CN218806518U

CN218806518U - Lifting frame for helicopter

Info

Publication number: CN218806518U
Application number: CN202223585357.XU
Authority: CN
Inventors: 沈本忠; 万堂山; 李德军; 付海波
Original assignee: Changzhou Zhonglian Airplane Manufacturing Co ltd
Current assignee: Changzhou Zhonglian Airplane Manufacturing Co ltd
Priority date: 2022-12-31
Filing date: 2022-12-31
Publication date: 2023-04-07
Anticipated expiration: 2032-12-31

Abstract

The utility model relates to a helicopter technical field, concretely relates to helicopter is with frame that plays. The utility model provides a helicopter is with frame that plays, include: the helicopter comprises a fixed platform, a landing gear, a plurality of buffer springs, two limiting blocks and a pedal assembly, wherein the fixed platform is fixed at the lower end of the helicopter; the landing gear is hinged at the lower end of the fixed platform; one end of each buffer spring is fixed on the side wall of the fixed platform, and the other end of each buffer spring is fixed on the side wall of the landing gear; the limiting block is fixed on the side wall of the undercarriage; the pedal assembly is rotatably arranged at the lower end of the fixed platform and is linked with the limiting block; wherein, footboard subassembly expansion end circumferential direction, to tip and stopper separation, the expansion end of footboard subassembly is suitable for outside extension so that trample. Through the cooperation of footboard subassembly and stopper, when realizing buffering the descending force that the undercarriage received, footboard and stopper separation and protrusion fixed platform provide about for the unmanned aerial vehicle upper and lower support of trampling.

Description

Lifting frame for helicopter

Technical Field

The utility model relates to a helicopter technical field, concretely relates to helicopter is with frame that falls.

Background

As shown in fig. 1, when a helicopter in the prior art lands, the landing gear cannot play a good role in buffering, and meanwhile, due to the high arrangement of the landing gear, when a person in the helicopter comes down, the person under the helicopter lacks a stepping pedal, which is not good for the person with short legs; therefore, it is necessary to develop a landing gear for a helicopter.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing a landing gear for helicopter to solve above-mentioned problem.

In order to achieve the above object, an embodiment of the present invention provides a landing rack for helicopter, including

The landing gear comprises a fixed platform, a landing gear, a plurality of buffer springs, two limiting blocks and a pedal assembly, wherein the fixed platform is fixed at the lower end of the helicopter;

the undercarriage is hinged at the lower end of the fixed platform;

one end of each buffer spring is fixed on the side wall of the fixed platform, and the other end of each buffer spring is fixed on the side wall of the landing gear;

the limiting block is fixed on the side wall of the landing gear;

the pedal assembly is rotatably arranged at the lower end of the fixed platform and is linked with the limiting block; wherein, the first and the second end of the pipe are connected with each other,

the movable end of the pedal assembly rotates circumferentially until the end part is separated from the limiting block, and the movable end of the pedal assembly is suitable for extending outwards so as to be convenient for treading.

Preferably, the pedal assembly includes: the device comprises a driver, a fixed ring and two telescopic columns, wherein the driver is fixed below the fixed platform;

the two telescopic columns are symmetrically arranged and are in transmission connection with the rotating shaft of the driver respectively;

the fixed ring is arranged above the telescopic column, and the telescopic column is matched with the fixed ring in a sliding manner.

Preferably, the two telescopic columns have different outer diameters, and one telescopic column is slidably inserted into the other telescopic column.

Preferably, a compression spring is further fixed in the telescopic column, and one end of the compression spring is fixed on the driver; the compression spring is suitable for pushing the two telescopic columns to slide away from each other.

Preferably, a horizontal rod is further fixed to each of the two sides of the undercarriage, the limiting blocks are fixed to the horizontal rods, and the two limiting blocks are symmetrically arranged.

Preferably, an inclined plane is seted up to the stopper lateral wall, and when the flexible post of driver drive rotated to the stopper, the inclined plane was suitable for the top to push away flexible post is inwards contract.

Preferably, a pedal is fixed at the end of each telescopic column, and a slope matched with the inclined plane is arranged on one side of each pedal.

Preferably, a sliding groove is formed in the fixing ring, and a sliding block matched with the sliding groove is fixed on the outer wall of the telescopic column.

Compared with the prior art, the utility model relates to a helicopter has following beneficial effect with embodiment of frame that falls: through the cooperation of footboard subassembly and stopper, when realizing the descending power that the buffering undercarriage received, footboard and stopper separation and protrusion fixed platform for the last personnel of unmanned aerial vehicle provide about from top to bottom trample the support.

Drawings

The present invention will be further described with reference to the accompanying drawings and examples.

Figure 1 shows a perspective view of the prior art of the present invention;

fig. 2 shows a perspective view of a landing gear for a helicopter according to the present invention;

fig. 3 shows a schematic view of the telescopic column of the present invention in a contracted state;

fig. 4 shows a schematic diagram of the extension state of the telescopic column of the present invention.

In the figure:

1. a fixed platform; 2. a landing gear; 3. a buffer spring; 4. a limiting block; 40. a horizontal bar; 41. a bevel; 5. a pedal assembly; 51. a driver; 52. a fixing ring; 53. a telescopic column; 54. a pedal.

Detailed Description

The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic drawings and illustrate the basic structure of the present invention only in a schematic manner, and thus show only the components related to the present invention.

As shown in fig. 1 to 4, the utility model provides a landing rack for helicopter, include: the helicopter comprises a fixed platform 1, an undercarriage 2, a plurality of buffer springs 3, two limiting blocks 4 and a pedal assembly 5, wherein the fixed platform 1 is fixed at the lower end of the helicopter; the fixed frame is suitable for being fixedly connected with the undercarriage 2, and the undercarriage 2 is hinged to the lower end of the fixed platform 1; one end of each buffer spring 3 is fixed on the side wall of the fixed platform 1, and the other end of each buffer spring 3 is fixed on the side wall of the landing gear 2; when the helicopter lands downwards, the landing gear 2 is stressed in the process that the landing gear 2 lands downwards gradually, and can play a role in buffering in the process that the landing gear 2 expands outwards under the action of the buffer spring 3; the arrangement of the fixed ring 52 and the two telescopic columns 53 also provides a cushioning effect during landing of the landing gear 2. The limiting block 4 is fixed on the side wall of the undercarriage 2; the pedal assembly 5 is rotatably arranged at the lower end of the fixed platform 1, and the pedal assembly 5 is linked with the limiting block 4; wherein, 5 expansion end circumferential direction of footboard subassemblies, to tip and the separation of stopper 4, the expansion end of footboard subassembly 5 is suitable for outside extension so that trample. Stopper 4 and the cooperation of footboard, cushioning effect when can playing the descending, and descend the back, footboard tip protrusion stopper 4 to make things convenient for the unmanned aerial vehicle to use from top to bottom, improved and used the travelling comfort.

In order to facilitate personnel getting on and off the drone, the pedal assembly 5 comprises: the device comprises a driver 51, a fixed ring 52 and two telescopic columns 53, wherein the driver 51 is fixed below the fixed platform 1; the driver 51 is suitable for driving the telescopic column 53 and the fixed ring 52 to synchronously rotate circumferentially; the two telescopic columns 53 are symmetrically arranged, and the two telescopic columns 53 are respectively in transmission connection with the rotating shaft of the driver 51; the fixed ring 52 is arranged above the telescopic column 53, and the telescopic column 53 is matched with the fixed ring 52 in a sliding manner. When the driver 51 drives the telescopic column 53 to rotate circumferentially to abut against the limiting block 4, the limiting block 4 is suitable for pushing the telescopic column 53 to contract inwards; and driver 51 drive flexible post 53 circumferential direction extremely, when flexible post 53 tip and stopper 4 break away from, two flexible posts 53 move apart from each other to make the footboard of tip protrusion fixed platform 1, provide the support when so that personnel trample from top to bottom.

Preferably, the two telescopic columns 53 have different outer diameters, and one telescopic column 53 is slidably inserted into the other telescopic column 53. A compression spring is further fixed in the telescopic column 53, and one end of the compression spring is fixed on the driver 51; the compression spring is adapted to urge the two telescopic legs 53 to slide apart. Two telescopic columns 53 can contract the activity in opposite directions, also can separate the expansion activity, and compression spring's setting can slow down the pressure that telescopic column 53 both ends were received on the one hand, and on the other hand also can provide thrust for the outside expansion of two telescopic columns 53.

In order to fix the limit blocks 4, horizontal rods 40 are respectively fixed on two sides of the undercarriage 2, the limit blocks 4 are fixed on the horizontal rods 40, and the two limit blocks 4 are symmetrically arranged. An inclined plane 41 is formed in the side wall of the limiting block 4, and when the driver 51 drives the telescopic column 53 to rotate towards the limiting block 4, the inclined plane 41 is suitable for pushing the telescopic column 53 to contract inwards. The arrangement of the fixed block and the inclined plane 41 is convenient for pushing the telescopic column 53 and the pedal 54 to contract inwards, and meanwhile, when the end part of the pedal 54 abuts against the side wall of the limiting column, the telescopic column 53 can play a role in buffering external force applied to the landing gear 2.

A pedal 54 is fixed at the end of each telescopic column 53, and a slope matched with the inclined plane 41 is arranged at one side of the pedal 54. A sliding groove is formed in the fixing ring 52, and a sliding block matched with the sliding groove is fixed on the outer wall of the telescopic column 53. The setting of footboard 54, unmanned aerial vehicle about the personnel of being convenient for provides the support, and the horizontal plane projection of footboard 54 is greater than the horizontal projection of flexible post 53. The arrangement of the sliding groove and the sliding block facilitates the inward contraction or outward expansion sliding of the telescopic column 53, and provides a guiding effect for the sliding of the telescopic column 53.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A landing gear for a helicopter, comprising:

the helicopter comprises a fixed platform (1), an undercarriage (2), a plurality of buffer springs (3), two limiting blocks (4) and a pedal assembly (5), wherein the fixed platform (1) is fixed at the lower end of the helicopter;

the undercarriage (2) is hinged at the lower end of the fixed platform (1);

one ends of the buffer springs (3) are fixed on the side wall of the fixed platform (1), and the other ends of the buffer springs (3) are fixed on the side wall of the landing gear (2);

the limiting block (4) is fixed on the side wall of the undercarriage (2);

the pedal assembly (5) is rotatably arranged at the lower end of the fixed platform (1), and the pedal assembly (5) is linked with the limiting block (4); wherein the content of the first and second substances,

the movable end of the pedal assembly (5) rotates in the circumferential direction until the end is separated from the limiting block (4), and the movable end of the pedal assembly (5) is suitable for extending outwards so as to be convenient for treading.

2. A landing gear for helicopters, according to claim 1,

the pedal assembly (5) comprises: the device comprises a driver (51), a fixed ring (52) and two telescopic columns (53), wherein the driver (51) is fixed below the fixed platform (1);

the two telescopic columns (53) are symmetrically arranged, and the two telescopic columns (53) are respectively in transmission connection with a rotating shaft of the driver (51);

the fixing ring (52) is arranged above the telescopic column (53), and the telescopic column (53) is matched with the fixing ring (52) in a sliding mode.

3. A landing gear for helicopters, according to claim 2,

the two telescopic columns (53) have different outer diameters, and one telescopic column (53) can be slidably inserted into the other telescopic column (53).

4. A landing gear for helicopters, according to claim 3,

a compression spring is further fixed in the telescopic column (53), and one end of the compression spring is fixed on the driver (51); the compression spring is suitable for pushing the two telescopic columns (53) to slide away from each other.

5. A landing gear for helicopters, according to claim 4,

a horizontal rod (40) is further fixed to each of the two sides of the landing gear (2), the limiting blocks (4) are fixed to the horizontal rods (40), and the two limiting blocks (4) are symmetrically arranged.

6. A landing gear for helicopters, according to claim 5,

an inclined plane (41) is formed in the side wall of the limiting block (4), and when the driver (51) drives the telescopic column (53) to rotate towards the limiting block (4), the inclined plane (41) is suitable for pushing the telescopic column (53) to contract inwards.

7. A landing gear for helicopters, according to claim 6,

a pedal (54) is fixed at the end part of each telescopic column (53), and one side of each pedal (54) is provided with a slope matched with the inclined plane (41).

8. A landing gear for helicopters, according to claim 7,

a sliding groove is formed in the fixing ring (52), and a sliding block matched with the sliding groove is fixed on the outer wall of the telescopic column (53).