CN212243798U

CN212243798U - Mechanical landing gear for aviation

Info

Publication number: CN212243798U
Application number: CN202020373569.3U
Authority: CN
Inventors: 滕雪冬; 张心明
Original assignee: Changchun University of Science and Technology; AVIC Aerodynamics Research Institute
Current assignee: Changchun University of Science and Technology; AVIC Aerodynamics Research Institute
Priority date: 2020-03-23
Filing date: 2020-03-23
Publication date: 2020-12-29
Anticipated expiration: 2030-03-23

Abstract

The utility model discloses an aircraft mechanical landing gear, which comprises a mounting plate, a supporting rod, a pulley block and a cabin door, wherein the mounting plate is in a two-layer ladder shape, the supporting rod comprises a cylinder and a telescopic rod, the upper end of the cylinder is hinged on the lower end surface of a lower layer transverse plate of the mounting plate, a first hydraulic telescopic rod is hinged between the side surface of the cylinder and the lower end of an upper layer transverse plate of the mounting plate, the telescopic rod is inserted at the lower end of the cylinder, a damping strut is fixedly arranged at the lower end of the telescopic rod, the pulley block comprises a wheel hub and a tire, the two wheel hubs are rotatably arranged at the lower ends of the damping strut, the tire is wrapped outside the wheel hub, a second hydraulic telescopic rod is hinged between the inner side surface of the cabin door and the side surface of the cylinder, the utility model has simple, and meanwhile, the landing gear is controlled to avoid the condition that the landing gear cannot work normally due to the failure of the cabin door.

Description

Mechanical landing gear for aviation

Technical Field

The utility model relates to an aviation technical field, concretely relates to machinery undercarriage for aviation.

Background

The landing gear is used as an aircraft part for supporting the weight of the aircraft and absorbing impact energy when the aircraft is parked, taxied, taken off, landed and run on the ground, so people design retractable landing gears, the landing gear is received in wings or a fuselage when the aircraft flies in the air to obtain good aerodynamic performance, the landing gear is put down when the aircraft lands, and when the general landing gear is taken off and put up, a cabin door needs to be opened firstly and then the operation is realized, but the cabin door sometimes breaks down, so the mechanical landing gear for aviation is provided for solving the problems.

SUMMERY OF THE UTILITY MODEL

Technical problem to be solved

In order to overcome the prior art not enough, present a machinery undercarriage for aviation, the mechanism is simple, and convenient operation articulates the one end of hatch door in the side of cylinder, and the other end articulates in the hatch door, and the hatch door can open and shut when rising and falling along with the undercarriage, and simultaneous control avoids the hatch door trouble to lead to the unable normal work of undercarriage.

(II) technical scheme

The utility model discloses a following technical scheme realizes: the utility model provides an aircraft machinery undercarriage, a serial communication port, including mounting panel, bracing piece, assembly pulley and hatch door, the mounting panel is two-layer echelonment, the bracing piece includes cylinder and telescopic link, the upper end of cylinder articulates on the terminal surface under the lower floor's diaphragm of mounting panel, is provided with first hydraulic telescoping rod of articulated between the side of cylinder and the upper diaphragm lower extreme of mounting panel, the telescopic link alternates in the lower extreme of cylinder, and the lower extreme of telescopic link is fixed to be provided with the shock attenuation pillar, the assembly pulley includes wheel hub and tire, two wheel hub rotates and sets up in the lower extreme of shock attenuation pillar, the tire wraps up in the wheel hub outside, be provided with articulated second hydraulic telescoping between the medial surface of hatch door and the side of cylinder.

Furthermore, a first connecting seat is fixedly arranged at the lower end of the lower-layer transverse plate of the mounting plate.

Furthermore, a second connecting seat is fixedly arranged at the lower end of the upper-layer transverse plate of the mounting plate.

Furthermore, a third connecting seat and a fourth connecting seat are fixedly arranged on the side faces of the air cylinder respectively.

Furthermore, a fifth connecting seat is fixedly arranged at the lower end of the inner side surface of the cabin door.

Further, the shock absorption strut comprises an inner cylinder and an outer cylinder which are connected in an inserting mode, and high-pressure nitrogen or dry air is filled between the inner cylinder and the outer cylinder.

(III) advantageous effects

Compared with the prior art, the utility model, following beneficial effect has:

1. the mechanism is simple, and convenient operation articulates the one end of hatch door in the side of cylinder, and the other end articulates in the hatch door, and the hatch door can open and shut along with undercarriage rising and falling when, and control simultaneously avoids the hatch door trouble to lead to the unable normal work of undercarriage.

2. The shock strut is including inner tube and the urceolus that alternates to connect, it has high-pressure nitrogen gas or dry air to fill between inner tube and the urceolus, and when the shock strut compression, gas receives the compression, and the absorbed energy plays buffering cushioning effect for the aircraft is gone more steadily.

Drawings

Fig. 1 is a schematic structural diagram of the present invention.

Fig. 2 is a front view of the present invention.

Fig. 3 is a bottom view of the mounting plate of the present invention.

1-mounting a plate; 2-a support rod; 3, pulley block; 4-a cabin door; 5-a first hydraulic telescopic rod; 6-a shock strut; 7-second hydraulic expansion and contraction; 11-a first connection seat; 12-a second connection seat; 21-cylinder; 22-a telescopic rod; 23-a third connection seat; 24-a fourth connection receptacle; 31-a hub; 32-a tire; 41-fifth connecting seat.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

As shown in fig. 1, 2 and 3, the aircraft mechanical landing gear comprises a mounting plate 1, a support rod 2, a pulley block 3 and a cabin door 4, the mounting plate 1 is two-layer stepped, the support rod 2 comprises a cylinder 21 and a telescopic rod 22, the upper end of the cylinder 21 is hinged to the lower end face of a lower transverse plate of the mounting plate 1, a first hydraulic telescopic rod 5 is hinged between the side face of the cylinder 21 and the lower end of an upper transverse plate of the mounting plate 1, the telescopic rod 22 is inserted into the lower end of the cylinder 21, a damping strut 6 is fixedly arranged at the lower end of the telescopic rod 22, the pulley block 3 comprises a hub 31 and a tire 32, the hub 31 is rotatably arranged at the lower end of the damping strut 6, the tire 32 is wrapped outside the hub 31, and a second hydraulic telescopic rod 7 is hinged between the inner side face of the cabin door 4 and the.

The lower end of the lower-layer transverse plate of the mounting plate 1 is fixedly provided with a first connecting seat 11; a second connecting seat 12 is fixedly arranged at the lower end of the upper-layer transverse plate of the mounting plate 1; the side surface of the cylinder 21 is respectively and fixedly provided with a third connecting seat 23 and a fourth connecting seat 24; a fifth connecting seat 41 is fixedly arranged at the lower end of the inner side surface of the cabin door 4; the shock absorption strut 6 comprises an inner cylinder and an outer cylinder which are connected in an inserting mode, and high-pressure nitrogen or dry air is filled between the inner cylinder and the outer cylinder.

The utility model provides a mechanical undercarriage for aviation, it is when specifically using, mounting panel 1 is installed within the hatch door, hatch door 4's side articulates on the hatch door border, the upper end of cylinder 21 articulates under mounting panel 1's lower floor diaphragm on the terminal surface, be provided with articulated first hydraulic telescoping rod 5 between the side of cylinder 21 and the upper diaphragm lower extreme of mounting panel 1, start first hydraulic telescoping rod 5 and can make the cylinder 21 vertical roll over a book and go out, be provided with articulated second hydraulic telescoping 7 between the medial surface of hatch door 4 and the another side of cylinder 21, prop when the bracing piece 2 turns over a book and move hatch door 4 and turn over a book and open, telescopic link 22 alternates in the lower extreme of cylinder 21, the steerable telescopic link 22 extension of cylinder 21, adjust the position of assembly pulley 3, the steerable hatch door 4's of the flexible 7 of second hydraulic telescoping degree of turning over, avoid the hatch door trouble to lead to the unable normal work of.

The fixed shock strut 6 that is provided with of lower extreme of telescopic link 22, shock strut 6 is filled with high-pressure nitrogen gas or dry air including inner tube and the urceolus that alternates to connect between inner tube and the urceolus, and when the compression of shock strut 6, gas received the compression, and the energy absorption plays buffering cushioning effect for the aircraft is gone more steadily.

The above-described embodiments are merely illustrative of the preferred embodiments of the present invention and are not intended to limit the spirit and scope of the present invention. Without departing from the design concept of the present invention, various modifications and improvements made by the technical solution of the present invention by those skilled in the art should fall into the protection scope of the present invention, and the technical contents claimed by the present invention have been fully recorded in the claims.

Claims

1. An aircraft mechanical landing gear, characterized in that: comprises a mounting plate (1), a support rod (2), a pulley block (3) and a cabin door (4), the mounting plate (1) is in a two-layer ladder shape, the support rod (2) comprises an air cylinder (21) and an expansion rod (22), the upper end of the cylinder (21) is hinged on the lower end surface of the lower-layer transverse plate of the mounting plate (1), a first hydraulic telescopic rod (5) which is hinged is arranged between the side surface of the cylinder (21) and the lower end of the upper-layer transverse plate of the mounting plate (1), the telescopic rod (22) is inserted at the lower end of the cylinder (21), the lower end of the telescopic rod (22) is fixedly provided with a shock absorption strut (6), the pulley block (3) comprises wheel hubs (31) and tires (32), the two wheel hubs (31) are rotatably arranged at the lower ends of the shock absorption struts (6), the tire (32) wraps the outer side of the wheel hub (31), and a hinged second hydraulic expansion device (7) is arranged between the inner side face of the cabin door (4) and the side face of the cylinder (21).

2. An aircraft mechanical landing gear according to claim 1, wherein: the lower floor diaphragm lower extreme of mounting panel (1) is fixed and is provided with first connecting seat (11).

3. An aircraft mechanical landing gear according to claim 1, wherein: and a second connecting seat (12) is fixedly arranged at the lower end of the upper-layer transverse plate of the mounting plate (1).

4. An aircraft mechanical landing gear according to claim 1, wherein: the side surface of the air cylinder (21) is respectively and fixedly provided with a third connecting seat (23) and a fourth connecting seat (24).

5. An aircraft mechanical landing gear according to claim 1, wherein: the lower end of the inner side surface of the cabin door (4) is fixedly provided with a fifth connecting seat (41).

6. An aircraft mechanical landing gear according to claim 1, wherein: the shock absorption strut (6) comprises an inner cylinder and an outer cylinder which are connected in an inserting mode, and high-pressure nitrogen or dry air is filled between the inner cylinder and the outer cylinder.