阅读说明：本技术 一种飞机紧急起落架 (Emergency landing gear of airplane ) 是由 王允 于 2020-12-24 设计创作，主要内容包括：本发明公开了一种飞机紧急起落架,包含上联合收纳仓、液压连杆机构、弹簧缓冲机构、防撞照明机构和轮胎转动机构,上联合收纳仓进行收纳起落架,液压连杆机构进行驱动起落架,弹簧缓冲机构作为紧急下落缓冲,防撞照明机构,作为驱散遮挡物和照明作用,轮胎转动机构作为起落架的滑行运动结构,通过弹簧缓冲机构和防撞照明机构进行紧急下落的缓冲和照明,可以应对各种各样的飞机紧急起落状况。本发明的一种飞机紧急起落架,使用单弹簧进行缓冲,解决了紧急情况油缸炸裂造成的起落架失效,且起落架可以使用弹簧辅助减震和在油路破坏情况的减震使用,保证飞机的安全紧急起落。(The invention discloses an aircraft emergency landing gear, which comprises an upper combined storage bin, a hydraulic link mechanism, a spring buffer mechanism, an anti-collision lighting mechanism and a tire rotating mechanism, wherein the upper combined storage bin is used for storing the landing gear, the hydraulic link mechanism is used for driving the landing gear, the spring buffer mechanism is used for buffering emergency falling, the anti-collision lighting mechanism is used for dispersing shelters and lighting, the tire rotating mechanism is used as a sliding motion structure of the landing gear, and the spring buffer mechanism and the anti-collision lighting mechanism are used for buffering and lighting the emergency falling, so that various aircraft emergency landing conditions can be met. According to the emergency landing gear of the airplane, the single spring is used for buffering, the problem that the landing gear fails due to the fact that an oil cylinder bursts in an emergency situation is solved, the landing gear can be used for spring-assisted damping and damping in the case of oil circuit damage, and the safe emergency landing of the airplane is guaranteed.)

1. The utility model provides an aircraft emergency landing gear, includes and unites collecting storage (1), hydraulic link mechanism (2), spring buffer gear (3), crashproof lighting mechanism (4) and tire slewing mechanism (5), its characterized in that:

the upper combined storage bin (1) comprises: a round rod (107) and a cylinder output shaft (109);

the hydraulic link mechanism (2) comprises: a large bracket (206) and an upper rotating plate (218);

the spring buffer mechanism (3) comprises: a pressure spring (301) and a pendulum cylinder (305);

the anti-collision lighting mechanism (4) comprises: a buffer frame (403) and a large friction head (407);

the tire rotating mechanism (5) comprises: a locking link (503) and a pressure shaft 516;

the round rod (107) is rotatably installed on a central hole of the large support (206), the oil cylinder output shaft (109) is fixedly installed on the upper surface of the upper rotating plate (218), the pressure spring (301) is fixedly installed in the central hole of the large support (206), the buffer frame (403) is fixedly installed on the outer side of the swinging cylinder (305), the large friction head (407) is fixedly installed on the outer side of the large support (206), the locking connecting rod (503) is fixedly installed on the outer side of the large support (206), and the pressure shaft (516) is fixedly installed on the lower surface of the pressure spring (301).

2. An aircraft emergency landing gear according to claim 1, wherein: the upper combined storage bin (1) also comprises a tail mounting seat (101), a tail seat rotating shaft (102), an oil cylinder tail seat (103), a storage bin plate (104), a round rod mounting seat 105, a round rod rotating shaft (106) and an oil cylinder outer sleeve (108), the tail mounting seat (101) is fixedly mounted on the upper surface of the storage bin plate (104), the tail base rotating shaft (102) is rotatably mounted in a hole of the tail mounting seat (101), the oil cylinder tailstock (103) is rotatably mounted on the upper surface of the tail base rotating shaft (102), the oil cylinder outer sleeve (108) is fixedly mounted on the oil cylinder tailstock (103), an oil cylinder output shaft (109) is rotatably mounted in a hole of the oil cylinder outer sleeve (108), the round rod mounting seat (105) is fixedly mounted on the storage bin plate (104), the round rod (107) is rotatably mounted on the round rod rotating shaft (106), and the round rod rotating shaft (106) is rotatably mounted on the round rod mounting seat (105).

3. An aircraft emergency landing gear according to claim 2, wherein: the hydraulic link mechanism (2) further comprises a rotating rod (201), a rotating shifting fork (202), a shifting fork shaft (203), a shifting fork sleeve (204), a disk-shaped rotating shaft (205), a headlamp base (207), a headlamp bulb (208), a headlamp cover (209), a bottom rotating shaft (210), a lower swing rod (211), a front swing rod (212), a front swing rotating shaft (213), an upper swing rotating shaft (214), a front swing base (215), an upper swing rod (216), an upper rotating shaft (217) and a support cover (219), wherein the rotating rod (201) is rotatably arranged on the rotating shifting fork (202), the shifting fork shaft (203) is slidably arranged on the upper surface of the rotating shifting fork (202), the shifting fork sleeve (204) is fixedly arranged on two sides of the rotating shifting fork (202), the disk-shaped rotating shaft (205) is fixedly arranged in a hole of the shifting fork sleeve (204), a large lamp holder (207) is rotatably arranged on a large support (206), and the large lamp bulb (208) is rotatably arranged on the, the large lampshade (209) is fixedly installed on a large lamp holder (207), the bottom rotating shaft (210) is rotatably installed on a central hole of the lower swing rod (211), the front swing rod (212) is rotatably installed on the front swing rotating shaft (213), the lower swing rod (211) is rotatably installed on the front swing rotating shaft (213), the upper swing rotating shaft (214) is rotatably installed in a hole of the front swing seat (215), the front swing seat (215) is fixedly installed on the upper swing rod (216), the upper rotating shaft (217) is rotatably installed in a hole of the upper swing rod (216), the upper rotating shaft (217) is rotatably installed in a central hole of the upper rotating plate (218), and the support cover (219) is fixedly installed on the upper surface of the large support (206).

4. An aircraft emergency landing gear according to claim 3, wherein: the spring buffer mechanism (3) further comprises a swing shaft (302), a swing sheet (303), a pressure base (304), a support rotating shaft (306), a small lamp cover (307) and a small lamp bulb (308), the swing shaft (302) is rotatably installed in a central hole of the swing sheet (303), the pressure spring (301) is fixedly installed in a hole of the pressure base (304), the support rotating shaft (306) is rotatably installed at the upper end of a swing cylinder (305), the swing cylinder (305) is fixedly installed on the pressure base (304), the small lamp cover (307) is rotatably installed at the upper end of the pressure base (304), and the small lamp bulb (308) is rotatably installed on the central hole of the small lamp cover (307).

5. An aircraft emergency landing gear according to claim 4, wherein: the anti-collision lighting mechanism (4) also comprises a small buffer (401), a small buffer pad (402), a small buffer rod (404), a small friction head (405), a buffer spring (406), a large buffer rod (408), a buffer seat (409), a large buffer head (410) and a large buffer pad 411, small buffer (401) is fixedly installed in small buffer (402) hole, small buffer (402) is fixedly installed in buffer frame (403) hole, small buffer rod (404) is fixedly installed in buffer frame (403) hole, small friction head (405) is installed on small buffer rod (404) shaft in a rotating mode, large friction head (407) is installed in large buffer rod (408) hole in a rotating mode, buffer spring (406) is installed on the upper surface of buffer seat (409) in a rotating mode, buffer seat (409) is installed in buffer frame (403) hole in a rotating mode, and large buffer head (410) and large buffer (411) are installed on large buffer rod (408) shaft in a rotating mode.

6. An aircraft emergency landing gear according to claim 5, wherein: the tire rotating mechanism (5) further comprises a small locking bolt (501), a small flange cap (502), a large flange cap (504), a left connecting rod (505), a bushing (506), a large locking bolt (507), a right connecting rod (508), a connecting block (509), a wheel hub (510), a tire (511), a wheel axle seat (512), a balancing rod (513), a wheel rotating shaft (514) and a supporting sleeve (515), wherein the small locking bolt (501) is fixedly arranged in a hole of the locking connecting rod (503), the small flange cap (502) is fixedly arranged on the small locking bolt (501), the large flange cap (504) is rotatably arranged on the large locking bolt 507, the large locking bolt (507) is rotatably arranged in the hole of the bushing (506), the left connecting rod (505) and the right connecting rod (508) are rotatably arranged on two sides of the bushing (506), the connecting block (509) is fixedly arranged on the inner sides of the left connecting rod (505) and the right connecting rod (508), the wheel hub (510) is rotatably mounted on a wheel rotating shaft (514), the wheel rotating shaft (514) is fixedly mounted on a wheel axle seat (512), a tire (511) is fixedly mounted on the wheel hub (510), a balancing rod (513) is rotatably mounted on the wheel axle seat (512), a supporting sleeve (515) is rotatably mounted on the wheel rotating shaft (514), and a pressure shaft (516) is fixedly mounted on the upper surface of the supporting sleeve (515).

7. An aircraft emergency landing gear according to claim 1, wherein: the round rod (107) is rotatably arranged on the inner wall of the large support (206), and the round rod (107) is also contacted with the pressure spring (301).

8. An aircraft emergency landing gear according to claim 1, wherein: the pressure spring (301) is rotatably arranged in the hole of the large bracket (206) to form a sliding fit, and the large lamp holder (207) is also contacted with the pressure shaft (516).

9. An aircraft emergency landing gear according to claim 1, wherein: the buffer spring (406) is also contacted with a large friction head 407, and the buffer spring (406) is also contacted with a buffer seat (409).

10. An aircraft emergency landing gear according to claim 1, wherein: the small locking bolt (501) is also rotatably installed with the pressure base (304), and the small bulb (308) and the large bulb (208) are connected in parallel, so that the large bulb (208) can be used when the small bulb (308) fails.

Technical Field

The invention relates to the technical field of advanced aviation machinery research and development, in particular to an emergency landing gear of an airplane.

Background

In the advanced aviation machinery research and development technology, the takeoff and landing of an airplane can cause unstable descending speed after an aviation accident occurs. The undercarriage serves as a ground travelling mechanism of an airplane, but because an accident can cause the damage of an original oil way and the mechanism, the undercarriage cannot be put down and the oil pressure buffering cannot be carried out, so that a larger accident occurs, application number CN201620266395.4 discloses an aircraft undercarriage specially used for aerospace, the weight of the undercarriage is reduced, the undercarriage cannot be lifted and fallen under multiple complex environments, and the damping buffering cannot be carried out under the condition that the oil way is damaged.

Disclosure of Invention

The invention provides an aircraft emergency landing gear aiming at the technical problem, which comprises an upper combined storage bin, a hydraulic link mechanism, a spring buffer mechanism, an anti-collision lighting mechanism and a tire rotating mechanism.

The upper joint storage bin comprises: a round rod and an oil cylinder output shaft; the hydraulic link mechanism includes: a large bracket and an upper rotating plate; the spring buffer mechanism comprises: a pressure spring and a pendulum cylinder; the anti-collision lighting mechanism comprises: a buffer frame and a large friction head; the tire rotating mechanism comprises: locking the connecting rod and the pressure shaft; the round rod is rotatably installed on a central hole of the large support, the oil cylinder output shaft is fixedly installed on the upper surface of the upper rotating plate, the pressure spring is fixedly installed in the central hole of the large support, the buffer frame is fixedly installed on the outer side of the swinging cylinder, the large friction head is fixedly installed on the outer side of the large support, the locking connecting rod is fixedly installed on the outer side of the large support, and the pressure shaft is fixedly installed on the lower surface of the pressure spring.

Further, go up and unite the collecting storage and still include afterbody mount pad, afterbody seat pivot, the hydro-cylinder tailstock, collect the storehouse board, the round bar mount pad, round bar pivot and hydro-cylinder outer sleeve, afterbody mount pad fixed mounting is at the upper surface of collecting the storehouse board, afterbody seat pivot is rotated and is installed in the downthehole of afterbody mount pad, the hydro-cylinder tailstock rotates and installs the upper surface at afterbody seat pivot, hydro-cylinder outer sleeve fixed mounting is on the hydro-cylinder tailstock, the hydro-cylinder output shaft rotates and installs in the downthehole of hydro-cylinder outer sleeve, round bar mount pad fixed mounting is on collecting the storehouse board, the round bar rotates and installs in the round bar pivot, the round bar pivot rotates and installs on the round bar mount.

Further, the hydraulic link mechanism also comprises a rotary rod, a rotary shifting fork, a shifting fork shaft, a shifting fork sleeve, a disc-shaped rotary shaft, a large lamp holder, a large bulb, a large lampshade, a bottom rotary shaft, a lower swing rod, a front swing shaft, an upper swing shaft, a front swing seat, an upper swing rod, an upper rotary shaft and a support cover, wherein the rotary rod is rotatably arranged on the rotary shifting fork, the shifting fork shaft is slidably arranged on the upper surface of the rotary shifting fork, the shifting fork sleeve is fixedly arranged on two sides of the rotary shifting fork, the disc-shaped rotary shaft is fixedly arranged in a hole of the shifting fork sleeve, the headlamp seat is rotatably arranged on the large support, the headlamp bulb is rotatably arranged on the large lamp holder, the headlamp cover is fixedly arranged on the large lamp holder, the bottom rotary shaft is rotatably arranged on a central hole of the lower swing rod, the front swing rod is rotatably arranged on the front swing shaft, the lower swing rod is, the front swing seat is fixedly arranged on the upper swing rod, the upper rotating shaft is rotatably arranged in the upper swing rod hole, the upper rotating shaft is rotatably arranged in the central hole of the upper rotating plate, and the support cover is fixedly arranged on the upper surface of the large support.

Further, the spring buffer mechanism further comprises a swinging shaft, a swinging piece, a pressure base, a supporting rotating shaft, a small lampshade and a small bulb, wherein the swinging shaft is rotatably installed in a central hole of the swinging piece, the pressure spring is fixedly installed in a hole of the pressure base, the supporting rotating shaft is rotatably installed at the upper end of the swinging barrel, the swinging barrel is fixedly installed on the pressure base, the small lampshade is rotatably installed at the upper end of the pressure base, and the small bulb is rotatably installed on the central hole of the small lampshade.

Further, crashproof lighting mechanism still include little buffer, little blotter, little buffer pole, little friction head, buffer spring, big buffer pole, the cushion socket, big buffer head and big blotter, little buffer fixed mounting is downthehole at little blotter, little buffer pad fixed mounting is downthehole at the cushion socket, little buffer pole fixed mounting is downthehole at the cushion socket, little friction head rotates and installs on the epaxial of little buffer pole, big friction head rotates and installs downthehole at big buffer pole, buffer spring rotates and installs at the cushion socket upper surface, the cushion socket rotates and installs in the cushion socket downthehole, big buffer head and big blotter rotate and install epaxially at big buffer pole.

Furthermore, the tire rotating mechanism also comprises a small locking bolt, a small flange cap, a large flange cap, a left connecting rod, a bushing, a large locking bolt and a right connecting rod, connecting block, wheel hub, the tire, the wheel axle bed, the balancing pole, wheel pivot and support sleeve, little locking bolt fixed mounting is downthehole at the locking connecting rod, little flange cap fixed mounting is on little locking bolt, big flange cap rotates to be installed on big locking bolt, big locking bolt rotates to be installed in the downthehole of bush, left side connecting rod and right side connecting rod rotate to be installed in the both sides of bush, connecting block fixed mounting is inboard at left side connecting rod and right side connecting rod, wheel hub rotates to be installed on the wheel pivot, wheel pivot fixed mounting is on the wheel axle bed, tire fixed mounting is on wheel hub, the balancing pole rotates to be installed on the wheel axle bed, support sleeve rotates to be installed on the wheel pivot, pressure shaft fixed mounting is on support sleeve.

Furthermore, the round rod is rotatably installed on the inner wall of the large support and is in contact with the pressure spring.

Furthermore, the pressure spring is rotatably arranged in the hole of the large bracket, so that the pressure spring is in sliding fit, and the large lamp holder is also contacted with the pressure shaft.

Furthermore, the buffer spring is also contacted with the large friction head and the buffer spring is also contacted with the buffer seat.

Furthermore, the small locking bolt is rotatably installed with the pressure base, and the small bulb and the large bulb are connected in parallel, so that the small bulb can be used when the large bulb fails.

Compared with the prior art, the invention has the beneficial effects that: (1) the landing gear can realize the landing and landing of the airplane in multiple complex environments; (2) the landing gear can realize mechanical buffering and shock absorption; (3) the landing gear can be used for assisting in damping by using the spring and damping under the condition that an oil way is damaged, and the safe emergency landing of the airplane is ensured.

Drawings

Fig. 1 is a schematic structural view of the present invention in use.

Fig. 2 is a schematic structural distribution diagram of the invention.

Fig. 3 is a schematic structural view of the upper united storage bin of the invention.

Fig. 4 is a schematic structural diagram of the hydraulic link mechanism of the invention.

Fig. 5 is a schematic view of the spring damper mechanism of the present invention.

Fig. 6 is a schematic view of the inventive anti-collision lighting mechanism.

Fig. 7 is a schematic view of an inventive tire rotation mechanism.

Reference numerals: 1-upper combined storage bin; 2-a hydraulic link mechanism; 3-a spring buffer mechanism; 4-an anti-collision lighting mechanism; 5-a tire rotation mechanism; 101-tail mount; 102-tail seat shaft; 103-oil cylinder tail seat; 104-a storage bin plate; 105-round bar mount; 106-round bar shaft; 107-round bar; 108-cylinder outer sleeve; 109-oil cylinder output shaft; 201-rotating rod; 202-rotating fork; 203-declutch shift shaft; 204-a shifting fork sleeve; 205-disc shaped rotating shaft; 206-large scaffold; 207-large lamp base; 208-large bulb; 209-large lamp shade; 210-bottom spindle; 211-lower swing link; 212-front swing link; 213-front swing rotating shaft; 214-upper swing shaft; 215-a front swing seat; 216-upper swing link; 217-upper rotating shaft; 218-upper rotating plate; 219-support cover; 301-a pressure spring; 302-a swing axis; 303-a swinging piece; 304-a pressure base; 305-a pendulum cylinder; 306-supporting the rotating shaft; 307-small lamp shade; 308-small bulb; 401-small buffer; 402-small cushion; 403-buffer frame; 404-small buffer rods; 405-a small friction head; 406-a buffer spring; 407-large friction head; 408-large buffer rod; 409-a buffer seat; 410-large buffer head; 411-big cushion; 501-small locking bolts; 502-small flange cap; 503-locking connecting rod; 504-large flange cap; 505-left side link; 506-a bushing; 507-big locking bolt; 508-right link; 509-connecting block; 510-a hub; 511-tire; 512-axle seat; 513-a balancing bar; 514-wheel rotation axis; 515-a support sleeve; 516-pressure axis.

Detailed Description

The present invention will be further described with reference to specific examples, which are illustrative of the invention and are not to be construed as limiting the invention.

Example (b): an aircraft emergency landing gear as shown in fig. 1, 2, 3, 4, 5, 6 and 7 includes an upper joint storage bin 1, a hydraulic link mechanism 2, a spring damper mechanism 3, a pre-crash lighting mechanism 4 and a tire rotating mechanism 5.

Go up and unite collecting storage 1 includes: a round rod 107 and a cylinder output shaft 109; the hydraulic link mechanism 2 includes: a large bracket 206 and an upper swivel plate 218; the spring damper mechanism 3 includes: a pressure spring 301 and a pendulum cylinder 305; the anti-collision illuminating mechanism 4 includes: a buffer frame 403 and a large friction head 407; the tire rotating mechanism 5 includes: locking link 503 and pressure shaft 516; the round rod 107 is rotatably mounted on a central hole of the large bracket 206, the cylinder output shaft 109 is fixedly mounted on the upper surface of the upper rotating plate 218, the pressure spring 301 is fixedly mounted in the central hole of the large bracket 206, the buffer bracket 403 is fixedly mounted on the outer side of the swinging cylinder 305, the large friction head 407 is fixedly mounted on the outer side of the large bracket 206, the locking connecting rod 503 is fixedly mounted on the outer side of the large bracket 206, and the pressure shaft 516 is fixedly mounted on the lower surface of the pressure spring 301.

Go up and unite collecting chamber 1 and still include afterbody mount pad 101, afterbody seat pivot 102, oil cylinder tailstock 103, collecting chamber board 104, pole mount pad 105, pole pivot 106 and cylinder outer sleeve 108, afterbody mount pad 101 fixed mounting is at collecting chamber board 104's upper surface, afterbody seat pivot 102 rotates and installs in the downthehole of afterbody mount pad 101, oil cylinder tailstock 103 rotates and installs the upper surface at afterbody seat pivot 102, cylinder outer sleeve 108 fixed mounting is on oil cylinder tailstock 103, oil cylinder output shaft 109 rotates and installs in the downthehole of cylinder outer sleeve 108, pole mount pad 105 fixed mounting is on collecting chamber board 104, pole 107 rotates and installs on pole pivot 106, pole pivot 106 rotates and installs on pole mount pad 105.

The hydraulic link mechanism 2 further comprises a rotating rod 201, a rotating fork 202, a fork shaft 203, a fork sleeve 204, a disk-shaped rotating shaft 205, a headlamp base 207, a headlamp bulb 208, a headlamp cover 209, a bottom rotating shaft 210, a lower swinging rod 211, a front swinging rod 212, a front swinging shaft 213, an upper swinging rotating shaft 214, a front swinging seat 215, an upper swinging rod 216, an upper rotating shaft 217 and a support cover 219, wherein the rotating rod 201 is rotatably installed on the rotating fork 202, the fork shaft 203 is slidably installed on the upper surface of the rotating fork 202, the fork sleeve 204 is fixedly installed on two sides of the rotating fork 202, the disk-shaped rotating shaft 205 is fixedly installed in a hole of the fork sleeve 204, the headlamp base 207 is rotatably installed on a large support 206, the headlamp bulb 208 is rotatably installed on the large lamp base 207, the headlamp cover 209 is fixedly installed on the large lamp base 207, the bottom rotating shaft 210 is rotatably installed on a central hole of the lower swinging rod 211, the front, the lower swing link 211 is rotatably mounted on the front swing shaft 213, the upper swing shaft 214 is rotatably mounted in the hole of the front swing seat 215, the front swing seat 215 is fixedly mounted on the upper swing link 216, the upper swing shaft 217 is rotatably mounted in the hole of the upper swing link 216, the upper swing shaft 217 is rotatably mounted in the central hole of the upper rotating plate 218, and the bracket cover 219 is fixedly mounted on the upper surface of the large bracket 206. The upper rotating plate 218 is pushed to move by the movement of the oil cylinder output shaft 109, so that the large bracket 206 is pushed to move backwards, and the large bracket 206 is stored backwards and enters the storage.

The spring buffer mechanism 3 further comprises a swinging shaft 302, a swinging piece 303, a pressure base 304, a supporting rotating shaft 306, a small lamp shade 307 and a small bulb 308, wherein the swinging shaft 302 is rotatably installed in a central hole of the swinging piece 303, the pressure spring 301 is fixedly installed in a hole of the pressure base 304, the supporting rotating shaft 306 is rotatably installed at the upper end of a swinging cylinder 305, the swinging cylinder 305 is fixedly installed on the pressure base 304, the small lamp shade 307 is rotatably installed at the upper end of the pressure base 304, the small bulb 308 is rotatably installed on a central hole of the small lamp shade 307, and the pressure spring 301 is a large-torque compression spring made of aviation spring steel.

The anti-collision lighting mechanism 4 also comprises a small buffer 401, a small buffer pad 402, a small buffer rod 404, a small friction head 405, a buffer spring 406, a large buffer rod 408, a buffer seat 409, a large buffer head 410 and a large buffer pad 411, wherein the small buffer 401 is fixedly arranged in a hole of the small buffer pad 402, the small buffer pad 402 is fixedly arranged in a hole of the buffer frame 403, the small buffer rod 404 is fixedly arranged in a hole of the buffer frame 403, the small friction head 405 is rotatably arranged on a shaft of the small buffer rod 404, the large friction head 407 is rotatably arranged in a hole of the large buffer rod 408, the buffer spring 406 is rotatably arranged on the upper surface of the buffer seat 409, the buffer seat 409 is rotatably arranged in a hole of the buffer frame 403, the large buffer head 410 and the large buffer pad 411 are rotatably arranged on a shaft of the large buffer rod 408, and the small buffer 401, the buffer works by self-discharging force through the large buffer rod 408 and the pressure of the buffer spring 406.

Tire rotating mechanism 5 further includes small locking bolt 501, small flange cap 502, large flange cap 504, left side link 505, bushing 506, large locking bolt 507, right side link 508, connecting block 509, hub 510, tire 511, axle seat 512, balancing lever 513, wheel pivot 514 and support sleeve 515, small locking bolt 501 is fixedly installed in the hole of locking link 503, small flange cap 502 is fixedly installed on small locking bolt 501, large flange cap 504 is rotatably installed on large locking bolt 507, large locking bolt 507 is rotatably installed in the hole of bushing 506, left side link 505 and right side link 508 are rotatably installed on both sides of bushing 506, connecting block 509 is fixedly installed on the inner sides of left side link 505 and right side link 508, hub 510 is rotatably installed on wheel pivot 514, wheel pivot 514 is fixedly installed on axle seat 512, tire 511 is fixedly installed on wheel seat 510, balancing lever 513 is rotatably installed on wheel pivot 512, the supporting sleeve 515 is rotatably mounted on the wheel rotating shaft 514, the pressure shaft 516 is fixedly mounted on the upper surface of the supporting sleeve 515, the wheel hub 510 is made of high-impact steel, and the tire 511 is made of a resin tire.

The round rod 107 is also rotatably installed with the inner wall of the large bracket 206, the round rod 107 is also contacted with the pressure spring 301, and the impact of the pressure spring on the containing cabin plate 104 is reduced. The pressure spring 301 is rotatably mounted in the bore of the large bracket 206 in a sliding fit, and the large base 207 is also in contact with the pressure shaft 516. The buffer spring 406 is also in contact with the large friction head 407, and the buffer spring 406 is also in contact with the buffer seat 409.

The small locking bolt 501 is also rotatably mounted on the pressure base 304, and the small bulb 308 and the large bulb 208 are connected in parallel, so that when the large bulb 208 is still available and is impacted due to the failure of the small bulb 308, the left connecting rod 505, the right connecting rod 508 and the connecting block 509 share part of the impact force.