CN211281454U - Reinforcing apparatus of supporting leg when aircraft falls to ground - Google Patents
Reinforcing apparatus of supporting leg when aircraft falls to ground Download PDFInfo
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- CN211281454U CN211281454U CN201921294163.XU CN201921294163U CN211281454U CN 211281454 U CN211281454 U CN 211281454U CN 201921294163 U CN201921294163 U CN 201921294163U CN 211281454 U CN211281454 U CN 211281454U
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- supporting leg
- backup pad
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Abstract
The utility model discloses a reinforcing apparatus of supporting leg when aircraft falls to ground relates to aircraft supporting leg technical field, specifically includes the backup pad to and set up buffer and reinforcing plate in the backup pad below, the middle part fixed mounting on backup pad top has aircraft supporting leg hydraulic stem, and the well cavity of mutual symmetry is all seted up to the both sides at backup pad top, the top and the outside air of well cavity are linked together. This reinforcing apparatus of supporting leg when aircraft falls to ground, through sliding block and the elastic component that sets up the buffering in the inside of backup pad, the pressure that aircraft supporting leg hydraulic stem received when falling aircraft cushions, and the both sides of aircraft supporting leg hydraulic stem are consolidated through setting up of anchor strut simultaneously for aircraft supporting leg hydraulic stem supports when descending more stable, has slowed down the wearing and tearing between the supporting leg part, and then has prolonged the life of supporting leg.
Description
Technical Field
The utility model relates to an aircraft supporting leg technical field specifically is a reinforcing apparatus of supporting leg when aircraft falls to the ground.
Background
An aircraft refers to an aircraft that has one or more engines and a power device for generating forward thrust or pull force, generates lift force by fixed wings of a fuselage, and flies heavier than air in the atmosphere, and the aircraft is the most common type of fixed wing aircraft, and the aircraft mainly comprises: the wing, the fuselage, the empennage, the landing gear, the power device and the like are taken as the landing gear of the airplane, and therefore, the research on the landing gear is needed as an important device for the landing of the airplane.
The supporting legs and the rollers of the airplane are supported and damped mostly by hydraulic rods or hydraulic devices in the prior airplane landing device, the downward pressure of the airplane is large when the airplane lands at a high speed, the acting force of the supporting legs and the hydraulic rods of the airplane is large, secondary reinforcement and buffering are not carried out on the supporting legs and the airplane wheels of the airplane, if the airplane is used for a long time, the supporting legs and the rollers of the airplane are abraded and damaged seriously, and the service life of the airplane are influenced.
SUMMERY OF THE UTILITY MODEL
The utility model provides a reinforcing apparatus of supporting leg when aircraft falls to the ground has solved the problem that above-mentioned background art provided.
In order to achieve the above purpose, the utility model discloses a following technical scheme realizes: a reinforcing device for a supporting leg when an airplane lands on the ground comprises a supporting plate, a buffering device and a reinforcing plate, wherein the buffering device and the reinforcing plate are arranged below the supporting plate, the middle part of the top end of the supporting plate is fixedly provided with an airplane supporting leg hydraulic rod, two symmetrical hollow cavities are formed in two sides of the top of the supporting plate, the top of each hollow cavity is communicated with the outside air, the inner cavities of the two supporting plates are fixedly connected with sliding rods positioned in the hollow cavities, the outside of each sliding rod is movably sleeved with an elastic piece, the outside of each sliding rod is movably sleeved with a sliding block positioned at one end of the elastic piece, the top of each sliding block is fixedly connected with a connecting block, the top of each connecting block extends to the outside of the supporting plate, the inside of each connecting block is movably connected with the bottom end of a reinforcing rod through a, one side of the connecting block is fixedly connected with the bottom of one side of the hydraulic rod of the aircraft supporting leg, two buffer devices are fixedly arranged in the middle of the bottom end of the supporting plate, and the bottoms of the two buffer devices are fixedly connected with a connecting sleeve, the inside of the connecting sleeve is fixedly sleeved with a connecting rod through a bearing, two ends of the connecting rod extend to the outside of the connecting sleeve and are fixedly arranged with the inside of the rolling wheel through a bearing, two sides of the bottom of the supporting plate are fixedly provided with mutually symmetrical positioning plates, the insides of the two positioning plates are movably connected through reinforcing plates, the number of the reinforcing plates is three to six, the length of the reinforcing plates is reduced from top to bottom at one time, three to six reinforcing plates are fixedly sleeved through U-shaped fastening screws, the reinforcing plate inside the positioning plate is fixedly sleeved through the U-shaped fastening screw rod, and the bottom of the reinforcing plate is in contact with the top of the connecting sleeve and is fixedly sleeved through the U-shaped fastening screw rod.
Optionally, the buffer device comprises an adapting rod, a reinforcing sleeve and an expansion spring, the top of the adapting rod is fixedly installed at the middle of the bottom end of the supporting plate, the reinforcing sleeve is sleeved on the outer portion of the bottom end of the adapting rod in a movable mode, the bottom end of the reinforcing sleeve is fixedly connected with the top of the connecting sleeve, and the bottom of the inner cavity of the reinforcing sleeve is in transmission connection with the bottom end of the adapting rod through the expansion spring.
Optionally, the size of cavity is mutually adapted with the size of sliding block in the backup pad is inside, and well cavity top link up to the width value at backup pad top and the width value of connecting block the same.
Optionally, the reinforcing plate is arc-shaped, and rubber pad discs are arranged at the contact parts of the two ends of the reinforcing plate and the inside of the positioning plate.
The utility model discloses possess following beneficial effect:
1. this reinforcing apparatus of supporting leg when aircraft falls to ground, through sliding block and the elastic component that sets up the buffering in the inside of backup pad, the pressure that aircraft supporting leg hydraulic stem received when falling aircraft cushions, and the both sides of aircraft supporting leg hydraulic stem are consolidated through setting up of anchor strut simultaneously for aircraft supporting leg hydraulic stem supports when descending more stable, has slowed down the wearing and tearing between the supporting leg part, and then has prolonged the life of supporting leg.
2. This reinforcing apparatus of supporting leg when aircraft falls to ground sets up buffer and rolls through the bottom at the backup pad and connects between the wheel to and set up the reinforcing plate between backup pad and roll wheel, can obtain the buffering when making aircraft ground connection, can slow down the effort that the aircraft acted on the roll wheel simultaneously, the effectual pressure and the wearing and tearing that have reduced the roll wheel, and then improved its life and year.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a cross-sectional view of the connecting rod of the present invention;
fig. 3 is a top view of the support plate of the present invention.
In the figure: 1. a support plate; 2. an airplane support leg hydraulic rod; 3. a hollow cavity; 4. a slide bar; 5. a slider; 6. connecting blocks; 7. a shaft sleeve rod; 8. a reinforcing rod; 9. positioning a plate; 10. a buffer device; 101. a bearing rod; 102. reinforcing the sleeve; 103. a tension spring; 11. a connecting sleeve; 12. a connecting rod; 13. a rolling wheel; 14. a reinforcing plate; 15. u-shaped fastening screw.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1 to 3, the present invention provides a technical solution: a reinforcing device for supporting legs when an airplane lands on the ground comprises supporting plates 1, a buffer device 10 and a reinforcing plate 14, wherein the buffer device 10 and the reinforcing plate 14 are arranged below the supporting plates 1, the middle part of the top end of each supporting plate 1 is fixedly provided with an airplane supporting leg hydraulic rod 2, the two sides of the top of each supporting plate 1 are respectively provided with a hollow cavity 3 which are symmetrical to each other, the top of each hollow cavity 3 is communicated with the outside air, the inner cavities of the two supporting plates 1 are fixedly connected with a sliding rod 4 which is positioned inside the hollow cavity 3, the outside of the sliding rod 4 is movably sleeved with an elastic part, the outside of the sliding rod 4 is sleeved with a sliding block 5 which is positioned at one end of the elastic part, the top of the sliding block 5 is fixedly connected with a connecting block 6, the top end of the connecting block 6 extends to the outside of the supporting plates 1, the inside of the connecting block 6 is movably connected with the bottom end of a, the safety of the landing aircraft is ensured, the top end of a reinforcing rod 8 is movably connected with the inside of a connecting block 6 through a shaft sleeve rod 7, one side of the connecting block 6 is fixedly connected with the bottom of one side of an aircraft supporting leg hydraulic rod 2, two buffering devices 10 are fixedly installed in the middle of the bottom end of a supporting plate 1, the bottoms of the two buffering devices 10 are fixedly connected with a connecting sleeve 11, the inside of the connecting sleeve 11 is fixedly sleeved with a connecting rod 12 through a bearing, two ends of the connecting rod 12 extend to the outside of the connecting sleeve 11 and are fixedly installed with the inside of a rolling wheel 13 through a bearing, two symmetrical positioning plates 9 are fixedly installed on two sides of the bottom of the supporting plate 1, the insides of the two positioning plates 9 are movably connected through reinforcing plates 14, the number of the reinforcing plates 14 is three to six, the acting force at the bottom of the supporting plate 1 can be buffered through the reinforcing plates 14, and the supporting force between, and the length of reinforcing plate 14 once reduces from top to bottom, and three to six reinforcing plates 14 pass through the fixed suit of U-shaped fastening screw 15, and the reinforcing plate 14 of locating plate 9 inside passes through the fixed suit of U-shaped fastening screw 15, and the bottom of reinforcing plate 14 contacts with the top of connecting sleeve 11 and passes through the fixed suit of U-shaped fastening screw 15.
Wherein, buffer 10 includes adapting rod 101, reinforcing sleeve 102 and expanding spring 103, the middle part fixed mounting of adapting rod 101's top and the 1 bottom of backup pad, the outside movable sleeve of adapting rod 101's bottom is equipped with reinforcing sleeve 102, reinforcing sleeve 102's bottom and connecting sleeve 11's top fixed connection, reinforcing sleeve 102 inner chamber's bottom is passed through expanding spring 103 and is connected with being located adapting rod 101 bottom transmission, can slow down the effort that the aircraft acted on rolling wheel 13, the effectual pressure and the wearing and tearing that have reduced rolling wheel 13, and then its life and year are improved.
Wherein, the big or small looks adaptation of cavity 3 in backup pad 1 inside and sliding block 5, and well cavity 3 top link up the width value to 1 top of backup pad and the width value of connecting block 6 is the same, sliding block 5 and the elastic component through setting up the buffering in backup pad 1 inside, the aircraft supporting leg hydraulic stem 2 cushions the pressure that receives when falling to the aircraft, consolidate aircraft supporting leg hydraulic stem 2's both sides through setting up of anchor strut 8 simultaneously, make aircraft supporting leg hydraulic stem 2 support when descending more stable, the wearing and tearing between the supporting leg part have been slowed down, and then the life of supporting leg has been prolonged.
Wherein, reinforcing plate 14's shape is circular-arc, and reinforcing plate 14 both ends are equipped with the rubber saucer with locating plate 9 inside contact part, and reinforcing plate 14 has certain rigidity and restoring force, has guaranteed that the aircraft can cushion it when descending, can slow down the effort to rolling wheel 13 simultaneously.
In conclusion, this reinforcing apparatus for supporting leg when aircraft lands, when the aircraft lands, at first the aircraft acts on aircraft supporting leg hydraulic stem 2 with the effort, when aircraft supporting leg hydraulic stem 2 descends because pressure is too big, aircraft supporting leg hydraulic stem 2 divides the effort to the anchor strut 8 of its both sides this moment, anchor strut 8 will receive the effort on connecting block 6 and sliding block 5 for sliding block 5 slides on slide bar 4, extrude the elastic component simultaneously, cushion the aircraft once, the aircraft acts on backup pad 1 with the effort simultaneously, backup pad 1 is with its pressure that receives, transmit to locating plate 9 and reinforcing plate 14 and buffer 10, reinforcing plate 14 supports and cushions roller 13, simultaneously slows down the pressure of backup pad 1 through the inside expanding spring 103 of reinforcing sleeve 102, can.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention; the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance, and furthermore, unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (4)
1. The utility model provides a reinforcing apparatus of supporting leg when aircraft falls to ground, includes backup pad (1) to and set up in buffer (10) and reinforcing plate (14) of backup pad (1) below, its characterized in that: the aircraft supporting leg hydraulic rod (2) is fixedly installed in the middle of the top end of the supporting plate (1), the two sides of the top of the supporting plate (1) are respectively provided with a hollow cavity (3) which are symmetrical to each other, the top of the hollow cavity (3) is communicated with the outside air, the inner cavities of the two supporting plates (1) are fixedly connected with a sliding rod (4) which is positioned inside the hollow cavity (3), the outside of the sliding rod (4) is movably sleeved with an elastic part, the outside of the sliding rod (4) is movably sleeved with a sliding block (5) which is positioned at one end of the elastic part, the top of the sliding block (5) is fixedly connected with a connecting block (6), the top end of the connecting block (6) extends to the outside of the supporting plate (1), the inside of the connecting block (6) is movably connected with the bottom end of a reinforcing rod (8) through a shaft sleeve rod (7), and the top end of the reinforcing rod (8) is, and one side of the connecting block (6) is fixedly connected with the bottom of one side of the aircraft supporting leg hydraulic rod (2), the middle part of the bottom end of the supporting plate (1) is fixedly provided with two buffering devices (10), the bottom of the two buffering devices (10) is fixedly connected with one connecting sleeve (11), the inside of the connecting sleeve (11) is fixedly provided with a connecting rod (12) through a bearing, the two ends of the connecting rod (12) extend to the outside of the connecting sleeve (11) and are fixedly arranged with the inside of a rolling wheel (13) through a bearing, two symmetrical positioning plates (9) are fixedly arranged on the two sides of the bottom of the supporting plate (1), the insides of the two positioning plates (9) are movably connected through reinforcing plates (14), the number of the reinforcing plates (14) is three to six, the length of the reinforcing plates (14) is reduced from top to bottom once, the reinforcing plates (14) are fixedly sleeved through U-shaped fastening screws (15), the positioning plate is characterized in that a reinforcing plate (14) in the positioning plate (9) is fixedly sleeved through a U-shaped fastening screw rod (15), and the bottom of the reinforcing plate (14) is in contact with the top of the connecting sleeve (11) and is fixedly sleeved through the U-shaped fastening screw rod (15).
2. An aircraft landing support leg reinforcement as claimed in claim 1, wherein: buffer (10) are including adapting rod (101), reinforcing sleeve (102) and expanding spring (103), the middle part fixed mounting of the top of adapting rod (101) and backup pad (1) bottom, the outside movable sleeve of the bottom of adapting rod (101) is equipped with reinforcing sleeve (102), the bottom of reinforcing sleeve (102) and the top fixed connection of connecting sleeve (11), the bottom of reinforcing sleeve (102) inner chamber is passed through expanding spring (103) and is located adapting rod (101) bottom transmission and be connected.
3. An aircraft landing support leg reinforcement as claimed in claim 1, wherein: the size of cavity (3) is the same with the size looks adaptation of sliding block (5) in backup pad (1) inside, and well cavity (3) top link up the width value at backup pad (1) top and the width value of connecting block (6) are the same.
4. An aircraft landing support leg reinforcement as claimed in claim 1, wherein: the reinforcing plate (14) is arc-shaped, and rubber pad discs are arranged at the contact parts of the two ends of the reinforcing plate (14) and the inside of the positioning plate (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921294163.XU CN211281454U (en) | 2019-08-12 | 2019-08-12 | Reinforcing apparatus of supporting leg when aircraft falls to ground |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921294163.XU CN211281454U (en) | 2019-08-12 | 2019-08-12 | Reinforcing apparatus of supporting leg when aircraft falls to ground |
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| Publication Number | Publication Date |
|---|---|
| CN211281454U true CN211281454U (en) | 2020-08-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921294163.XU Active CN211281454U (en) | 2019-08-12 | 2019-08-12 | Reinforcing apparatus of supporting leg when aircraft falls to ground |
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| CN (1) | CN211281454U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116443241A (en) * | 2023-04-25 | 2023-07-18 | 南京儒一航空机械装备有限公司 | Shock attenuation aircraft undercarriage |
-
2019
- 2019-08-12 CN CN201921294163.XU patent/CN211281454U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116443241A (en) * | 2023-04-25 | 2023-07-18 | 南京儒一航空机械装备有限公司 | Shock attenuation aircraft undercarriage |
| CN116443241B (en) * | 2023-04-25 | 2023-10-17 | 南京儒一航空机械装备有限公司 | Shock attenuation aircraft undercarriage |
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