CN211076320U

CN211076320U - Front undercarriage retracting mechanism for light sport aircraft

Info

Publication number: CN211076320U
Application number: CN201922112103.8U
Authority: CN
Inventors: 王燕强; 韩树林; 钟瑶; 黄奕然; 于华东
Original assignee: Chengdu Hangus Aviation Technology Co ltd
Current assignee: Chengdu Hangus Aviation Technology Co ltd
Priority date: 2019-12-01
Filing date: 2019-12-01
Publication date: 2020-07-24
Anticipated expiration: 2029-12-01

Abstract

The utility model discloses a nose-gear jack for light-duty motion aircraft, including the fuselage subassembly, the fuselage subassembly rotates through the erection joint and is connected with the landing gear pole, the landing gear wheel is passed through pivot fixedly connected with to landing gear pole bottom. The utility model discloses in, wave the handle and drive the axis of rotation and rotate, through transmission axis and universal joint drive worm rotary motion, the worm drives the worm wheel and rotates, the worm wheel then drives its outside appearance wall an organic whole welded rocking arm and does the swing, the rocking arm drives damping component and makes the landing gear pole be rotary motion around the erection joint when linear motion, receive on the undercarriage, the wheelset receives in the fuselage subassembly, the undercarriage operation of putting down is opposite with above-mentioned operation, and pack up and carry on spacingly when putting down the wheelset through the retainer, thereby the receiving and releasing of undercarriage has been realized, the result of use of undercarriage jack has been improved.

Description

Front undercarriage retracting mechanism for light sport aircraft

Technical Field

The utility model relates to an aviation technical field especially relates to a nose landing gear jack for light-duty motion aircraft.

Background

Landing gear is an attachment device for supporting an aircraft for ground (surface) movement during takeoff and landing or ground (surface) taxiing on the lower portion of the aircraft. The landing gear is the only part for supporting the whole airplane, so that the landing gear is an integral part of the airplane; without it, the aircraft cannot move on the ground. After the aircraft takes off, the landing gear may be retracted depending on flight performance.

At present, the existing nose landing gear retraction mechanism of the light sport aircraft still has some defects, firstly, the existing retractable nose landing gear of the light sport aircraft is mostly controlled by hydraulic pressure, and has the defects of large structural weight, complex mounting structure, high manufacturing cost and maintenance cost and the like, thereby reducing the using effect of the nose landing gear retraction mechanism of the light sport aircraft; secondly, the existing nose landing gear retracting and releasing mechanism of the light sport airplane lacks a protection mechanism of a nose landing gear wheel, and during the takeoff stage of the airplane, a barrier exists on the road surface during the run-up, and a larger barrier can impact the nose landing gear wheel and a landing gear rod to damage the nose landing gear wheel and the landing gear rod, so that the using effect of the nose landing gear retracting and releasing mechanism of the light sport airplane is reduced.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide a: in order to solve the problems, a nose landing gear retracting and releasing mechanism for a light sport aircraft is provided.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

a nose landing gear retracting mechanism for a light sport aircraft comprises a fuselage assembly, the fuselage assembly is rotatably connected with a landing gear rod through an installation joint, the bottom of the landing gear rod is fixedly connected with a front landing gear wheel through a pivot, the outer surface wall of the landing gear rod is fixedly provided with a pull rod joint, the machine body component is fixedly provided with a connecting seat at the longitudinal end, the inner surface wall of the longitudinal end of the connecting seat is rotatably connected with a worm wheel through a rotating shaft, rocker arms are welded on two sides of the longitudinal end of the worm wheel in a whole body, a damping component is arranged between the rocker arms and the pull rod joint, a worm meshed with the worm wheel is arranged at the bottom of the connecting seat, and one side of the horizontal end of the worm is fixedly provided with a transmission shaft which is connected with a rotating shaft through a universal joint in a transmission way, and one side of the rotating shaft far away from the universal joint is fixedly provided with a handle, and the inner surface wall of the longitudinal end of the machine body assembly is fixedly provided with a stop piece.

As a further description of the above technical solution:

the outer surface wall of the lifting frame rod is fixedly connected with a fixing sleeve, a protection block is fixedly mounted on one side of the fixing sleeve, and the protection block is of a triangular pyramid structure.

As a further description of the above technical solution:

the damping assembly comprises a center rod, a spring and a joint bearing, and the rocker arm and the pull rod joint are rotatably connected with the damping assembly through the joint bearing.

As a further description of the above technical solution:

the pull rod joint and the landing gear rod are bonded into a whole through epoxy resin glue and are reinforced through glass fiber cloth.

As a further description of the above technical solution:

the two groups of the stop pieces are respectively an upper stop end and a lower stop end.

As a further description of the above technical solution:

the fixed sleeve is fixedly connected with the landing gear rod through a bolt.

To sum up, owing to adopted above-mentioned technical scheme, the beneficial effects of the utility model are that:

1. the utility model discloses in, wave the handle and drive the axis of rotation and rotate, through transmission axis and universal joint drive worm rotary motion, the worm drives the worm wheel and rotates, the worm wheel then drives its outside appearance wall an organic whole welded rocking arm and does the swing, the rocking arm drives damping component and makes the landing gear pole be rotary motion around the erection joint when linear motion, receive on the undercarriage, the wheelset receives in the fuselage subassembly, the undercarriage operation of putting down is opposite with above-mentioned operation, and pack up and carry on spacingly when putting down the wheelset through the retainer, thereby the receiving and releasing of undercarriage has been realized, the result of use of undercarriage jack has been improved.

2. The utility model discloses in, the hack lever that rises and falls is triangular pyramid structural design through fixed cover fixedly connected with protection piece, and through protection piece for leading to rise and fall gear wheel is at the in-process of advancing, and protection piece can contact earlier with the barrier and push away from it, has avoided the barrier can direct contact wheelset and cause the damage to wheelset, thereby has improved the stability that leading to fall gear jack used.

Drawings

Fig. 1 shows a schematic structural diagram provided according to an embodiment of the present invention;

fig. 2 shows a schematic structural diagram of a rocker arm provided according to an embodiment of the present invention;

fig. 3 shows a schematic structural diagram of a protection block provided according to an embodiment of the present invention.

Illustration of the drawings:

1. a fuselage assembly; 2. a landing gear lever; 3. installing a connector; 4. a tie-rod joint; 5. fixing a sleeve; 6. a protection block; 7. a pivot; 8. a front landing gear wheel; 9. a shock absorbing assembly; 901. a center pole; 902. a spring; 903. a knuckle bearing; 10. a rocker arm; 11. a worm gear; 12. a connecting seat; 13. a stopper; 14. a worm; 15. a drive shaft; 16. a universal joint; 17. a rotating shaft; 18. a handle.

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 of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the protection scope of the present invention.

Referring to fig. 1-3, the present invention provides a technical solution: a front landing gear retracting mechanism for a light sport airplane comprises a machine body component 1, the machine body component 1 is rotatably connected with a landing gear rod 2 through a mounting joint 3, the bottom of the landing gear rod 2 is fixedly connected with a front landing gear wheel 8 through a pivot 7, the outer surface wall of the landing gear rod 2 is fixedly provided with a pull rod joint 4, the longitudinal end of the machine body component 1 is fixedly provided with a connecting seat 12, the inner surface wall of the longitudinal end of the connecting seat 12 is rotatably connected with a worm wheel 11 through a rotating shaft, two sides of the longitudinal end of the worm wheel 11 are integrally welded with rocker arms 10, a damping component 9 is arranged between the rocker arms 10 and the pull rod joint 4, the bottom of the connecting seat 12 is provided with a worm 14 engaged with the worm wheel 11, one side of the horizontal end of the worm 14 is fixedly provided with a transmission shaft 15, the transmission shaft, the inner surface wall of the longitudinal end of the fuselage assembly 1 is fixedly provided with a stop 13.

Specifically, as shown in fig. 1 and 3, the outer surface wall of the landing gear rod 2 is fixedly connected with a fixing sleeve 5, one side of the fixing sleeve 5 is fixedly provided with a protection block 6, and the protection block 6 is in a triangular pyramid structure, so that in the advancing process of the front landing gear wheel 8, the protection block 6 can be firstly contacted with the barrier and pushes away the barrier, the barrier is prevented from directly contacting the wheel set to damage the wheel set, and the use stability of the front landing gear retracting mechanism is improved.

Specifically, as shown in fig. 1, the damping assembly 9 includes a central rod 901, a spring 902 and a knuckle bearing 903, and the rocker arm 10 and the tie rod joint 4 are rotatably connected to the damping assembly 9 through the knuckle bearing 903, so as to ensure stability of the wheel set when being retracted and put down.

Specifically, as shown in fig. 1, the tie rod joint 4 and the landing gear rod 2 are bonded together by epoxy resin adhesive, and are reinforced by glass fiber cloth to ensure the structural strength of the tie rod joint 4 and the landing gear rod 2.

Specifically, as shown in fig. 1, two sets of the stoppers 13 are provided, and the two sets of the stoppers 13 correspond to an upper stopping end and a lower stopping end respectively, and the upper stopping end and the lower stopping end are installed at designated positions on the machine body assembly 1 through bolts respectively and are used for limiting when the wheel set is retracted and put down.

Specifically, as shown in fig. 1, the fixing sleeve 5 is fixedly connected with the landing gear rod 2 through a bolt, so that the fixing sleeve 5 and the protection block 6 can be conveniently detached.

The working principle is as follows: when in use, the rocking handle 18 drives the rotating shaft 17 to rotate, the worm 14 is driven to rotate by the transmission shaft 15 and the universal joint 16, the worm 14 drives the worm wheel 11 to rotate, the worm wheel 11 drives the rocker arm 10 integrally welded on the outer surface wall of the worm wheel 11 to swing, the rocker arm 10 drives the shock absorption assembly 9 to do linear motion and simultaneously enables the landing gear rod 2 to do rotary motion around the mounting joint 3, the landing gear is retracted on the landing gear, the wheel set is received in the machine body assembly 1, the landing gear lowering operation is opposite to the operation, and the limit is carried out on the wheel set when retracted and lowered by the retainer 13, thereby realizing the retraction and extension of the front landing gear, improving the use effect of the retraction and extension mechanism of the front landing gear, the shock absorption assembly 9 plays a shock absorption role on the wheel set when lowered, the worm wheel 11 and the worm 14 have self-locking property, and can ensure that the landing, and the protection block 6 is designed to be in a triangular pyramid structure, so that the protection block 6 can be firstly contacted with and pushed away from the obstacle when the nose landing gear wheel 8 advances, the obstacle is prevented from directly contacting with the wheel set to damage the wheel set, and the use stability of the nose landing gear retraction jack is improved.

The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.

Claims

1. The utility model provides a nose landing gear jack for light-duty motion aircraft, includes fuselage subassembly (1), its characterized in that, fuselage subassembly (1) rotates through erection joint (3) and is connected with landing gear pole (2), landing gear pole (2) bottom is through pivot (7) fixedly connected with nose landing gear wheel (8), landing gear pole (2) exterior wall fixed mounting has pull rod joint (4), fuselage subassembly (1) longitudinal end fixed mounting has connecting seat (12), the interior table wall of connecting seat (12) longitudinal end rotates through the pivot and is connected with worm wheel (11), and equal integrative welding in worm wheel (11) longitudinal end both sides has rocking arm (10), be provided with between rocking arm (10) and pull rod joint (4) damper (9), connecting seat (12) bottom is provided with worm (14) of being connected with worm wheel (11) meshing, just worm (14) horizontal end one side fixed mounting has transmission shaft (15), transmission shaft (15) are connected with axis of rotation (17) through universal joint (16) transmission, and one side fixed mounting that universal joint (16) were kept away from in axis of rotation (17) has handle (18), surface wall fixed mounting has retainer (13) in fuselage subassembly (1) vertical end.

2. A nose landing gear retraction mechanism for a light sport aircraft, according to claim 1, characterized in that said landing gear rod (2) is fixedly connected to a fixed sleeve (5) on the outer surface wall, a protection block (6) is fixedly mounted on one side of said fixed sleeve (5), and said protection block (6) is in a triangular pyramid structure.

3. A nose gear stowing mechanism for a light sport aircraft according to claim 1 characterised in that said shock absorbing assembly (9) comprises a central rod (901), a spring (902) and a knuckle bearing (903), and said rocker arm (10) and tie rod joint (4) are both rotatably connected to the shock absorbing assembly (9) by the knuckle bearing (903).

4. A nose landing gear stowing mechanism for a light sports aircraft according to claim 1, characterised in that the tie rod joint (4) and the landing gear rod (2) are bonded together by epoxy glue and reinforced by fiberglass fibre cloth.

5. A nose landing gear stowing mechanism for a light sport aircraft according to claim 1 characterised in that said stops (13) are provided in two sets and in that the two sets of stops (13) correspond respectively to an upper stop end and a lower stop end.

6. A nose landing gear stowing mechanism for a light sport aircraft according to claim 2, characterised in that said fixing cuff (5) is fixedly connected to the landing gear rod (2) by means of bolts.