an enlarged view of a portion B in fig. 2.
Reference numerals: 1. an outer sleeve; 2. an inner sleeve; 3. an end plate; 31. a slip hole; 4. a force bearing column; 5. a pushing plate; 6. a first cushioning assembly; 61. a buffer tension spring; 7. a second cushioning assembly; 71. a buffer compression spring; 8. a third cushioning assembly; 81. a piston plate; 82. a return spring; 9. a guide sleeve; 91. an embedding groove; 10. a seal ring; 11. a partition plate; 111. a damping hole; 112. a receiving groove; 12. a gas storage space; 13. an oil storage space; 14. a guide rod; 15. a limiting plate; 16. a friction washer; 17. an anti-twist assembly; 171. a connecting rod; 1711. a movable rod; 1712. a connecting spring; 1713. a connecting sleeve; 18. a connecting seat; 19. and a machine wheel.
Detailed Description
The present application is described in further detail below in conjunction with figures 1-4.
The embodiment of the application discloses a landing gear buffer mechanism.
Referring to fig. 1 and 2, a landing gear cushioning mechanism includes an outer sleeve 1 disposed in a vertical direction, the outer sleeve 1 having a cylindrical structure with an open bottom end.
An inner sleeve 2 is slidably mounted in the outer sleeve 1, a pushing plate 5 is integrally formed at one end of the inner sleeve 2, and the pushing plate 5 is located in the outer sleeve 1. The opening part integrated into one piece of outside sleeve 1 has end plate 3, is equipped with first buffer assembly 6 between end plate 3 and the push pedal 5, and inside sleeve 2 slides the in-process, and first buffer assembly 6 constantly stretches out and draws back, realizes the buffering.
Referring to fig. 2 and 3, a sliding hole 31 through which the inner sleeve 2 passes is formed in the center of the end plate 3, and a bearing post 4 is coaxially welded after one end of the inner sleeve 2, which is far away from the thrust plate 5, passes through the sliding hole 31.
Specifically, the first damper assembly 6 includes a damper tension spring 61, one end of the damper tension spring 61 is welded to the thrust plate 5, and the other end is welded to the end plate 3. During the take-off or landing process of the aircraft, the bearing column 4 is impacted by the ground and slides in the outer sleeve 1 to drive the inner sleeve 2 and the pushing plate 5 to move, and the buffer tension spring 61 is stretched under stress to generate deformation. The buffer tension spring 61 consumes impact energy in the continuous expansion and contraction process, generates heat consumption, and plays a primary buffer effect, namely, first heavy buffer.
The outer sleeve 1 and the inner sleeve 2 in the embodiment of the application are forged by adopting ultrahigh-strength steel matched with a vacuum heat treatment technology, and have stronger bearing capacity.
Referring to fig. 2, in addition, the push plate 5 is sleeved with the guide sleeve 9, and the side wall of the guide sleeve 9 abuts against the inner wall of the outer sleeve 1, so that the push plate 5 and the inner sleeve 2 slide along the extending direction of the outer sleeve 1 all the time when impacted, a guide effect is achieved, and the stability of the inner sleeve 2 in the sliding process is improved.
Referring to fig. 2 and 4, further, a partition plate 11 is provided in the outer sleeve 1, the partition plate 11 divides the interior of the outer sleeve 1 into a gas storage space 12 and an oil storage space 13, nitrogen is stored in the gas storage space 12, and hydraulic oil is filled in the oil storage space 13. The partition plate 11 is provided with a plurality of damping holes 111 in a penetrating manner, and the damping holes 111 are communicated with the oil storage space 13 and the gas storage space 12.
When the aircraft takes off or lands, the supporting column is impacted by the ground to drive the inner sleeve 2, the pushing plate 5 and the guide sleeve 9 to move towards the partition plate 11, the oil storage space 13 is compressed, and hydraulic oil in the oil storage space 13 is extruded into the air storage space 12 through the damping hole 111 to play a role in buffering.
Referring to fig. 2 and 4, in order to further improve the buffering effect, in this embodiment, the second buffering component 7 is disposed in the oil storage space 13, the second buffering component 7 includes a buffering pressure spring 71, one end of the buffering pressure spring 71 is welded on the partition plate 11, the other end is welded on the pushing plate 5, and the pushing plate 5 compresses the buffering pressure spring 71 during moving, so as to play a role in buffering. In addition, since the buffer compression spring 71 has a long length, a bending phenomenon may occur during the compression process, and the buffer effect may be affected once the buffer compression spring 71 is bent.
Therefore, in this application embodiment, the guide rod 14 is disposed in the oil storage space 13, the guide rod 14 is disposed along the extending direction of the outer sleeve 1, one end of the guide rod 14 penetrates through the partition plate 11, and then the partition plate 11 is integrally formed with the limit plate 15, the surface of the partition plate 11 facing away from the pushing plate 5 is provided with the accommodating groove 112 into which the limit plate 15 is embedded, and the limit plate 15 is embedded into the accommodating groove 112 in an adapting manner, and then is fixed on the partition plate 11 by bolts, so that the fixing of the guide rod 14 is completed. Furthermore, in the present application, the end of the guide rod 14 far away from the limiting plate 15 is inserted into the inner sleeve 2 in an adaptive manner, so that the stability of the installation of the guide rod 14 in the oil storage space 13 is improved.
Referring to fig. 2 and 4, a third buffer assembly 8 is further provided in the air storage space 12, and the third buffer assembly 8 includes a piston plate 81, and a periphery of the piston plate 81 abuts against an inner wall of the outer sleeve 1. The side of the piston plate 81 facing away from the partition plate 11 is provided with a plurality of return springs 82, one end of each return spring 82 is welded on the inner wall of the outer sleeve 1, and the other end is welded on the piston plate 81.
When the aircraft flies (i.e. the force-bearing column 4 is not impacted by the ground), the return spring 82 presses the piston plate 81 against the partition plate 11, so that the hydraulic oil is blocked in the oil storage space 13; when the aircraft takes off or lands, the force-bearing column 4 is influenced by impact force to slide upwards, the pushing plate 5 and the guide sleeve 9 slide upwards to compress the oil storage space 13, hydraulic oil in the oil storage space 13 is extruded into the air storage space 12, and the piston plate 81 returns the hydraulic oil to the oil storage space 13, so that the hydraulic oil flows between the oil storage space 13 and the air storage space 12 through the damping hole 111, and the buffering effect is further improved.
Referring to fig. 2 and 3, in addition, since the oil storage space 13 is filled with hydraulic oil, the oil storage space 13 is continuously squeezed during the buffering process. Therefore, in order to reduce the leakage of hydraulic oil in the embodiment of the present application, a plurality of embedded grooves 91 are disposed on the side wall of the guide sleeve 9 at intervals, and the embedded grooves 91 are disposed along the circumferential direction of the guide sleeve 9. The seal ring 10 is embedded in the embedding groove 91, the seal ring 10 in the application is made of rubber materials, and the seal ring 10 is abutted against the side wall of the outer sleeve 1, so that a closed space is formed inside the outer sleeve 1.
With reference to fig. 2 and 3, further, a friction washer 16 is adhered to the end plate 3 at the sliding hole 31, and the friction washer 16 is sleeved on the side wall of the inner sleeve 2 and is adapted to block the gap between the inner sleeve 2 and the wall of the sliding hole 31. In the buffering process, the side wall of the inner sleeve 2 and the inner ring of the friction washer 16 are rubbed with each other to generate heat consumption, so that the buffering effect is further improved.
Referring to fig. 1 and 2, in addition, in order to ensure the smoothness of sliding of each component in the buffering process, the outer sleeve 1, the inner sleeve 2, the end plate 3 and the pushing plate 5 in the present application all adopt structures with circular cross sections, and the adoption of structures with circular cross sections can also make the outer sleeve 1 and the inner sleeve 2 easily affected by external force in the buffering process, and deflection phenomena occur between each other, so that the sliding of an aircraft is affected.
Therefore, the anti-torsion assembly 17 is arranged between the outer sleeve 1 and the inner sleeve 2, the anti-torsion assembly 17 comprises a pair of connecting rods 171, one ends of the connecting rods 171 close to each other are hinged, and one ends of the connecting rods 171 away from each other are respectively hinged on the side walls of the corresponding outer sleeve 1 and inner sleeve 2, so that deflection is not easy to occur between the outer sleeve 1 and the inner sleeve 2 in the circumferential direction.
Referring to fig. 2, specifically, the link 171 includes a connection sleeve 1713, two movable rods 1711 are inserted at two ends of the connection sleeve 1713, a connection spring 1712 is disposed between a pair of movable rods 1711, the connection spring 1712 is welded with the movable rods 1711, the connection spring 1712 is located in the connection sleeve 1713, and a pair of sliding rods continuously press the connection spring 1712 along with the lifting movement of the inner sleeve 2, so as to play a role of buffering.
The embodiment of the application also discloses a landing gear applying the landing gear buffer mechanism.
Referring to figures 1 and 2, a landing gear comprises a connection mount 18 for connection to an aircraft, the connection mount 18 being integrally formed at the top end of the outer sleeve 1, and wheels 19 being mounted at the end of the support post remote from the inner sleeve 2, the wheels 19 supporting the aircraft for taxiing on the ground during take-off and landing of the aircraft. The wheel 19 in the present application adopts a tubeless, dual tread tire construction, also having a cushioning function.
The implementation principle of the undercarriage buffer mechanism and the undercarriage is as follows: during take-off or landing of the aircraft, the wheels 19 will receive an impact from the ground and transmit the impact to the load post 4, thereby driving the inner sleeve 2 to slide in the outer sleeve 1. The first buffer assembly 6, the second buffer assembly 7 and the third buffer assembly 8 stretch and retract under the driving of the pushing plate 5, consume vibration energy in the stretching process, and play a role in buffering impact force received by the force bearing column 4. And the triple buffering is mutually matched, the needed buffering stage number can be automatically selected according to the size of the received impact, the grading buffering is realized, the larger impact can be absorbed, the slight vibration can be filtered, and the buffering effect is good.
The foregoing are all preferred embodiments of the present application, and are not intended to limit the scope of the present application in any way, therefore: all equivalent changes in structure, shape and principle of this application should be covered in the protection scope of this application.
Claims (6)
1. An undercarriage buffer mechanism, characterized in that: the novel sliding sleeve comprises an outer sleeve (1) and an inner sleeve (2), wherein the inner sleeve (2) is slidably arranged in the outer sleeve (1), one end of the outer sleeve (1) is provided with an end plate (3), a sliding hole (31) for the inner sleeve (2) to pass through is formed in the end plate (3), one end of the inner sleeve (2) passes through the sliding hole (31) and then is connected with a bearing column (4), one end, far away from the bearing column (4), of the inner sleeve (2) is provided with a pushing plate (5), and the pushing plate (5) is positioned in the outer sleeve (1);
a first buffer assembly (6) is arranged between the pushing plate (5) and the end plate (3), a second buffer assembly (7) and a third buffer assembly (8) are further arranged in the outer sleeve (1), and the first buffer assembly (6), the second buffer assembly (7) and the third buffer assembly (8) are driven by the pushing plate (5) to stretch out and draw back;
the first buffer assembly (6) comprises a buffer tension spring (61) sleeved on the side wall of the inner sleeve (2), the buffer tension spring (61) is positioned between the pushing plate (5) and the end plate (3), one end of the buffer tension spring (61) is fixed on the pushing plate (5), and the other end of the buffer tension spring is fixed on the end plate (3);
the hydraulic oil storage device is characterized in that a partition plate (11) is arranged in the outer sleeve (1), the partition plate (11) divides the interior of the outer sleeve (1) into a gas storage space (12) and an oil storage space (13), hydraulic oil is filled in the oil storage space (13), damping holes (111) are formed in the partition plate (11) in a penetrating mode, the damping holes (111) are communicated with the gas storage space (12) and the oil storage space (13), and the inner sleeve (2) is located in the oil storage space (13);
the second buffer assembly (7) is arranged in the oil storage space (13), the second buffer assembly (7) comprises a buffer pressure spring (71), one end of the buffer pressure spring (71) is fixed on the partition plate (11), and the other end of the buffer pressure spring is fixed on the pushing plate (5);
a guide rod (14) is arranged in the oil storage space (13), the guide rod (14) is arranged along the expansion and contraction direction of the buffer pressure spring (71), the buffer pressure spring (71) is sleeved on the side wall of the guide rod (14), one end of the guide rod (14) penetrates through the partition plate (11) and then is connected with a limit plate (15), a containing groove (112) for the limit plate (15) to be embedded is formed in the surface, facing away from the buffer pressure spring (71), of the partition plate (11), the limit plate (15) is fixed with the partition plate (11) after being embedded in the containing groove (112) in an adapting mode, and one end, facing away from the limit plate (15), of the guide rod (14) is inserted into the inner sleeve (2) in an adapting mode;
the third buffer assembly (8) is arranged in the gas storage space (12), the third buffer assembly (8) comprises a piston sheet (81), the periphery of the piston sheet (81) is abutted against the inner wall of the gas storage space (12), a return spring (82) is arranged on one side, facing away from the separation plate (11), of the piston sheet (81), one end of the return spring (82) is fixed on the piston sheet (81), and the other end of the return spring is fixed on the inner wall of the outer sleeve (1);
the first buffer component (6), the second buffer component (7) and the third buffer component (8) stretch under the driving of the pushing plate (5), the impact force received by the force bearing column (4) is buffered, the first buffer component (6), the second buffer component (7) and the third buffer component (8) are matched with each other, and the force bearing column (4) drives the first buffer component (6), the second buffer component (7) and/or the third buffer component (8) according to the magnitude of the impact force, so that hierarchical buffering is realized.
2. A landing gear cushioning mechanism according to claim 1, wherein: the guide sleeve (9) is sleeved on and fixed to the pushing plate (5), the guide sleeve (9) is slidably mounted in the outer sleeve (1), an embedded groove (91) is formed in the outer ring of the guide sleeve (9), the embedded groove (91) is formed in the circumferential direction of the pushing plate (5), a sealing ring (10) is embedded in the embedded groove (91), and the sealing ring (10) is abutted to the inner wall of the outer sleeve (1).
3. A landing gear cushioning mechanism according to claim 1, wherein: the end plate (3) is provided with a friction washer (16) at the sliding hole (31), the friction washer (16) is arranged along the circumference of the sliding hole (31) and sleeved on the side wall of the inner sleeve (2), and the friction washer (16) is used for adaptively plugging a gap between the side wall of the inner sleeve (2) and the wall of the sliding hole (31).
4. A landing gear cushioning mechanism according to claim 1, wherein: an anti-torsion assembly (17) is arranged between the inner sleeve (2) and the outer sleeve (1), the anti-torsion assembly (17) comprises a pair of connecting rods (171) hinged with each other, one connecting rod (171) is fixed on the outer sleeve (1), and the other connecting rod (171) is fixed on the inner sleeve (2).
5. A landing gear cushioning mechanism according to claim 4, wherein: the connecting rod (171) comprises a pair of movable rods (1711), a connecting spring (1712) and a connecting sleeve (1713), wherein the connecting spring (1712) is arranged in the connecting sleeve (1713), one end of one movable rod (1711) extends into the connecting sleeve (1713) and is connected with the connecting spring (1712), and the other end of the movable rod is hinged with the movable rod (1711) on the other connecting rod (171);
one end of the other movable rod (1711) extends into the connecting sleeve (1713) from the other end of the connecting sleeve (1713) and is connected with the connecting spring (1712), and the other end is hinged on the corresponding outer sleeve (1) or the inner sleeve (2).
6. A landing gear employing the landing gear cushioning mechanism of claim 1, wherein: including being used for connecting seat (18) of aircraft, connecting seat (18) are fixed outside sleeve (1) keep away from on the one end of bearing post (4), bearing post (4) keep away from one end of inside sleeve (2) is installed organic wheel (19).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105626740A (en) * | 2014-10-27 | 2016-06-01 | 蒋磊 | Multistage damping shock-absorbing apparatus |
| CN206087274U (en) * | 2016-10-13 | 2017-04-12 | 中交遥感载荷（北京）科技有限公司 | Manned undercarriage buffer |
| CN110725883A (en) * | 2019-09-27 | 2020-01-24 | 彩虹无人机科技有限公司 | Energy storage type buffer |
| CN111609073A (en) * | 2020-06-02 | 2020-09-01 | 上海应用技术大学 | Aircraft landing gear buffer |
| CN112249312A (en) * | 2020-10-21 | 2021-01-22 | 郭文坤 | Be used for unmanned aerial vehicle buffering undercarriage |
| CN213414208U (en) * | 2020-11-13 | 2021-06-11 | 北京海利天梦科技有限公司 | Unmanned aerial vehicle undercarriage |
| CN113716028A (en) * | 2021-10-18 | 2021-11-30 | 复旦大学 | Shock attenuation undercarriage and unmanned aerial vehicle |
| CN215554099U (en) * | 2021-08-17 | 2022-01-18 | 天津欧巡科技有限公司 | Unmanned aerial vehicle undercarriage of combatting earthquake |
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2023
- 2023-04-19 CN CN202310421029.6A patent/CN116812142B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105626740A (en) * | 2014-10-27 | 2016-06-01 | 蒋磊 | Multistage damping shock-absorbing apparatus |
| CN206087274U (en) * | 2016-10-13 | 2017-04-12 | 中交遥感载荷（北京）科技有限公司 | Manned undercarriage buffer |
| CN110725883A (en) * | 2019-09-27 | 2020-01-24 | 彩虹无人机科技有限公司 | Energy storage type buffer |
| CN111609073A (en) * | 2020-06-02 | 2020-09-01 | 上海应用技术大学 | Aircraft landing gear buffer |
| CN112249312A (en) * | 2020-10-21 | 2021-01-22 | 郭文坤 | Be used for unmanned aerial vehicle buffering undercarriage |
| CN213414208U (en) * | 2020-11-13 | 2021-06-11 | 北京海利天梦科技有限公司 | Unmanned aerial vehicle undercarriage |
| CN215554099U (en) * | 2021-08-17 | 2022-01-18 | 天津欧巡科技有限公司 | Unmanned aerial vehicle undercarriage of combatting earthquake |
| CN113716028A (en) * | 2021-10-18 | 2021-11-30 | 复旦大学 | Shock attenuation undercarriage and unmanned aerial vehicle |
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| CN116812142A (en) | 2023-09-29 |
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