Mechanical undercarriage for aviation

Abstract

The utility model discloses a mechanical undercarriage for aviation, which relates to the technical field of aviation accessories and comprises a mounting unit, a connecting unit, a first buffer unit and a second buffer unit. The first buffering unit comprises a hydraulic rod fixedly connected to the center of the top of the connecting unit and a sealing piston fixedly connected to the top of the hydraulic rod and used for sealing hydraulic buffering, and the second buffering unit comprises transverse sliding rods arranged in the bottoms of the two ends of the mounting unit. And the second buffer spring sleeves the outer surface of the transverse sliding rod and is used for external buffering. According to the mechanical undercarriage for aviation, impact force is effectively reduced under the buffering action of the first buffering springs and the buffering action of inert gas, impact force buffering can be conducted on the two sides of the undercarriage under the action of the second buffering springs arranged on the two sides at the same time, and damage caused by uneven impact force bearing is avoided; the buffering effect is improved, and the service life of the undercarriage is guaranteed.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation accessories, in particular to an aviation mechanical landing gear. Background Art

[0002] The landing gear is an accessory device at the bottom of the aircraft that supports the aircraft and moves on the ground (water surface) during takeoff and landing or taxiing on the ground (water surface). The landing gear is the only part that supports the entire aircraft. It is an aircraft part that supports the weight of the aircraft and absorbs the impact energy when the aircraft is parked, taxied, and taxiing on the ground. Therefore, it is an indispensable part of the aircraft; without it, the aircraft cannot move on the ground. After the aircraft takes off, the landing gear can be retracted depending on the flight performance.

[0003] Publication (announcement) number: CN215944876U, discloses an aviation mechanical landing gear. First, when an aircraft is falling, a large impact force is generated. The second hydraulic rod will squeeze the inert gas in the buffer cylinder through the output end. At this time, the slider fixedly installed on the output end of the second hydraulic rod slides downward, and the slider squeezes the buffer spring. The buffer spring squeezes the slider to provide an upward buffer force, which disperses the impact force of the output end of the second hydraulic rod, thereby reducing the impact acceleration of the output end of the second hydraulic rod, and then slowing down the speed at which the second hydraulic rod impacts the buffer cylinder. On the one hand, the buffering effect in the buffer cylinder is improved, and on the other hand, the inner wall of the buffer cylinder can adapt to the increase of internal air pressure, thereby avoiding damage to the buffer cylinder caused by the instantaneous increase of air pressure, thereby increasing the service life of the buffer cylinder and reducing the maintenance cost of aircraft inspection.

[0004] In the above patent, the cushioning performance generated by the landing gear during landing is insufficient, and it does not have dynamic cushioning on both sides of the outside. The cushioning effect is relatively poor, and uneven cushioning force is prone to occur, resulting in unequal impact force on both sides and damage. Therefore, it is necessary to provide a mechanical landing gear for aviation. Utility Model Content

[0005] The main purpose of the utility model is to provide an aviation mechanical landing gear, which can effectively solve the problem that the landing gear in the background technology has insufficient buffering performance when landing, does not have dynamic buffering on both sides of the outside, has a relatively poor buffering effect, and is prone to uneven buffering force, resulting in damage due to unequal impact forces on both sides.

[0006] To achieve the above-mentioned purpose, the technical solution adopted by the utility model is as follows: an aviation mechanical landing gear, comprising a mounting unit, and a connecting unit arranged below the bottom of the mounting unit, and also comprising a first buffer unit and a second buffer unit arranged between the mounting unit and the connecting unit;

[0007] The first buffer unit comprises a hydraulic rod fixedly connected to the center of the top of the connection unit, and a sealing piston fixedly connected to the top of the hydraulic rod for sealing the hydraulic buffer;

[0008] The second buffer unit includes a transverse sliding rod arranged inside the bottom of both ends of the mounting unit, and a second buffer spring sleeved on the outer surface of the transverse sliding rod for external buffering.

[0009] Preferably, the mounting unit comprises a mounting plate, two sliding grooves provided at the bottom of both ends of the mounting plate, and a buffer cylinder fixedly connected to the center of the bottom of the mounting plate.

[0010] Preferably, the connecting unit comprises a shaft sleeve block fixedly connected to the bottom end of the hydraulic rod, a shaft bridge passing through both sides of the shaft sleeve block, and rollers movably arranged at both ends of the shaft bridge.

[0011] Preferably, the first buffer unit further comprises a fixing rod fixedly connected to the center of the top of the sealing piston, a pushing plate fixedly connected to the top of the fixing rod, and a first buffer spring sleeved on the outer surface of the fixing rod.

[0012] Preferably, the second buffer unit also includes a first rotating seat fixedly connected to both sides of the sleeve block, a connecting rod connected to the inside of the first rotating seat, a sliding block sleeved on the outer surface of the cross sliding rod, a second rotating seat fixedly connected to the bottom of the sliding block, and a through hole opened at one end of the sliding block.

[0013] Preferably, the top end of the hydraulic rod is located inside the buffer cylinder, the outer diameter of the sealing piston is matched with the inner diameter of the buffer cylinder, the top end of the fixed rod passes through the internal partition of the buffer cylinder, and the first buffer spring is fixedly connected to the bottom of the internal partition of the buffer cylinder and the top of the sealing piston.

[0014] Preferably, the connecting rod is rotatably connected between the first rotating seat and the second rotating seat, the sliding block is movably arranged inside the sliding groove, the inner diameter of the through hole is adapted to the outer diameter of the cross sliding rod, and the second buffer spring is fixedly connected between the inner wall of the sliding groove and one end of the sliding block.

[0015] Compared with the prior art, the utility model has the following beneficial effects:

[0016] In the utility model, the hydraulic rod is forced to move toward the inside of the buffer cylinder, driving the sealing piston to rise inside the buffer cylinder. The sealing piston drives the fixed rod to rise under the sealing action, compressing the first buffer spring located on the outer surface. The rising of the fixed rod squeezes the inert gas filled in the upper area inside the buffer cylinder through the push plate, thereby reducing the impact speed. Under the buffering action of the first buffer spring and the inert gas, the buffering effect of the landing gear is improved, and the impact force is effectively reduced.

[0017] 2. In the utility model, the shaft sleeve block is buffered by the hydraulic rod inside the buffer cylinder, thereby driving the first rotating seat to vibrate with the shaft sleeve block. Through the rotational connection of the first rotating seat, the connecting rod and the second rotating seat, when the landing gear vibrates, the sliding block is driven to slide on the outer surface of the transverse sliding rod inside the sliding groove, compressing the second buffer spring sleeved on the outer surface of the transverse sliding rod. Under the action of the second buffer springs on both sides, the impact force on both sides of the landing gear can be buffered, avoiding damage caused by uneven impact force, improving the buffering effect, and ensuring the service life of the landing gear. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a three-dimensional structural schematic diagram of the utility model;

[0019] Figure 2 This is a schematic diagram of the front view internal cross-section structure of the utility model;

[0020] Figure 3 For this utility model Figure 2 The enlarged structural diagram at A in the middle;

[0021] Figure 4 For this utility model Figure 2 Enlarged structural diagram at B in the middle.

[0022] In the figure:

[0023] 100, mounting unit; 101, mounting plate; 102, sliding groove; 103, buffer cylinder;

[0024] 200, connecting unit; 201, shaft bridge; 202, shaft sleeve block; 203, roller;

[0025] 300, first buffer unit; 301, hydraulic rod; 302, sealing piston; 303, fixed rod; 304, push plate; 305, first buffer spring;

[0026] 400, second buffer unit; 401, first rotating seat; 402, connecting rod; 403, sliding block; 404, second rotating seat; 405, through hole; 406, horizontal sliding rod; 407, second buffer spring. DETAILED DESCRIPTION Example

[0027] Please refer to Figure 1 — Figure 4 As shown, the utility model is an aviation mechanical landing gear, comprising a mounting unit 100, and a connecting unit 200 disposed below the bottom of the mounting unit 100, and further comprising a first buffer unit 300 and a second buffer unit 400 disposed between the mounting unit 100 and the connecting unit 200;

[0028] The second buffer unit 400 includes a transverse sliding rod 406 disposed inside the bottom of both ends of the mounting unit 100 , and a second buffer spring 407 sleeved on the outer surface of the transverse sliding rod 406 for external buffering.

[0029] like Figure 1 — Figure 4 As shown, the mounting unit 100 includes a mounting plate 101, two sliding grooves 102 opened at the bottom of both ends of the mounting plate 101, and a buffer cylinder 103 fixedly connected at the bottom center of the mounting plate 101. The mounting plate 101 is used to be installed on the bottom of the aircraft. Through the sliding grooves 102 opened at the bottom of both ends of the mounting plate 101, the impact force generated when the landing gear lands can be buffered on both sides to reduce the impact force. The buffer cylinder 103 set at the bottom center is used for the direct impact force generated by the landing gear.

[0030] like Figure 1 and Figure 2 The connecting unit 200 shown includes a bushing block 202 fixedly connected to the bottom end of the hydraulic rod 301, an axle bridge 201 passing through both sides of the bushing block 202, and rollers 203 movably arranged at both ends of the axle bridge 201. The rollers 203 movably connected at both ends of the axle bridge 201 are used for the sliding of the aircraft, and the bushing block 202 sleeved at the center of the axle bridge 201 facilitates the connection of the buffer structure.

[0031] like Figure 1 — Figure 3 As shown, the first buffer unit 300 includes a hydraulic rod 301 fixedly connected at the top center of the connecting unit 200, and a sealing piston 302 fixedly connected to the top of the hydraulic rod 301 for sealing the hydraulic buffer. The first buffer unit 300 also includes a fixed rod 303 fixedly connected at the top center of the sealing piston 302, a push plate 304 fixedly connected to the top of the fixed rod 303, and a first buffer spring 305 sleeved on the outer surface of the fixed rod 303. The top of the hydraulic rod 301 is located inside the buffer cylinder 103, the outer diameter of the sealing piston 302 is matched with the inner diameter of the buffer cylinder 103, the top of the fixed rod 303 passes through the internal partition of the buffer cylinder 103, and the first buffer spring 305 is fixedly connected to the bottom of the internal partition of the buffer cylinder 103 and the top of the sealing piston 302.

[0032] Working principle: When the aircraft lands, the roller 203 of the landing gear first contacts the ground, bearing the weight of the aircraft while generating an impact force. Under the action of the impact force, the hydraulic rod 301 is forced to move toward the inside of the buffer cylinder 103, driving the sealing piston 302 to rise inside the buffer cylinder 103. The sealing piston 302 drives the fixed rod 303 to rise under the sealing action, compressing the first buffer spring 305 located on the outer surface. The rise of the fixed rod 303 squeezes the inert gas filled in the upper area inside the buffer cylinder 103 through the push plate 304, reducing the impact speed. Under the buffering action of the first buffer spring 305 and the inert gas, the buffering effect of the landing gear is improved, and the impact force is effectively reduced. Example

[0033] Please refer to Figure 1 — Figure 4 As shown, the utility model is an aviation mechanical landing gear, comprising a mounting unit 100, and a connecting unit 200 disposed below the bottom of the mounting unit 100, and further comprising a first buffer unit 300 and a second buffer unit 400 disposed between the mounting unit 100 and the connecting unit 200;

[0034] The first buffer unit 300 includes a hydraulic rod 301 fixedly connected to the top center of the connection unit 200 , and a sealing piston 302 fixedly connected to the top of the hydraulic rod 301 for sealing hydraulic buffering.

[0035] like Figure 1 — Figure 4 As shown, the mounting unit 100 includes a mounting plate 101, two sliding grooves 102 opened at the bottom of both ends of the mounting plate 101, and a buffer cylinder 103 fixedly connected at the bottom center of the mounting plate 101. The mounting plate 101 is used to be installed on the bottom of the aircraft. Through the sliding grooves 102 opened at the bottom of both ends of the mounting plate 101, the impact force generated when the landing gear lands can be buffered on both sides to reduce the impact force. The buffer cylinder 103 set at the bottom center is used for the direct impact force generated by the landing gear.

[0036] like Figure 1 and Figure 2 The connecting unit 200 shown includes a bushing block 202 fixedly connected to the bottom end of the hydraulic rod 301, an axle bridge 201 passing through both sides of the bushing block 202, and rollers 203 movably arranged at both ends of the axle bridge 201. The rollers 203 movably connected at both ends of the axle bridge 201 are used for the sliding of the aircraft, and the bushing block 202 sleeved at the center of the axle bridge 201 facilitates the connection of the buffer structure.

[0037] like Figure 1 , Figure 2 and Figure 4As shown, the second buffer unit 400 includes a transverse sliding rod 406 arranged inside the bottom of both ends of the mounting unit 100, and a second buffer spring 407 for external buffering arranged on the outer surface of the transverse sliding rod 406. The second buffer unit 400 also includes a first rotating seat 401 fixedly connected to both sides of the shaft sleeve block 202, a connecting rod 402 connected to the inside of the first rotating seat 401, a sliding block 403 arranged on the outer surface of the transverse sliding rod 406, a second rotating seat 404 fixedly connected to the bottom of the sliding block 403, and a through hole 405 extending through one end of the sliding block 403. The connecting rod 402 is rotatably connected between the first rotating seat 401 and the second rotating seat 404. The sliding block 403 is movably arranged inside the sliding groove 102. The inner diameter of the through hole 405 is adapted to the outer diameter of the transverse sliding rod 406. The second buffer spring 407 is fixedly connected between the inner wall of the sliding groove 102 and one end of the sliding block 403.

[0038] Working principle: When the aircraft lands, the roller 203 of the landing gear first contacts the ground, bearing the weight of the aircraft while generating an impact force. Under the action of the impact force, the sleeve block 202 moves and buffers inside the buffer cylinder 103 through the hydraulic rod 301, thereby driving the first rotating seat 401 to vibrate following the sleeve block 202. Through the rotation connection of the first rotating seat 401, the connecting rod 402 and the second rotating seat 404, when the landing gear vibrates, it drives the sliding block 403 to slide on the outer surface of the transverse sliding rod 406 inside the sliding groove 102, compressing the second buffer spring 407 sleeved on the outer surface of the transverse sliding rod 406. Under the action of the second buffer springs 407 on both sides, the impact force on both sides of the landing gear can be buffered, avoiding damage caused by uneven impact force, improving the buffering effect, and ensuring the service life of the landing gear.

Claims

1. An aviation mechanical landing gear, comprising a mounting unit (100), and a connecting unit (200) arranged below the bottom of the mounting unit (100), characterized in that: It also includes a first buffer unit (300) and a second buffer unit (400) arranged between the mounting unit (100) and the connecting unit (200); The first buffer unit (300) comprises a hydraulic rod (301) fixedly connected to the center of the top of the connection unit (200), and a sealing piston (302) fixedly connected to the top of the hydraulic rod (301) and used for sealing hydraulic buffering; The second buffer unit (400) comprises a transverse sliding rod (406) arranged inside the bottom of both ends of the mounting unit (100), and a second buffer spring (407) sleeved on the outer surface of the transverse sliding rod (406) for external buffering.

2. The mechanical landing gear for aviation according to claim 1, characterized in that: The mounting unit (100) comprises a mounting plate (101), two sliding grooves (102) provided at the bottom of both ends of the mounting plate (101), and a buffer cylinder (103) fixedly connected to the center of the bottom of the mounting plate (101).

3. The mechanical landing gear for aviation according to claim 2, characterized in that: The connection unit (200) comprises a shaft sleeve block (202) fixedly connected to the bottom end of the hydraulic rod (301), a shaft bridge (201) passing through both sides of the shaft sleeve block (202), and rollers (203) movably arranged at both ends of the shaft bridge (201).

4. The mechanical landing gear for aviation according to claim 2, characterized in that: The first buffer unit (300) further comprises a fixing rod (303) fixedly connected to the top center of the sealing piston (302), a pushing plate (304) fixedly connected to the top of the fixing rod (303), and a first buffer spring (305) sleeved on the outer surface of the fixing rod (303).

5. The mechanical landing gear for aviation according to claim 3, characterized in that: The second buffer unit (400) further comprises a first rotating seat (401) fixedly connected to both sides of the shaft sleeve block (202), a connecting rod (402) connected to the inside of the first rotating seat (401), a sliding block (403) sleeved on the outer surface of the transverse sliding rod (406), a second rotating seat (404) fixedly connected to the bottom of the sliding block (403), and a through hole (405) extending through one end of the sliding block (403).

6. The mechanical landing gear for aviation according to claim 4, characterized in that: The top end of the hydraulic rod (301) is located inside the buffer cylinder (103), the outer diameter of the sealing piston (302) is matched with the inner diameter of the buffer cylinder (103), the top end of the fixing rod (303) passes through the inner diaphragm of the buffer cylinder (103), and the first buffer spring (305) is fixedly connected to the bottom of the inner diaphragm of the buffer cylinder (103) and the top of the sealing piston (302).

7. The mechanical landing gear for aviation according to claim 5, characterized in that: The connecting rod (402) is rotatably connected between the first rotating seat (401) and the second rotating seat (404), the sliding block (403) is movably arranged inside the sliding groove (102), the inner diameter of the through hole (405) is matched with the outer diameter of the horizontal sliding rod (406), and the second buffer spring (407) is fixedly connected between the inner wall of the sliding groove (102) and one end of the sliding block (403).

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