CN214653346U

CN214653346U - Jack catch for aircraft tail support jack

Info

Publication number: CN214653346U
Application number: CN202120629051.6U
Authority: CN
Inventors: 胡悦欣
Original assignee: Nanjing Nanhang Tianchen Civil Aviation Equipment Co ltd
Current assignee: Nanjing Nanhang Tianchen Civil Aviation Equipment Co ltd
Priority date: 2021-03-29
Filing date: 2021-03-29
Publication date: 2021-11-09
Anticipated expiration: 2031-03-29

Abstract

The utility model discloses a jack catch for aircraft afterbody supports jack, include: the two ends of the connecting block are hinged with a first clamping jaw and a second clamping jaw; a first rod pin and a second rod pin are arranged on the first clamping jaw; a third rod pin and a fourth rod pin are arranged on the second jaw; the two sides of the fixed frame are connected with sliding blocks, and the sliding blocks are provided with waist-shaped grooves for the first rod pins to slide; a clamping groove is formed in the position, corresponding to the rod pin IV, of the fixing frame; the bottom of the connecting block is connected with a base, an elastic part is arranged between one end of the fixing frame close to the second clamping jaw and the base, one end of the elastic part is connected with the fixing frame, and the other end of the elastic part is connected with the base; the utility model discloses a two jack catchs of holding aircraft fuselage top tightly have solved aircraft fuselage and jack and have the problem that breaks away from the hidden danger, have improved the reliability of aircraft fuselage and jack.

Description

Jack catch for aircraft tail support jack

Technical Field

The utility model relates to a jack catch for aircraft afterbody supports jack belongs to mechanical device technical field.

Background

When the aircraft tail supporting jack is connected with the aircraft body, the top head on the aircraft tail body is clamped into the concave surface at the end part of the supporting jack, when the aircraft unloads, the aircraft tail moves up and down, and the jack is easy to have the potential safety hazard of being separated from the aircraft body.

SUMMERY OF THE UTILITY MODEL

The utility model aims to overcome among the prior art when unloading on the aircraft, the aircraft afterbody reciprocates, and it has the not enough that breaks away from fuselage potential safety hazard to take place the jack easily, provides a jack catch for aircraft afterbody supports jack.

A jack catch for an aircraft aft support jack, comprising:

the two ends of the connecting block are hinged with a first clamping jaw and a second clamping jaw; a first rod pin and a second rod pin are arranged on the first clamping jaw; a third rod pin and a fourth rod pin are arranged on the second jaw;

the two sides of the fixed frame are connected with sliding blocks, and the sliding blocks are provided with waist-shaped grooves for the first rod pins to slide; a clamping groove is formed in the position, corresponding to the rod pin IV, of the fixing frame;

the bottom of the connecting block is connected with a base, an elastic part is arranged between one end, close to the second clamping jaw, of the fixing frame and the base, one end of the elastic part is connected with the fixing frame, and the other end of the elastic part is connected with the base.

Furthermore, the position of the fixing frame corresponding to the waist-shaped groove is provided with a safety hole, and the safety hole is provided with a safety screw in a matching way.

Furthermore, the second rod pin and the third rod pin are clamped at the upper part of the fixed frame.

Furthermore, one end of the fixing frame is connected with a handle, and the other end of the fixing frame is provided with a rod beam used for connecting the elastic component.

Furthermore, two ends of the connecting block are connected with the first clamping jaw and the second clamping jaw through a first rotating pin shaft and a second rotating pin shaft respectively.

Further, the elastic component is a tension spring.

Compared with the prior art, the utility model discloses the beneficial effect who reaches: the utility model solves the problem that the aircraft body and the jack are separated from hidden danger through two clamping claws tightly holding the aircraft body top, and improves the reliability of the aircraft body and the jack;

the utility model discloses scheme light in weight implements effectively, compares hydraulic structure mode locking, and the entire system degree of difficulty reduces a lot, and the cost is cheap, makes simplely, and the insurance function is complete and effective.

Drawings

Fig. 1 is a schematic view of the open state of the present invention;

fig. 2 is a schematic view of the locking state of the present invention.

In the figure: 1. a base; 2. connecting blocks; 3. a first rotating pin; 4. a first rod pin; 5. a waist-shaped groove; 6. a handle; 7. a slider; 8. a rod pin II; 9. a first clamping jaw; 10. a safety screw; 11. a fixed mount; 12. a second jaw; 13. a rod pin III; 14. a beam; 15. a rod pin IV; 16. a tension spring; 17. a second rotating pin shaft; 18. a card slot; 19. and a stop block.

Detailed Description

The present invention will be further described with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and the protection scope of the present invention is not limited thereby.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.

As shown in fig. 1-2, a jaw for an aircraft tail support jack is disclosed, comprising:

the device comprises a connecting block 2, wherein a first clamping jaw 9 and a second clamping jaw 12 are hinged to two ends of the connecting block 2; the first jaw 9 is provided with a first rod pin 4 and a second rod pin 8; a third rod pin 13 and a fourth rod pin 15 are arranged on the second jaw 12; the second rod pin 8 and the third rod pin 13 are clamped at the upper part of the fixed frame 11;

the device comprises a fixed frame 11, wherein two sides of the fixed frame 11 are connected with sliding blocks 7, and the sliding blocks 7 are provided with waist-shaped grooves 5 for sliding of a rod pin I4; a clamping groove 18 is formed in the position, corresponding to the rod pin IV 15, of the fixed frame 11;

the bottom of the connecting block 2 is connected with a base 1, an elastic part is arranged between one end, close to the second clamping jaw 12, of the fixing frame 11 and the base 1, the elastic part is used for pulling the fixing frame 11, one end of the elastic part is fixed at one end, close to the second clamping jaw 12, of the fixing frame 11 during installation, and the other end of the elastic part is connected with the base 1.

Specifically, the first rod pin 4 is matched with the kidney-shaped groove 5 to play a limiting role, the first jaw 9 is limited to rotate along the first rotating pin shaft 3 by an angle, the fourth pin rod 15 is matched with the clamping groove 18 to lift the fixing frame 11 upwards, the fourth pin rod 15 is separated from the clamping groove 18, the fixing frame 11 moves towards the right (as shown in fig. 1) to open the first jaw 9 and the second jaw 12, and the first jaw 9 can only be opened by a certain angle due to the limitation of the first rod pin 4 and the fixing frame 11 while the first jaw 9 is opened, and the angle is set to be 15 degrees according to needs in the embodiment; the second jaw 12 is limited on the fixing frame 11 by the third rod pin 13, so that the second jaw 12 can only open for a certain angle, and in the embodiment, the angle is set to 15 degrees according to requirements.

As shown in fig. 2, when the two jaws are combined together, a safety hole (blocked by the slider 7) is formed in the position of the fixed frame 11 corresponding to the waist-shaped groove 5, the safety hole is provided with a safety screw 10 in a matching manner, so as to clamp the bar pin four 15 in the clamping groove 18, and at this time, due to a movable stop 19 arranged at the end of the slider 7, the stop 19 is stopped at the edge of the clamping groove 18, so as to ensure that the bar pin four 15 enters the clamping groove 18. As shown in fig. 2, when the sliding block 7 is pushed to the right until the safety hole on the fixing frame 11 is exposed in the waist-shaped groove 5, the mounting safety screw 10 is in threaded connection with the safety hole, so that the sliding block cannot move to the right, and the pin shaft 15 is ensured to be positioned in the clamping groove 18. The second bar pin 8 is located at the vertically upper portion of the fixing frame 11.

In this embodiment, one end of the fixing frame 11 is connected with a handle 6, the other end is provided with a rod beam 14 for connecting an elastic component, the rod beam 14 is arranged to facilitate the connection of the elastic component with the base 1, and the handle 6 can facilitate the clamping of the rod pin four 15 into the clamping or separating groove 18; the downward tension of the tension spring 16 in this embodiment maintains the jaws in the present condition.

In this embodiment, the two jaws move in the following manner: the two ends of the connecting block 2 are connected with the first jaw 9 and the second jaw 12 through the first rotating pin shaft 3 and the second rotating pin shaft 17 respectively, and the jaws rotate around the rotating pin shafts when being opened.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.

The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be considered as the protection scope of the present invention.

Claims

1. A jack catch for an aircraft tail support jack, comprising:

the device comprises a connecting block (2), wherein a first clamping jaw (9) and a second clamping jaw (12) are hinged to two ends of the connecting block (2); a first rod pin (4) and a second rod pin (8) are arranged on the first jaw (9); a third rod pin (13) and a fourth rod pin (15) are arranged on the second jaw (12);

the device comprises a fixed frame (11), wherein two sides of the fixed frame (11) are connected with sliding blocks (7), and the sliding blocks (7) are provided with waist-shaped grooves (5) for sliding of a rod pin I (4); a clamping groove (18) is formed in the position, corresponding to the rod pin IV (15), of the fixed frame (11);

the bottom of the connecting block (2) is connected with a base (1); an elastic part is arranged between one end of the fixing frame (11) close to the second clamping jaw (12) and the base (1), one end of the elastic part is connected with the fixing frame (11), and the other end of the elastic part is connected with the base (1).

2. Claw for an aircraft tail support jack according to claim 1, characterized in that the fixing frame (11) is provided with a safety hole corresponding to the waist-shaped groove (5), and the safety hole is provided with a safety screw (10) in a matching way.

3. Claw for an aircraft tail support jack according to claim 1, characterised in that the bar pin two (8) and the bar pin three (13) are clamped in the upper part of the fixing frame (11).

4. Claw for an aircraft tail support jack according to claim 1, characterised in that the holder (11) is connected at one end with a handle (6) and at the other end with a beam (14) for connection with an elastic member.

5. Jaw for an aircraft tail support jack, according to claim 1, characterized in that said connecting block (2) is connected at one end to a first jaw (9) by means of a first rotating pin (3) and at the other end to a second jaw (12) by means of a second rotating pin (17).

6. Jaw for an aircraft tail support jack according to claim 1, characterized in that said elastic member is a tension spring (16).